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NASA TECHNICAL
MEMORANDUM
CVJ
><
NASA TM X-2905
S!K>1
PERFORMANCE OF TRANSONIC FAN STAGE
WITH WEIGHT FLOW PER UNIT ANNULUS
AREA OF 198 KILOGRAMS PER SECOND
PER SQUARE METER (40.6 (LB SEC)/FT2)
by George Kovkh, Royce D. Moore, and Donald C. Urasek
Lewis Research Center
Cleveland, Ohio 44135
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION • WASHINGTON, D. C. • NOVEMBER 1973
https://ntrs.nasa.gov/search.jsp?R=19740001915 2020-03-20T21:22:17+00:00Z
1. Report No.
NASA TM X-29052. Government Accession No. 3. Recipient's Catalog No.
4. Title and Subtitle PERFORMANCE OF TRANSONIC FAN STAGE WITH
WEIGHT PLOW PER UNIT ANNULUS AREA OF 198 KILOGRAMSPER SECOND PER SQUARE METER (40.6 (LB/SEC)/FT2)
5. Report DateNovember 1973
6. Performing Organization Code
7. Author(s)
George Kovich, Royce D. Moore, and Donald C. Urasek8. Performing Organization Report No.
E-7205
9. Performing Organization Name and Address
Lewis Research CenterNational Aeronautics and Space AdministrationCleveland, Ohio 44135
10. Work Unit No.
501-2411. Contract or Grant No.
12. Sponsoring Agency Name and Address
National Aeronautics and Space AdministrationWashington, D. C. 20546
13. Type of Report and Period Covere4
Technical Memorandum14. Sponsoring Agency Code
15. Supplementary Notes
16. Abstract
The overall and blade-element performance are presented for an air compressor stage designedto study the effect of weight flow per unit annulus area on efficiency and flow range. At the de-sign speed of 424. 8 m/sec the peak efficiency of 0. 81 occurred at the design weight flow and atotal pressure ratio of 1. 56. Design pressure ratio and weight flow were 1. 57 and 29.5 kg/sec(65. 0 Ib/sec), respectively. Stall margin at design speed was 19 percent based on the weightflow and pressure ratio at peak efficiency and at stall.
17. Key Words (Suggested by Author(s))
Turbomachinery; Compressors; Transoniccompressors; Axial flow compressors;Turbofans
18. Distribution Statement
Unclassified - unlimited
19. Security Classlf. (of this report)
Unclassified20. Security Classif. (of this page)
Unclassified21. No. of Pages
91
22. Price*
Domestic, $3.75Foreign, $6.25
* For sale by the National Technical Information Service, Springfield, Virginia 22151
PERFORMANCE OF TRANSONIC FAN STAGE WITH WEIGHT FLOW PER
UNIT ANNULUS AREA OF 198 KILOGRAMS PER SECOND
PER SQUARE METER (40.6 (LB/SEO/FT2)»
by George Kovich, Royce D. Moore, and Donald C. Urasek•j
Lewis Research Center
SUMMARY
The overall performance and the blade-element performance are presented for atransonic axial-flow air compressor stage designed to study the effects of weight flowper unit annulus area on efficiency and flow range. The rotor is designed for a weightflow per unit annulus area of 198.2 kilograms per second per square meter and a tipspeed of 424. 8 meters per second. Design values of weight flow and pressure ratio are29. 5 kilograms per second and 1.57, respectively.
At design speed the peak efficiency of 0. 81 occurred at an equivalent weight flow of29.5 kilograms per second with a total pressure ratio of 1. 56. Stall margin at designspeed was 19 percent, based on weight flow and pressure ratio at peak efficiency and atstall.
The radial survey data indicate that the rotor-blade dampers had a considerableeffect on the blade-element losses. Losses at measured peak efficiency in general werehigher than design values for the rotor, while stator-blade losses were for the mostpart equal to design values except in the region behind the dampers and near the endwalls. Suction-surface incidence angles corresponding to minimum losses were within±1° of design values for the rotor. The stator minimum losses could be consideredconstant over a range of suction-surf ace incidence angles from about -6° to +2° formost of the blade span.
Rotor-blade deviation angles were as much as 3.5° less than the design values ex-cept in a portion of the damper region. Stator deviation angles exceeded design valuesby as much as 5° in the tip and hub regions but were close to design over the rest of theblade.
INTRODUCTION
A research program on axial-flow fans and compressors for advanced airbreathingengines is currently being conducted at the NASA Lewis Research Center. This pro-gram is primarily directed toward reducing the size and weight of fans and compressorswhile maintaining high levels of performance. In support of this program, experimentalstudies are being conducted to evaluate the effects of blade solidity, blade aspect ratio,blade loading, area margin above choke, different blade shapes, weight flow per unitanliulus area, velocity ratio, and blade spacing on efficiency and flow range.
• A series of tests are being conducted to evaluate the effect of weight flow per unitannulus area on the performance of axial-flow fan stages. Three stages were designedfor weight flows per unit annulus area of 178, 198, and 208 kilograms per second persquare meter. All three stages were designed to produce a pressure ratio of 1.57, andall had the same meridional flow path geometry. The performance of the first stage,with a weight flow of 178 kilograms per second per square meter, is presented in ref-erence 1, and that of the last stage, with a weight flow of 208 kilograms per second persquare meter, in reference 2.
This report presents the performance of an axial-flow fan stage designed for198 kilograms per second per square meter. It presents the aerodynamic designparameters and the overall and blade-element performance. Data were obtained overthe stable operating range of the stage for six rotative speeds from 50 to 100 percent ofdesign speed. Blade-element data were obtained for the rotor and the stator at 11 radialpositions. The stage discussed in this report has been designated "stage 11-4" withthe rotor being rotor 11 and the stator being stator 4. The data in this report are pre-sented in tabular and in machine-plotted form. The symbols and equations are given inappendixes A and B, respectively. The definitions and units used for the tabular dataare presented in appendix C.
AERODYNAMIC DESIGN
Three computer programs were used in the design of this compressor stage: thestreamline analysis program, the blade geometry program, and the blade coordinateprogram. These programs are described in references 3 and 4; only a brief descrip-tion of each is presented in this report.
The streamline analysis program was used to calculate the flow field parametersat several axial locations, including planes approximating the blade leading and trailingedges for both the rotor and stator. The weight flow, rotative speed, flow path geom-etry, and radial distributions of total pressure and temperature are inputs in this pro-
gram. The program accounts for both streamline curvature and entropy gradients;boundary-layer blockage factors are also included.
The distributions of velocity vector, total pressure, and total temperature calcu-lated in the streamline analysis program are used in the blade geometry program tocompute blade geometry parameters. The total loss, which is computed within the pro-gram, includes a calculated shock loss (as related to the selected blade shape) and aprofile loss. The profile losses used for this stage are based on loss - diffusion factorcorrelations that include the data presented in reference 1 for the rotor and in refer-ence 5 for the stator.
The blade geometry parameters are used in the blade coordinate program to com-pute blade elements on conical surfaces, approximating the stream surfaces passingthrough the blade. The blade elements are then stacked on a line passing through theircenters of gravity, and Cartesian blade coordinates, which are used directly in fabrica-tion, are computed.
The overall design parameters for stage 11-4 are listed in table I and the flow pathgeometry is shown in figure 1. This stage was designed for an overall pressure ratio
n
of 1. 57 at a weight flow of 29.5 kilograms per second (198.2 (kg/sec)/m of annulusarea). The design tip speed was 424.8 meters per second. The stage was designed fora tip solidity of 1.30 for the rotor and 1.27 for the stator. This resulted in 44 rotorblades with an aspect ratio of 2. 5 and 48 stator blades with an aspect ratio of 2. 4.
The blade-element design parameters for rotor 11 are presented in table n. Thisrotor was designed for a radially constant total pressure ratio of 1. 60. The statorblade element design parameters are given in table HI. The blade geometry is pre-sented in table IV for rotor 11 and in table V for stator 4. Both the rotor and statorhave multiple-circular-arc blade shapes.
The equations used for calculating overall blade-element performance parametersare presented in appendix B. All definitions and units of the parameters presented inthe tables are shown in appendix C.
APPARATUS AND PROCEDURE
Compressor Test Facility
The compressor stage was tested in the Lewis single-stage compressor facility(described in detail in ref. 6. A schematic diagram of the facility is shown in fig. 2).Atmospheric air enters the test facility at an inlet located on the roof of the building andflows through the flow measuring orifice and into the plenum chamber upstream of thetest stage. The air then passes through the experimental compressor stage into thecollector and is exhausted to the atmosphere.
Test Stage
Photographs of the rotor and stator are shown in figures 3 and 4. Each rotor bladehas a vibration damper located at about 50 percent span from the outlet rotor tip. Themaximum thickness of the damper was 0.213 centimeter. The nonrotating radial tipclearance of the rotor was a nominal 0. 050 centimeter at ambient conditions. The axialspacing between the rotor hub trailing edge and the stator hub leading edge was3.20 centimeters.
Instrumentation
The compressor weight flow was determined from measurements on a calibratedthin-plate orifice. The temperature at the orifice was measured with two Chromel-Alumel thermocouples. Pressures at the orifice were measured by calibrated trans-ducers.
Radial surveys of the flow were made upstream of the rotor, between the rotor andstator, and downstream of the stator (fig. 1). Photographs of the survey probes areshown in figure 5. Total pressure, total temperature, and flow angle were measuredwith the combination probe (fig. 5(a)), and the static pressure was measured with an8° C-shaped wedge probe (fig. 5(b)). Each probe was positioned with a null-balancing,stream-directional sensitive control system that automatically alined the probe to thedirection of flow. The probes were angularly alined in an air tunnel. One combinationprobe and one wedge static probe were used at each of the three measuring stations.The thermocouple was of the iron/constantan type.
Inner- and outer-wall static pressure taps were located at the same axial stationsas the survey probes. The circumferential locations of both types of survey probesalong with inner- and outer-wall static-pressure taps are shown in figure 6. The com-bination probe downstream of the stator (station 3) was circumferentially traversed onestator blade passage (7.5°) counterclockwise from the nominal value shown.
An electronic speed counter, in conjunction with a magnetic pickup, was used tomeasure rotative speed (rpm).
The estimated errors of the data based on inherent accuracies of the instrumenta-tion and recording system are as follows:
Weight flow, kg/sec ±0.3Rotative speed, rpm ±30Flow angle, deg ±1Temperature, K ±0. 6
O
Rotor inlet total pressure, N/cm ±0. 012Rotor outlet total pressure, N/cm ±0.102Stator outlet total pressure, N/cm ±0.10
2Rotor inlet static pressure, N/cm ±0. 04oRotor outlet static pressure, N/cm ±0. 07
9Stator outlet static pressure, N/cm ±0.07
A further indication of the consistency of the data can be observed by comparing the in-tegrated weight flow at each measuring station with the orifice weight flow in table VI.
Test Procedure
The stage survey data were taken over a range of weight flows from maximum flowto the near-stall conditions. At 70, 90, and 100 percent of design speed, radial surveyswere taken at five weight flows. At 50, 60, and 80 percent of design speed, radial sur-veys were taken for the near-stall weight flow only. Data were recorded at 11 radialpositions for each speed and weight flow.
At each radial position the combination probe behind the stator was circumferen-tially traversed to nine different locations across the stator gap. The wedge probe wasset at midgap because previous studies showed that the static pressure across the statorgap was nearly constant. Values of pressure, temperature, and flow angle were re-corded at each circumferential position. At the last circumferential position values ofpressure, temperature, and flow angle were also recorded at stations 1 and 2. Allprobes were then traversed to the next radial position, and the circumferential traverseprocedure repeated.
At each of the six rotative speeds the back pressure on the stage was increased byclosing the sleeve valve in the collector until a stalled condition was detected by a sud-den drop in stage outlet total pressure. This pressure was measured by a probe locatedat midpassage and was recorded on an X-Y plotter. Stall was corroborated by largeincreases in the measured blade stresses on both rotor and stator along with a suddenincrease in noise level.
Calculation Procedure
The measured total temperatures and total pressures were corrected for Machnumber and streamline slope. These corrections were based on instrument probe cali-brations given in reference 7. The stream static pressure was corrected for Machnumber and streamline slope based on an average calibration for the type of probe used.
Because of the physical size of the C-shaped static pressure wedges, it was notpossible to obtain static pressure measurements at 5, 10, and 95 percent of span. Thestatic pressure at 95 percent span was obtained by assuming a linear variation in staticpressure between the values at the inner wall and the probe measurement at 90 percentspan. A similar variation was assumed between the static pressure measurements atthe outer wall and the 30 percent span to obtain the static pressure at 5 and 10 percentspan.
At each radial position, averaged values of the nine circumferential measurementsof pressure, temperature, and flow angle downstream of the stator (station 3) were ob-tained. The nine values of total temperature were mass averaged to obtain the statoroutlet total temperature. The nine values of total pressure were energy averaged. Themeasured values of pressure, temperature, and flow angle were used to calculate axialand tangential velocities at each circumferential position. The flow angles presentedfor each radial position are calculated based on these mass averaged axial and tangentialvelocities. To obtain the overall performance, the radial values of total temperaturewere mass averaged, and the values of total pressure were energy averaged. At eachmeasuring station the integrated weight flow was computed based on the radial surveydata.
The data, measured at the three measuring stations, were translated to the rotorand stator blade leading and trailing edges by the method presented in reference 4.
The weight flow at stall was obtained in the following manner: During operation inthe near-stall condition, the collector valve was slowly closed in small increments. Ateach increment the weight flow was obtained. The weight flow obtained just before stalloccurred is called the stall weight flow. The pressure ratio at stall was obtained byextrapolating the total pressure obtained from the survey data to the stall weight flow.
Orifice weight flow, total pressures, static pressures, and temperatures were allcorrected to sea-level conditions based on the rotor inlet conditions.
RESULTS AND DISCUSSION
The results from this investigation will be presented in three main sections. Theoverall performances for the rotor and the stage are presented first. Radial distribu-
6
tions of several performance parameters are then presented for the rotor and stator.Finally, the blade-element data are presented for both the rotor and stator. The datapresented are computer plotted; occasionally, a data point will be omitted because itfalls outside the range of the parameters shown in the figure.
All plotted data and some additional performance parameters are presented in tabu-lar form. The overall performance data are presented in table VI. The blade-elementdata are presented first for the rotor and then for the stator in tables VII and vm. Thedefinitions and units used for the tabular data are presented in appendix C.
Overall Performance
The overall performance for rotor 11 and for stage 11-4 are presented in figure 7and 8. In both of these computer plotted figures, data are presented for speeds from50 to 100 percent of design speed. For the 70, 90, and 100 percent of design speedsdata are presented at several weight flows from choke to the near-stall conditions. Forthe 50, 60, and 80 percent of design speeds, the overall performance is presented forthe near-stall condition only. (Design-point values are shown as solid symbols in bothfigures.) The stall line (dashed line) shown in figure 8 was determined using the methoddiscussed in the section Test Procedure.
The experimental total pressure and total temperature ratios attained by the stagewere 1. 557 and 1.167, respectively, at the design weight flow of 29.5 kilograms persecond. The experimental stage peak efficiency of 0. 81 was 5 points less than the de-sign value and occurred at design weight flow. Experimental rotor peak efficiency wasalso 5 points less than design, indicating that the low stage efficiency could be attributedto the rotor. The maximum measured efficiencies for the rotor and the stage at thelower speeds were slightly higher than the peak efficiency measured at design speed.
Stall margin at design speed was 19 percent based on weight flows and stage totalpressure ratios at peak efficiency and at stall.
Blade-Element Performance - Radial Distributions
The radial distribution of selected flow and performance parameters at design speedare shown in figure 9 for the rotor and in figure 10 for the stator. The data shownrepresents the flow conditions at near stall, peak efficiency, and choke. (Design valuesare shown by solid symbols.) Flow and performance results at the peak efficiencyweight flow of 29.5 kilograms per second are compared with the design values.
Rotor. - The local values of pressure ratio at the measured peak efficiency weightflow were equal to or slightly lower than design values except in the tip region. Thetemperature rise efficiency was less than design over the entire blade span, with thegreatest difference occurring in the damper region. Losses, as evidenced by the totalloss parameter and total loss coefficient, were higher than design values over the wholeblade span. The dampers located at the 50 percent radial span position appear to haveinfluenced the losses particularly over the 30 to 70 percent portion of the blade span.Deviation angles were as much as 3.5° lower than design values except in a portion ofthe damper region. Measured D-factor was comparable with the design values.
Stator. - The design suction-surf ace incidence angles were obtained experimentallyexcept in the region behind the rotor blade dampers. Stator deviation angles were with-in 2° except at the tip and hub regions. In these regions the deviation angles were asmuch as 5° higher than the design values. Stator losses, as evidenced by the total lossparameter, were equal to design except in the region of the rotor blade dampers and thetip and hub. Stator blade D-factor was comparable with the design values. Although theeffect of the rotor-blade dampers was not considered in the design of the rotor bladeand stator blade, the experimental data indicate that the stator design objective wasreasonably attained.
Variations with Incidence Angle
The variations of selected blade-element performance parameters are presented in'figure 11 for the rotor and in figure 12 for the stator. The data are presented for 60,80, and 100 percent of design speed at the blade-element locations at 5, 10, 30, 45, 70,90, and 95 percent of blade span (measured from the tip). (Design values are shown bysolid symbols.) These blade-element performance curves are presented primarily forfuture reference, to be compared with results for other blade shapes. Only a few briefobservations are made in this section.
Both the rotor and stator blades were designed for a zero incidence angle at theblade suction-surf ace leading edge. Except at the hub, measured suction-surf ace inci-dence angles corresponding to minimum losses were within ±1° of the design values forthe rotor blade. The minimum losses for the stator could be considered constant overa range of suction-surf ace incidence angles from about -6° to 2° for most of the bladespan. The variation of stator losses with incidence angle as indicated by the total lossparameter or the total loss coefficient remained essentially constant from 60 to 100 per-cent of design speed.
SUMMARY OF RESULTS
The overall and blade-element performance are presented for a transonic axial-flow compressor stage. The rotor was designed for a tip speed of 424. 8 meters persecond and a weight flow per unit annulus area of 198.2 kilograms per second persquare meter. Design values of weight flow, pressure ratio, and temperature ratio were29. 5 kilograms per second, 1.57 and 1.16, respectively. The investigation yielded thefollowing principal results:
1. At design speed the stage peak efficiency of 0. 81 occurred at design weight flow.The stage total pressure ratio was 1. 56 and the stage total temperature ratio was 1.17.
2. Stall margin at design speed was 19 percent, based on weight flows and pressureratio at peak efficiency and at stall.
3. The rotor blade losses were in general higher than design. The blade damperlocated at 50 percent span from the tip appeared to have considerable effect on theselosses. Stator blade losses were equal to design values except in the region behind therotor dampers and near the end walls.
4. Suction-surface incidence angles corresponding to minimum losses were within±1° of the design values for the rotor blades except at the hub. The minimum lossesfor the stator could be considered constant over a range of incidence angles from -6° to2° for most of the blade span.
5. Deviation angles for the rotor were as much as 3. 5° less than the design valuesexcept in a portion of the damper region. Stator deviation angles exceeded design valuesby as iblade.by as much as 5° in the'tip and hub regions but were close to design over the rest of the
Lewis Research Center,National Aeronautics and Space Administration,
Cleveland, Ohio, July 11, 1973,501-24.
APPENDIX A
SYMBOLS
2A annulus area at rotor leading edge, 0.147 man
2A. frontal area at rotor leading edge, 0.198 m
C specific heat at constant pressure, 1004 J/(kg)(K)
c aerodynamic chord, cm
D diffusion factor2
g acceleration of gravity, 9. 81 m/sec
i mean incidence angle, angle between inlet air direction and line tangent to blademean camber line at leading edge, deg
i__ suction-surface incidence angle, angle between inlet air direction and line tan-ssgent to blade suction surface at leading edge, deg
J mechanical equivalent of heat
N rotative speed, rpm2
P total pressure, N/cmn
p static pressure, N/cm
r radius, cm
SM stall margin
T total temperature, K
U wheel speed, m/sec
V air velocity, m/sec
W weight flow, kg/sec
Z axial distance referenced from rotor blade hub leading edge, cm
otc cone angle, deg
a slope of streamline, degs
/3 air angle, angle between air velocity and axial direction, deg
)3* relative meridional air angle based on cone angle, arctan (tan /3' cos a /cos or_),{* m c sdeg
y ratio of specific heats (1. 40)
10
o6 ratio of rotor inlet total pressure to standard pressure of 10.13 N/cm
6° deviation angle, angle between exit air direction and tangent to blade mean cam-ber line at trailing edge, deg
6 ratio of rotor inlet total temperature to standard temperature of 288.2 K
TJ efficiencyKmc angle between the blade mean camber line and the meridional plane, deg
K_O angle between the blade suction-surf ace camber line at the leading edge and theoo
meridional plane, deg
a solidity, ratio of chord to spacing
~u> total loss coefficient
"oL profile loss coefficient
~co_ shock loss coefficientsSubscripts:
ad adiabatic (temperature rise)
id ideal
LE blade leading edge
m meridional direction
mom momentum-rise
p polytropic
r radial direction
ref reference
TE blade trailing edge
z axial direction
6 tangential direction
1 instrumentation plane upstream of rotor
2 instrumentation plane between rotor and stator
3 instrumentation plane downstream of stator
Superscript:
' relative to blade
11
APPENDIX B
EQUATIONS
Suction surface incidence angle -
LE 'ss (Bl)
Mean incidence angle -
" (Kmc)LE(B2)
Deviation angle -
= (^c)TE - (*mc)TE(B3)
Diffusion factor -
D = !-v1
VLE(B4)
Total loss coefficient -
CO =(pid)TE - (p')TE
(B5)
Profile loss coefficient -
cop = co - (B6)
Total loss parameter -
CO COSTE
(B7)
12
Profile loss parameter -
_ cosP
2(7
Adiabatic (temperature-rise) efficiency -
TLE
Momentum-rise efficiency -
. >-D/rTE
.
(B8)
Equivalent weight flow -
W^ (Bll)6
Equivalent rotative speed -
— (B12)V0
Weight flow per unit annulus area -
6— (B13)Aan
13
Weight flow per unit frontal area -
W
(B14)
Head-rise coefficient -
U2Utip
TE\(y-D/r
-1 (B15)
Flow coefficient -
(B16)
Stall margin -
SM =
TE
'LE,fw
stall
TE
x - 1 x 100
ref6 /stall
(B17)
Polytropic efficiency -
Tjp = exp
TE
LTE
(B18)
14
APPENDIX C
ABS
AERO CHORD
AREA RATIO
BETAM
CONE ANGLE
DELTA INC
DEV
D-FACT
EFF
IN
INCIDENCE
KIC
KOC
KTC
LOSS COEFF
LOSS PARAM
MERID
MERID VEL R
OUT
PERCENT
SPAN
PHISS
DEFINITIONS AND UNITS USED IN TABLES
absolute
aerodynamic chord, cm
ratio of actual flow area to critical area (where local Mach number isone)
meridional air angle, deg
angle between axial direction and conical surface representing bladeelement, deg
difference between mean camber blade angle and suction-surf ace bladeangle at leading edge, deg
deviation angle (defined by eq. (B3)), deg
diffusion factor (defined by eq. (B4))
adiabatic efficiency (defined by eq. (B9))
inlet (leading edge of blade)
incidence angle (suction surface defined by eq. (Bl) and mean definedbyeq. (B2))
angle between the blade mean camber line at the leading edge and themeridional plane, deg
angle between the blade mean camber line at the trailing edge and themeridional plane, deg
angle between the blade mean camber line at the transition point andthe meridional plane, deg
loss coefficient (total defined by eq. (B5) and profile defined by eq. (B6))
loss parameter (total defined by eq. (B7) and profile defined by eq. (B8))
meridional
meridional velocity ratio
outlet (trailing edge of blade)
percent of blade span from tip at rotor outlet
suction surface camber ahead of assumed shock location, deg
15
PRESS
PROF
RADII
REL
RI
RO
RP
RPM
SETTING ANGLE
SOLIDITY
SPEED
SS
STREAMLINESLOPE
TANG
TEMP
TI
TM
TO
TOT
TOTAL CAMBER
VEL
WT FLOW
X FACTOR
ZIC
ZMC
ZOC
ZTC
pressure, N/cm
profile
radius, cm
relative to the blade
inlet radius (leading edge of blade), cm
outlet radius (trailing edge of blade), cm
radial position
equivalent rotative speed, rpm
angle between aerodynamic chord and meridional plane, deg
ratio of aerodynamic chord to blade spacing
speed, m/sec
suction surface
slope of streamline, deg
tangential
temperature, K
thickness of blade at leading edge, cm
thickness of blade at maximum thickness, cm
thickness of blade at trailing edge, cm
total
difference between inlet and outlet blade mean camber lines, deg
velocity, m/sec
equivalent weight flow, kg/sec
ratio of suction-surf ace camber ahead of assumed shock location ofa multiple circular arc blade section to that of a double-circular-arc blade section
axial distance to blade leading edge from inlet, cm
axial distance to blade maximum thickness point from inlet, cm
axial distance to blade trailing edge from inlet, cm
axial distance to transition point from inlet, cm
16
REFERENCES
1. Moore, Royce D.; Urasek, Donald C.; and Kovich, George: Performance of Tran-sonic Fan Stage with Weight Flow per Unit Annulus Area of 178 Kilograms perSecond per Square Meter (36. 5 (lb/sec)/ft2). NASA TM X-2904, 1973.
2. Urasek, Donald C.; Kovich, George; and Moore, Royce D.: Performance of Tran-sonic Fan Stage with Weight Flow per Unit Annulus Area of 208 Kilograms perSecond per Square Meter (42. 6 (lb/sec)/ft2). NASA TM X-2903, 1973.
3. Ball, Calvin L.; Janetzke, David C.; and Reid, Lonnie: Performance of a1380 Foot-Per-Second Tip-Speed Axial-Flow Compressor Rotor with Blade TipSolidity of 1. 5. NASA TM X-2379, 1971.
4. Crouse, James E.; Janetzke, David C.; and Schwirian, Richard E.: A ComputerProgram for Composing Compressor Blading from Simulated Circular-ArcElements on Conical Surfaces. NASA TN D-5437, 1969.
5. Keenan, M. J.; and Bartok, J. A.: Experimental Evaluation of Transonic Stators,Data and Performance Report, Multiple-Circular-Arc Stator B. Rep. PWA-3356,Pratt & Whitney Aircraft (NASA CR-54622), 1968.
6. Urasek, Donald C.; and Janetzke, David C.: Performance of Tandem-Bladed Tran-sonic Compressor Rotor with Tip Speed of 1375 Feet-Per-Second. NASA TMX-2484, 1972.
7. Glawe, George E.; Krause, Lloyd N.; and Dudzinski, Thomas J.: A Small Com-bination Sensing Probe for Measurement of Temperature, Pressure, and FlowDirection. NASA TN D-4816, 1968.
17
TABLE I. - DESIGN OVERALL PARAMETERS
FOR STAGE 11-4
ROTOR TOTAL PRESSURE RATIO 1.601STAGE TOTAL PRESSURE RATIOi 1.574ROTOR TOTAL TEKPERATURE RATIO 1.162STAGE TOTAL TEMPERATURE RATIO 1.162ROTOR AOIABATIC EFFICIENCY 0.889STAGE ADIABATIC EFFICIENCY 0.855ROTOR POLYTROPIC EFFICIENCY 0.896STAGE POLYTROP 1C EFFICIENCY 0.864ROTOR HEAD RISE COEFFICIENT 0.231STAGE HEAD RISE COEFFICIENT, 0.222FLOW COEFFICIENT 0.45?HT FLOW PER UNIT FRONTAL AREA U7.822WT FLOW PER UNIT ANNULUS AREA 198.166HT FLOW 29.484RPM 16100.000TIP SPEED 424.815
18
TABLE H. - DESIGN BLADE-ELEMENT PARAMETERS FOR ROTOR 11
RADIIRPTIP
123456789
1011HUB
IN25.1972^.62824.06021.74119.96019.65819.35619.05218.74716.87114.20213.49212.700
OUT24.81624.28023.74421.60019.99219.72419.45619.18818.92017.31315.16914.63314.097
ABS VELRPTIP
123456789
1011HUB
IN179.2184.1188.4198.8201.7201.9202.0202.0201.9200.0192.9190. e188.0
OUT199.9199.1199.2204.3210.0211.2212.4213.6215.0224.2241.9248.1255.2
ABS MACH NORPTIP
123456789
10UHUB
IN0.5420.5580.5710.6050.6150.6150.6160.6160.6150.6090.5860.5790.570
OUT0.5530.5540.5560.5750.5940.5970.6010.6050.6090.6380.6930.7120.734
ABSIN0.
-0.0.0.0.0.0.0.0.0.0.0.0.
RELIN
461.1454.2447.3417.0392.3388.1383.8379.4375.0347.7307.5296.8284.9
BET AMOUT43.141.340.039.340.040.240.440.740.942.545.847.148.4
VELOUT
317.2315.8312.2283.2258.2253.9249.7245.4241.2216.9187.6181.1175.6
REL MACH NOIN
1.3941.376
.357
.270
.196
.183
.170
.157
.143
.0590.9340.9010.864
PERCENT INCIDENCERPTIP
123456789
1011HUB
SPAN0.5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
100.00
MEAN2.52.83.4.4.5.5.5.5.6.7.7.7.
01912453356
SS-0.0-0.0
0.0-0.0
0.00.00.00.0
-0.00.00.00.0
-0.1
OUT0.8780.8780.8720.7970.7300.7180.7070.6950.6830.6170.5370.5200.505
DEV
4.84.44.02.92.72.72.72.82.83.55.66.37.1
REL BETAMIN
67.166.165.161.559.158.758.257.857.454.951.150.048.7
MERIDIN
179.2184.1188.4198.8201.7201.9202.0202.0201.9200.0192.9190.6188.0
OUT62.661.760.756.051.550.649.748.747.640.426.021.015.4
VELOUT
145.9149.7152.7158.2160.8161.2161.6162.0162.5165.3168.6169.0169.3
MERID MACH NOIN
0.5420.5580.5710.6050.6150.6150.6160.6160.6150.6090.5860.5790.570
D-FACT
0.4250.4130.4070.4240.4490.4530.4580.4620.4670.4920.5190.5240.523
OUT0.4040.4160.4260.4450.4550.4560.4570.4590.4600.4700.4830.4850.487
EFF
0.7280.7740.8130.8840.9U0.9180.9210.9240.9270.9420.9380.9290.917
TOTAL TEMPIN
288.2288.2288.2288.2288.2288.2288.2288.2288.2288.2288.2288.2288.2
RATIO.198.186.177
.163
.157
.157
.1561.1561.1551.1531.1531.1551.157
TANG VELIN0.
-0.0.0.0.0.0.0.0.0.0.0.0.
OUT136.7131.3127.9129.3135.1136.4137.8139.2140.8151.5173.5181.7191.0
STREAMLINE SLOPEIN
-5.69-5.12-4.46-0.98
2.142.703.283.864.468.45
15.3817.5820.23
OUT-8.84-7.72-6.60-2.24
0.871.391.922.442.976.33
11.4412.8714.35
LOSS COEFFTOT0.2120.1710.1400.0880.0690.0670.0650.0630.0620.0540.0690.0840.107
PROF0.1190.0850.0580.0240.0160.0160.0160.0160.0160.0200.0520.0730.102
TOTALIN
10.1310.1310.1310.1310.1310.1310.1310.1310.1310.1310.1310.1310.13
WHEELIN
424.8415.2405.7366.5336.5331.4326.3321.2316.1284.4239.4227.5214.1
MERIDVEL R0.8140.8130.8100.7960.7970.7990.8000.8020.8050.8260.8740.8870.901
PRESSRATIO1.6011.6011.6011.601
.601
.601
.601
.601
.601
.601
.601
.601
.601
SPEEDOUT
418.4409.4400.3364.2337.1332.6328.0323.5319.0291.9255.7246.7237.7
PEAK SSMACH NO
1.5621.5491,5391.5191.5091.5081.5071.5061.5061.5011.4671.4311.379
LOSS PARAMTOT0.0380.0310.0250.0170.0130.0130.0130.0120.0120.0110.0140.0170.020
PROF0.0210.0150.0100.0040.0030.0030.0030.0030.0030.0040.010O.OU0.019
19
TABLE m. - DESIGN BLADE-ELEMENT PARAMETERS FOR STATOR 4
RADIIRPTIP
123456789
t o11HUB
IN24.39423.91923.45321.55720.11319.87219.63019.38819.14617.69215.75515.27314.643
OUT24.38423.90823.45921.63620.26520.03819.81019.58219.35518.00416.23915.80515.240
ABS vaRPTIP
123A56789
1011HUB
IN224.5222.9222.1223.4226.7227.5228.3229.3230.2237.4251.3256.2263.6
OUT177.1176.2176.0179.2179.9180.0180.2180.4180.6182.3182.5181.4179.3
ABS HACH NORPTIP
123456789
1011HUB
iN0.6260.6250.6250.6330.6440.6470.6500.6530.6560.6790.7230.7380.761
OUT0.4870.4870.4880.5010.5040.5040.5050.5060.5060.5120.5120.5090.502
ABSIN
38.336.735.735.536.336.536.736.937.238.641.642.844.4
RELIN
224.5222.9222.1223.4226.7227.5228.3229.3230.2237.4251.3256.2263.6
BET AMOUT0.
-0.0.0.0.0.0.0.0.0.0.0.
-0.
VELOUT
177.1176.2176.0179.2179.9180.0180.2180.4180.6182.3182.5181.4179.3
REL MACH NOIN
0.6260.6250.6250.6330.6440.6470.6500.6530.6560.6790.7230.7380.761
PERCENT INCIDENCERPTIP
123456789
1011HUB
SPAN0.5.00
10.0030.0045.0047.5050,0052.5055.0070.0090.0095.00
100.00
MEAN6.6.6.6.6.6.6.6.6.6.6.6.6.
4444444444332
SS-0.0
0.0-0.0
0.00.00.00,00.00.00.00.00.0
-0.0
OUT0.4870.4870.4880.5010.5040.504-0.5050.5060.5060.5120.5120.5090.502
DEV
10.79.79.08.28.08.08.Q8.08.07.98.18.38.5
REL BETAMIN
38.336.735.735.536.336.536.736.937-. 238.641.642.844.4
MERIDIN
176.1178.7180.5181.9182.6182.8183.0183.2183.5185.4187.8188.1188.3
OUT0.
-0.0.0.0.0.0.0.0.0.0.0.
-0.
VELOUT
177.1176. 2176.0179.2179.9180.0180.2180.4180.6182.3182.5181.4179.3
MERID MACH NOIN
0.4910.5010.5080.5150.5190.5200.5210.5220.5230.5300.5400.5420.543
D-FACT
0.4550.4410.4280.3990.3990.399Q.4QO0.4010.4020.4100.4420.4580.483
OUT0.4870.4870.4880.5010.5040.5040.5050.5060.5060.5120.5120.5090.502
EFT
0.0.0.0.0.0.0.0.0.0.0.0.0.
TOTAL TEMPIN
345.2341.7339.1335.0333.5333.3333.2333.0332.9332.2332.3332.8333.5
RATIO.000.000.000.000.000.000.000.000.000.000.000.000.000
TANG VELIN
139.3133.3129.5129.6134.3135.4136.5137.8139.1148.2167.0174.0184.4
OUT0.
-0.0.0.0.0.0.0.0.0.0.0.
-0.
STREAMLINE SLOPEIN
-(.16-0.70-0.29
1.232.592.843.093.363.635.488.689.65
10.99
OUT-0.06o.n0.260.911.54t.651.771.892.0)2.814.024.304.64
LOSS COEFFTOT0.0800.0820.0790.0470.0510.0520.0530.0540.0550.0600.0880.1110.146
PROF0.0800.0820.0790.0470.0510.0520.0530.0540.0550.0600.0880.1110.146
TOTALIN
16.2216.2216.2216.2216.2216.2216.2216.2216.2216.2216.2216.2216.22
WHEELIN0.0.0.0.0.0.0.0.0.0.0.0.0.
KERIDVEL R1.0060.9860.9750.9850.9850.9850.9850.9840.9840.9830.9720.9640.952
PRESSRATIO0.9830.9810.9820.9890.9880.9870.9870.9870.9860.9840.9740.9660.953
SPEEDOUT0.o.0.0.0.0.0.0.0.0.0.0.0.
PEAK SSMACH NO
0.9050.8840.8700.8650.8780.8820.8860.8900.8940.9250.9921.0171.055
LOSS PARAHTOT0.0320.0310.0300.0160.0170.0170.0170.0170.0170.0170.0230.0270.035
PROF0.0320.0310.0300.0160.0170.0170.0170.0170.0170.0170.0230.0270.035
20
TABLE IV. - BLADE GEOMETRY FOR ROTOR 11
RPTIP
123456789
1011HUB
PERCENTSPAN
0.5.10.30.45.48.50.53.55.70.90.95.100.
BLADERPTIP1234567891011HU3
TI0000000000000
.051
.051
.051
.051
.051
.051
.051
.051
.051
.051
.051
.051
.051
AERORPTIP
1234567891011HUB
CHORD4444444444444
.634
.628
.625
.616
.614
.615
.615
.616
.618
.635
.716
.753
.830
RADIIRI RO
25.197 24.81624.623 24.28024.060 23.74421.741 21.60019.960 19.99219.658 19.72419.356 19.45619.052 19.18818.74716.87114.20213.49212.700
18.92017.31315.16914.63314.097
BLADE ANGLESKIC KTC KOC64.37 62.97 57.7163.11 61.83 57.2661.90 60.58 56.6557.35 54.88 53.1554.13 50.29 48.7953.59 49.49 47.8753.05 48.68 46.9152.51 47.86 45.89514844
.97
.65
.0542.8241
THICKNESSESTM0.1520.1620.1720.2150.2480.2540.2600.2650.2710.3060.3560.3700.385
SETTINGANGLE62.6761.5360.3355.2050.8650.0649.2448.3947.5241.6630.4526.8522.79
TO0.0510.0510.0510.0510.0510.0510.0510.0510.0510.0510.0510.0510.051
TOTALCAMBER6.665.855.254.215.345.726.156.627.1611.9123.8628.3433.41
.44
47.0242.0734.0031.9329.85
44.8236.7420.1914.488.02
DELTA CONEINC ANGLE2.53 -10.4312.78 -9.1823.04 -8.0354.13 -3.0954.95 0.6515.09 1.2915.22 1.9355.36 2.5815.496.307.287.497.69
3.2327.40313.91915.77418.485
AXfAL DIMENSIONSZIC1.1.0.0.0.0.0.0.0.0.0.0.0.
046002955761621598574550526377147079000
SOLIDITYt
f
r
1.1.2.2.2.
298325355492618641665691717899249367525
ZMC2.0392.0402.0402.0272.0212.0192.0182.0172.0162.0031.9891.9831.972
XFACTOR0.7040.7470.7991.011.110.122.132.142.151.165.242
1.2561.251
ZTC2.4442.4152.3812.1912.003.967.930.892.852.588.143.013
0.861
PHISS4.945.045.307.128.718.999.279.559.8511.3013.9714.5114.85
3333333333444
ZOC.116.156.198.363.502.527.553.579.606.774.050.116.179
AREARATIO1.0401.0401.0401.0391.0391.0391.0391.0391.0391.0391.0401.0401.041
21
TABLE V. - BLADE GEOMETRY FOR STATOR 4
RPTIP123456789
1011HUB
PERCENT RADIISPAN RI RO
0.5.10.30.45.48.50.53.55.70.90.95.100.
24.39423.91923.45321 .55720.11319.87219.63019.38819.14617.69215.75515.27314.643
24.38423.90823.45921.63620.26520.03819.81019.58219.35518.00416.23915.80515.240
BLADE ANGLES1C 1C KTC KOC
31302929293030303032353638
BLADE THICKNESSESRPTIP
1234567891011HUB
RPTIP
1234567891011HUB
TI0.0510.0510.0510.0510.0510.0510.0510.0510.0510.0510.0510.0510.051
AEROCHORD4.0534.0534.0534.0544.0564.0564.0574.0584.0584.0654.0834.0884.098
TM0.2790.2790.2790.2790.2790.2790.2790.2790.2790.2790.2790.2790.279
TO0.0510.0510.0510.0510.0510.0510.0510.0510.0510.0510.0510.0510.051
.97
.32
.26
.04
.94
.14
.35
.57
.81
.31
.44
.61
.35
DELTAINC
26.38 -10.6725.4124.8024.9625.8326.0126.2026.4026.6127.9730.6831.6633.10
-9.67-9.00-8.21-8.02-8.01-7.99-7.98-7.97-7.93-8.11-8.25-8.48
6.386.406.416.416.406.396.396.396.386.366.306.286.25
CONEANGLE
-0.151-0.1600.0921.1582.2482.4502.6592.8743.0964.6217.2327.9608.954
AXIAL DIMENSIONSZ1C7.7.7.7.7.7.7.7.7.7.7.7.7.
085068056047052053055056057066095106123
SETTING TOTALANGLE15.8114.9014.3314.1314.5414.6414.7414.8414.9615.6717.1917.7618.62
CAMBER42.6340.0038.2737.2637.9638. 1438.3438.5538.7840.2443.5544.8646.83
SOLIDITY.
(.
t1.1.1.1.2.2.
270295320434535553572591611740950010095
ZMC8.8978.9018.9028.8988.8968.8958.8948.8948.8938.8868.8808.8768.871
XTACTOR0.6000.6000.6000.6000.6000.6000.6000.6000.6000.6000.6000.6000.600
ZTC8.4158.3358.2738.1678.1218.1158.1088.1028.0968.0578.0258.0228.020
PHISS10.339.418.778.057.927.927.917.917.917.928.188.358.62
10101010101010101010101010
zoc.935.935.933.928.926.925.925.924.924.919.916.914.911
AREARATIO.194.184.176.157.141.138.135.132.129
1.1061.0771.0701.061
22
TABLE VI. - OVERALL PERFORMANCE FOR STAGE 11-4
(a) 100 Percent of design speed
Parameter
ROTOR TOTAL PRESSURE RATIOSTAGE TOTAL PRESSURE RATIOROTOR TOTAL TEMPERATURE RATIOSTAGE TOTAL TEMPERATURE RATIOROTOR TEMP. RISE EFTtCIENCYSTAGE TEMP. RISE EFFICIENCYROTOR MOMENTUM RISE EFFICIENCYROTOR HEAD RISE COEFFICIENTSTAGE HEAD RISE COEFFICIENTFLOW COEFFICIENTWT FLOW PER UNIT FRONTAL AREAWT FLOW PER UNIT ANNULUS AREAWT FLOW AT ORIFICEWT FLOW AT ROTOR INLETWT FLOW AT ROTOR OUTLETWT aOW AT STATOR OUTLETROTATIVE SPEEDPERCENT OF DESIGN SPEED
Reading number
968
1.4871.4561.147I.U30.8160.7940.8030.1940.1830.422
150.26201.4429.9730.0330.1530.21
16046.799.7
969
1.5961.5571.1701.1670.8380.8090.8280.2290.2160.411
147.80198.1329.4829.5529.6329.78
16122.1100.1
970
1.6501.6031.1861.1830.8260.7880.8320.2470.2320.386
141.09189.1328. U28.2228.3428.78
16100.5100.0
975
1.6711.6111.1931.1930.8180.7560.8190.2550.2350.359
133.50178.9726.6326.5927.5327.80
16059.499.7
978
1.6701.6051.1941.1940.8120.7460.8140.2550.2340.353
131.55176.3426.2426.2527.3127.53
16042.499.6
(b) 90 Percent of design speed
Parameter
ROTOR TOTAL PRESSURE RATIOSTAGE TOTAL PRESSURE RATIOROTOR TOTAL TEMPERATURE RATIOSTAGE TOTAL TEMPERATURE RATIOROTOR TEMP. RISE EFFICIENCYSTAGE TEMP. RISE EFFICIENCYROTOR MOMENTUM RISE EFFICIENCYROTOR HEAD RISE COEFFICIENTSTAGE HEAD RISE COEFFICIENTFLOW COEFFICIENTWT FLOW PER UNIT FRONTAL AREAWT FLOW PER UNIT ANNULUS AREAWT aOW AT ORIFICEWT aOW AT ROTOR INLETWT aOW AT ROTOR OUTLETWT aOW AT STATOR OUTLETROTATIVE SPEEDPERCENT OF DESIGN SPEED
Reading number
982
1.3151.2841.0991.0980.8200.7540.8260.1610.1460.426
140.92188.9128.1128.1328.8028.93
14519.990.2
983
1.4801.4511.1401.1370.8460.8170.8620.2350.2230.376
127.22170.5525.3725.4126.2625.89
14471.189.9
984
1.4231.4011.1241.1210.8580.8350.8700.2090.2000.410
136.57183.0827.2427.2528.0227.66
14505.090.1
985
1.4881.4521.1481 .1460.8120.7690.8260.2390.2230.343
118.02158.2123.5423.5224.5124.35
U461.789.8
986
1.4931.4391.1571.1560.7710.7000.774.0.2410.2170.309
107.93144.6921.5321.5322.5223.07
14480.589.9
(c) 80 Percent of design speed
Parameter Readingnumber
987
ROTOR TOTAL PRESSURE RATIOSTAGE TOTAL PRESSURE RATIOROTOR TOTAL TEMPERATURE RATIOSTAGE TOTAL TEMPERATURE RATIOROTOR TEMP. RISE EFFICIENCYSTAGE TEMP. RISE EFFICIENCYROTOR MOMENTUM RISE EFFICIENCYROTOR HEAD RISE COEFFICIENTSTAGE HEAD RISE COEFFICIENTFLOW COEFFICIENTWT aOW PER UNIT FRONTAL AREAWT aOW PER UNIT ANNULUS AREAWT aOH AT ORIFICEHT FLOW AT ROTOR INLETWT aOW AT ROTOR OUTLETWT aOW AT STATOR OUTLETROTATIVE SPEEDPERCENT OF DESIGN SPEED
1.3751.3391.1231.1230.7730.7090.7780.2380.2170.30295.70128.2919.0919.0719.8820.22
12900.580.1
23
TABLE VI. - Concluded. OVERALL PERFORMANCE FOR STAGE 11-4
(d) 70 Percent of design speed
Parameter
ROTOR TOTAL PRESSURE RATIOSTAGE TOTAL PRESSURE RATIOROTOR TOTAL TEMPERATURE RATIOSTAGE TOTAL TEMPERATURE RATIOROTOR TEMP. RISE EFFICIENCYSTAGE TEMP. RISE EFFICIENCYROTOR MOMENTUM RISE EFFICIENCYROTOR HEAD RISE COEFFICIENTSTAGE HEAD RISE COEFFICIENTaOW COEFFICIENTWT FLOW PER UNIT FRONTAL AREAWT aOW PER UNIT ANNULUS AREAHT FLOW AT ORIFICEWT FLOW AT ROTOR INLETWT FLOW AT ROTOR OUTLETWT FLOW AT STATOR OUTLETROTATIVE SPEEDPERCENT OF DESIGN SPEED
Reading number
988
1.1661.1541.0521.0520.8580.8000.889O.U50.1350.430
115.99155.4923. U23.1723.5823.45
11331.470.4
989
1.2161.2041.0661.0660.8680.8310.8970.1860.1760.399
108.90145.9921.7221.7422.3921.98
11338.270.4
990
1,2471.2351.0771.0750.8490.8270.8680.2090.2000.368
101.80136.4720.3020.3220.9020.55
11368.570.6
991
1.2661 .2501.0851.0840.8160.7820.8«0.2250.2130.33493.09
124.7918.5718.5619.3618.94
11353.170.5
992
1.2771.2551.0931.0920.7750.7250.7870.2340.2160.30184.80
113.6816.9116.9017.4217.68
11348.370.5
(e) 60 Percent of design speed (f) 50 Percent of design speed
Parameter
ROTOR TOTAL PRESSURE RATIOSTAGE TOTAL PRESSURE RATIOROTOR TOTAL TEMPERATURE RATIOSTAGE TOTAL TEMPERATURE RATIOROTOR TEMP. RISE EFFICIENCYSTAGE TEMP. RISE EFFICIENCYROTOR MOMENTUM RISE EFFICIENCYROTOR HEAD RISE COEFFICIENTSTAGE HEAD RISE COEFFICIENTaOW COEFFICIENTWT FLOW PER UNIT FRONTAL AREAHT FLOW PER UNIT ANNULUS AREAHT FLOW AT ORIFICEHT FLOW AT ROTOR INLETHT FLOW AT ROTOR OUTLETHT aOH AT STATOR OUTLETROTATIVE SPEEDPERCENT OF DESIGN SPEED
Readingnumber
993
1.1961.1801.0681.0670.7780.7260.7960.2360.2170.29370.6894.7514.1014.0914.6214.68
9630.359.8
Parameter
ROTOR TOTAL PRESSURE RATIOSTAGE TOTAL PRESSURE RATIOROTOR TOTAL TEMPERATURE RATIOSTAGE TOTAL TEMPERATURE RATIOROTOR TEMP. RISE EFFICIENCYSTAGE TEMP. RISE EFFICIENCYROTOR MOMENTUM RISE EFFICIENCYROTOR HEAD RISE COEFFICIENTSTAGE HEAD RISE COEFFICIENTaOW COEFFICIENTHT aOW PER UNIT FRONTAL AREAWT aOH PER UNIT ANNULUS AREAHT aOH AT ORIFICEWT aOH AT ROTOR INLETHT aOH AT ROTOR OUTLETHT aOH AT STATOR OUTLETROTATIVE SPEEDPERCENT OF DESIGN SPEED
Readingnumber
994
1.1351.1241.0471.0460.7780.7320.8000.2360.2170.28558.0477.8111.5811.5712.0912.05
8050.850.0
24
TABLE VII. - BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(a) 100 Percent of design speed; reading number 968
RADIIRP
123456789
1011
IN24.52824.06121.74019.95919.66019.35519.05318.74816.87114.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABS VELRP
123t56789
10!1
IN189.1194.4201.5208.2206.9207.1207.3207.0207.2201.8199.0
OUT210.2211.2212.7219.0210.0200.4196.0200.7232. S254.3262.1
ABS MACH NORP
123456789
1011
IN0.5730,5900.6140.6300.631
. 0.6330.6340.6330.6330.6150.606
OUT0.5910.5970.6060.6240.5960.5700.5570.5710.6700.7360.759
ABSIN
-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0
RELIN
455.4448.8417.6393.5390.3385.8382.0377.0350.6312.3301.5
BET AMOUT34.4
32.932.838.538.838.4
38.939.037.340.542.8
VELOUT
337.6335.3305.7263.0258.7256.5251.6247.1237.5213.0203.7
REL MACH NOIN.380.363.273.202.191.179.167.152.071
0.9520.918
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN2.2.3.4.4.4.4.4.5.5.6.
23834578292
SS-0.6-0.8-0.4-0.7-0.7-0.7-0.7-0.7-1.1-1.4-1.3
OUT0.9490.9470.8710.7490.7350.7290.7150.7030.6840.6170.590
DEV
1.71.31.00.52.95.36.86.02.14.44.6
REL BETAMIN
65.564.361.158.4
58.057.557.156.7
53.849.848.7
MERIDIN
189.1194.4201.5206.2206.9207.1207.3207.0207.2201.8199.0
OUT59.158.154.249.350.852.252.7
50.838.924.819.3
VELOUT
173.5177.4178.7171.5163.7157.1152.6156.0184.9193.3192.2
TOTAL TEMPIN
288.7288.6288.1287.9288.4288.0287.8287.8288.0288.0288.0
RATIO.168.158.143.149.146.139.136.137.136.142.150
TANG VELIN
-0.1-0.1-0.1-0.1-0.1-0.0-0.1-0.1-0.0-0.1-0.0
OUT118.7114.6115.3136.2131.6124.4123.0126.3141.1165.2178.2
MERID MACH. NOIN
0.5730.5900.6140.6300.6310.6330.6340.6330.6330.6150.606
D-FACT
0.3560.3470.3600.4390.4400.4320.4370.4430.4300.4400.454
OUT0.4880.5010.5090.4880.4650.4460.4340.4440.5320.5600.556
EFT
0.7520.7900.8430.7790.7290.7160.7060.7260.8840.9000.879
LOSS COEFFTOT0.1730.1410.1070.1640.2000.2030.2090.1990.0950.1020.135
PROF0.0890.0630.0430.1140.1510.1560.1630.1560.0650.0850.124
TOTALIN
10.0810.1210.1310.1410.1410.1410.1410.1410.1410.1510.13
WHEELIN
414.2404.5365.7335.0330.9325.5320.8315.0282.7238.3226,4
MERIDVEL R0.9170.9130.8870.8320.7910.7590.7360.7530.8920.9580.966
PRESSRATIO
.516
.509
.489
.469
.426
.394
.3791.3931.4881.5251.543
SPEEDOUT
408.4399.1363.3335.6332.0327.2323.0317.9290.1254.5245.6
PEAK SSMACH UQ
1.5321.5191.5091.4911.4921.4901.4901.4881.4691.450t.417
LOSS PARAMTOT0.0330.0280.0210.0330.0380.0370.0370.0370.0200.0210.027
PROF0.0170.0120.0080.0230.0290.0290.0290.0290.0130.0170.025
25
TABLE VH. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(b) 100 Percent of design speed; reading number 969
RADIIRP
123456789
1011
IN24.62824.06121.74019.95919.66019.35519.05318.74816.871U.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABS VELRP
1234561*
89
1011
IN184.4189.5197.6201.9201.5202.0201.8202.4201.7194.9192.0
OUT221.2217.4213.3224.4219.8215.0209.4208.1229.3244.9256.4
ABS MACH NORP
123456789
1011
IN0.5580.5740.6010.6160.6140.6160.6150.6170.6150.5930.583
OUT0.6110.6060.6010.6330.6200.6070.5910.5870.6540.7040.737
ABSIN
-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0
RELIN
454.0448.6417.1393.4388.3384.3379.9375.9349.0309.0297.7
BET AMOUT41.840.339.442.442.843.344.144.542.544.846.7
VElOUT
309.0309. 0282.5249.9244.4239.4233.4228.5218.0192.8185.8
REL MACH NOIN
1.3741.3601.2691.1991.1841.1711.1581.1461.0640.9400.904
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10 .0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN2.3.4.5.5.5.5.5.6.7.7.
7o'302345103
SS-0.0-0.1
0.20.10.10 .00.10.0
-0.2-0.3-0.2
OUT0.8540.8610.7950.7050.6900.6750.6580.6450.6220.5540.534
DEV
0.40.81.1
-0.40.82.34.04.72.35.24.2
REL BET AMIN
66.065.061.759.158.758.357.957.454.750.949.8
KERIDIN
184.4189.5197.6201.9201.5202.0201.8202.4201.7194.9192.0
OUT57.857.554.348.448.749.249.849.539.125.718.9
VELOUT
164.8165.8164.8165.8161.3156.5150.5148.4169.2173.8175.9
TOTAL TEMPIN R A T I O
288.6288.6288.1288.1287.9288.1287.9287.9287.9287.9288.0
TANGIN
-0.1-0.0-0.-0.-0.-0.-0.0-0.-0.-0.1-0.1
1.2131.191
.169
.171
.169
.165
.162
.160
.153
.151
.159
VELOUT
147.5140.5135.4151.2149.3147.4145.7145.8154.8172.6186.6
MERID MACH NOIN
0.5580.5740.6010.6160.6140.6160.6150.6170.6150.5930.583
D-FACT
0.4410.4260.4310.4840.4880.4930.4990.5060.4940.5040.514
OUT0,4550.4620.4640.4680.4550.4420.4250.4190.4830.4990.506
Err0.7440.8070.8540.8420.8180.8090.7900.7890.8920.9110.901
LOSS COEFFTOT0.2160.153O . M 40.1340.1540.1610.1760.1770.0990.0960.120
PROr0.1300.0710.0480.0800.1030 . 1 1 10.1280.1310.0640.0790 .109
TOTALIN
10.0810.1210.1310.1410.1410.1410.1410.1410.1410.-1410.13
WHEELIN
414.8406.6367.2337.5331.9326.8321.8316.7284.8239.7227.4
MERIDVEL R0.8940.8750,8340,8210,8000,7750.7460.7330.8390.8920.916
PRESSRATIO1.6731.6521.6011.6021.5741.5501.5251.5151.5651.5701.599
SPEEDOUT
408.9401.2364.9338.1333.0328.5324.1319.6292.3256.0246.7
PEAK SSMACH NO
1,5451,5401,5261.5141.5111.5101.5101,5091.4971.4671.430
LOSS PARAMTOT0.0430.0300.0220.0270 .0310.0320.0340.0340.0200.0190.024
PROF0.0260.0140.0090.0160.0210.0220.0240.0250.0130.0160.022
26
TABLE VII. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(c) 100 Percent of design speed; reading number 970
RADIIRP
123456789
1011
IN24.62824.06121.74019.95919.66019.35519.05318.74816.87114.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABS VELRP
123l56789
1011
IN172.1176.7184.9188.5188.6188.8188.4188.6188.5181.5178.5
OUT227.1221.2213.3220.1217.5213.2209.5209.9226.6236.4250.3
ABS MACH NORP
123456789
1011
IN0.5190.5340.5600.5720.5720.5730.5720.5720.5720.5500.540
OUT0.6200.6100.5960.6180.6100.5980.5880.5890.6430.6750.716
ABSIN
-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0
RaIN
449.6442.6410.8385.7381.6377.2372.3367.8341.5300.4289.1
BET AMOUT47.644.543.745.745.946.848.448.646.047.749.1
vaOUT
286.2291.6266.3236.4232.8226.2217.0212.7203.6178.6173.7
REL MACH NOIN.355.336.245.170.158.145.130
1.1161.0360.9100.874
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN4.24.45.96.66.87.07.17.27.99.09.3
SS.4.4.7.7.7.7.8.7.6.7.8
OUT0.78!0.8050.7440.6640.6530.6350.6090.5970.5770.5100.497
DEV
0.30.51.40.61.52.94.34.42.66.54.6
REL BETAMIN
67.566.563.360.760.460.059.659.256.552.851.9
MERIDIN
172.1176.7184.9188.5188.6188.8188.4188.6188.5181.5178.5
OUT57.657.354.649.449.449.850.249.339.426.919.3
vaOUT
153.2157.'7154.2153.9151.4146.0139. Q138.8157.4159.3163.9
TOTALIN
288.7288.6288.0288.1288.0287.9287.8288.1288.0287.9288.0
TEMPRATIO1.2461.2171.1861.1801.1781.1761.1751.1741.1631.1581.164
TANG VaIN
-0.1-0.1-0.1-0.1-0.1-0.1-0.1-0.1-0.1-0.1-0.1
OUT167.7155.2147.3157.4156.1155.4156.8157.5163.0174.8189.1
MERID MACH NOIN
0.5190.5340.5600.5720.5720.5730.5720.5720.5720.5500.540
D-FACT
0.5030.4700.4720.5130.5150.5240.5420.5470.5310.5390.543
OUT0.4180.4350.4310.4320.4250.4100.3900.3900.4460.4550.469
EFF
0.7120.7800.8400.8500.8380.8210.7990.8010.8880.8990.909
LOSS COEFFTOT0.2720.1950.1380.1370.1480.1640.1850.1850.1120.1190.119
PROF0.1820.1110.0700.0810.0940.1110.1350.1370.0730.1030.109
TOTALIN
10.0810.1210.1310.1410.1410.1410.1510.1410.1410.1510.13
WHEELIN
415.4405.8366.7336.4331.8326.5321.1515.7284.7239.3227.3
MERIDVEL R0.8900.8920.8340.8160.8030.7730.7380.7360.8350.8770.918
PRESSRATIO1.758
.729
.660
.645
.628
.605
.583
.577
.606
.590
.626
SPEEDOUT
409.5400.4364.4337.0332.8328.2323.4318.6292.1255.6246.5
PEAK ssMACH NO
1.5771.5661.5561.5451.547
.5461.5461.5451.5441.4801.442
LOSS PAlttMTOT0.0550.0390.0270.0270.0290 . 0320.0350.0350.0230.0240.024
PROF0.0370.0220.0140.0160.0190.0220.0260.0260.0150.0200.022
27
TABLE VH. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(d) 100 Percent of design speed; reading number 975
RADIIRP
123456789
1011
IN24.6282^.06121.74019.95919.66019.35519.05318.74816.87114.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
A8S YELRP
123456
^89
•a'*
IN157.1161.2170.3174.7174.4174.4174.5174.5174.1168. a162.6
OUT222.5225.9214.7217.4216.5212.2210.9210.9222.2234.6246.9
A8S MACH NORP
123456789
1011
IN0.4710.4840.5140.5280.5270.5270.5270.5270.5260.5060.489
OUT0.6040.6190.5970.6080.6060.5940.5900.5900.6280.6690.706
ABSIN
-0.0- .1- .1- .0- .0- .0- .0- .0- .0- .0-0.9
RELIN
443.6438.6406.5381.5376.8371.8367.5363.1335.5294.0281.0
BET AMOUT50.548.645.547.047.248.951.051.347.048.248.9
VELOUT
276.1274.3258.8231.3227.3217.8206.7202.4198.7175.6173.1
REL MACH NOIN.331.317.226.152.138.123.110.097.013
0.8860.845
PERCENT INCIDENCERP
123A56789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN6.6.7.8.8.9.9.9.
10.11.12.
04969023231
SS3.23.43.73.73.83.83.83.83.94.04.6
OUT0.7490.7520.7200.6470.6370.6090.5780.5660.5620.5010.495
DEV
1.80.31.31.41.83.24.24.53.56.65.5
REL BETAMIN
69.368.4
65.262.862.4
62.061.7
61.358.7
55.254.6
MERIDIN
157.1161.1170.3174.6174.3174.4174.5174.5174.1167.9162.6
OUT59.257.054.4
50.249.650.150.149.340.327.120.2
VELOUT
141.4149.5150.5148.2147.2139.6132.7131.9151.5156.4162.4
TOTAL TEMPIN
288.8288.8288.1287.9287.8287.8287.8287.9287.9287.9288.0
RATIO1.2561.2341.1961.1861.184
.182
.181
.182
.166
.1591.162
TANG VELIN
-0.1-3.1-3.2-3.2-3.2-3.2-3.2-3.2-3.1-2.8-2.6
OUT171.8169.4153.1159.0158.7159.8164.0164.6162.5174.9185.9
MERID MACH NOIN
0.4710.4840.5130.5280.5270.5270.5270.5270.5260.5060.489
D-FACT
0.5230.5190.4920.5250.5280.5460.5730.5780.5390.5410.531
OUT0.3840.4100.4190.4150.4120.3910.3710.3690.4280.4460.465
EFF
0.6900.7630.8270.8410.8360.8190.8030.7920.8770.9080.935
LOSS COEFFTOT0.3050.2260.1580.15.00.1570.1740.1910.2050.1280.1130.088
PROF0.2110.1330.0810.0860.0940.1140.1330.1470.0800.0960.078
TOTALIN
10.0710.1110.1410.1510..1510.1510.1510.1510.1510.1510.09
WHEELIN
414.8404.8366.0336.0330.9325.2320.2315.2283.7238.5226.5
MERIDVEL R0.9000.9280.8840.8490.8440.8010.7600.7560.8700.9310.999
PRESSRATIO
.768
.778
.692
.662
.649
.625
.609
.602
.611
.602
.637
SPEEDOUT
408.9399.5363.6336.6331.9326.9322.5318.1291.1254.8245.6
PEAK ssMACH NO
.614
.615
.606
.559
.601
.600
.601
.604
.612
.512
.474
LOSS PARAMTOT0.0590.0450.0310.0300.0310.0330.0360.0390.0260.0220.018
PROF0.0410.0270.0160.0170.0190.0220.0250.0280.0160.0190.015
28
TABLE VH. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(e) 100 Percent of design speed; reading number 978
RADIIRP
123A56789
1011
IN24.62824.06121.7*019.95919.66019.35519.05318.74816.87114.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABS VELRP
123456789
101!
IN155.5158.9167.2170.8171.0171.3171.1170.6170.3165.3162.9
OUT223.0226.3213.9215.0215.7212.1211.5213.4220.8235.9247.0
ABS MACH NORP
123A56789
1011
IN0.4660.4770.5040.5150.5160.5170.5160.5150.5140.4980.490
OUT0.6050.6200.5950.6010.6040.5930.5910.5970.6240.6730.706
ABSIN
-1.1-1.1-1.1-t.t- .0- .1- .0- .0- .0- .0-0.9
RELIN
445.0437.5404.5379.0374.8370.3365.6360.6333.0292.6281.3
BET AMOUT50.7
48.645.547.347.848.851.652.547.848.249.1
VELOUT
274.8274.1258.5229.9224.8217.9204.5197.2195.1175.9172.2
REl MACH NOIN.334,313.219.144
,131.117.103,088.004
0.8820.847
PERCENT INCIDENCERPI23456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN6.6.8.9.9.9.9.9.
10.11.12.
37213468770
SS3.53.64.14.14.24.24.34.34.44.54.6
OUT0.7450.7510.7190.6430.6300.6090.5720,5510.5510.5010.492
DEV
1.7O.I1.41.92.03.24.13.93.86.35.4
REL BETAMIN
69.668.7
65.663.262.962.462.161.859.355.654.6
MERIDIN
155.5158.9167.1170.8170.9171.3171.1170.5170.2165.3162.9
OUT59.156.954.550.649.950.150.048.740.626.720.1
VELOUT
141.3149.8150.0145.8144.9139.6131.5130.1148.2157.1161.7
TOTAL TEMPIN
288.8288.9288.1287.9287.8287.9287.9288.0287.9287.9287.9
RATIO.257.237.196.164.183.182.183.184.168.160.163
TANG VELIN
-3.0-3.0-3.1-3.1-3.1-3.2-3.1-3.1-3.0-2.8-2.7
OUT172.5169.6152.4158.0159.7159.6165.7169.2163.7176.0186.6
HER ID MACH NOIN
0.4660.4770.5040.5150.5160.5170.5160.5140.5140.4980.490
D-FACT
0.5300.5180.4890.5250.5330.5440.5780.5930.5470.5390.535
OUT0.3830.4100.4170.4080.4060.3910.3680.3640.4190.4480.462
EFF
0.6690.7590.82*0.8370.8380.8170.7960.7910.8600.9100.918
LOSS COEFFTOT0.3060.2310.1620.1550.1550.1770.2010.2100.1480.1120.111
PROF0.2080.1380.0850.0900.0910.1160.1410.1520.0980.0940 .100
TOTALIN
10.0910.1010.14U.U10.1410.1410.1410.1510.1510.1410.13
WHEELIN
414.0404.6365.3335.2330.5325.1320.0314.6283.1238.7226.6
MERIDVEL R0,9090.9430.8970,8530.8480.8150.7690.7630.8710.9510.993
PRESSRATIO
.770
.783
.687
.651
.647
.626
.611
.6081.6041.6091.629
SPEEDOUT
408.1399.2362.9335.8331.6326.8322.3317.5290.5255.0245.8
PEAK SSMACH NO
1,6271.6201.612.608.610.610.612.615.628.517.475
LOSS PARAMTOT0.0590.0470.0310.0300.0300.0340.0380.0400.0300.0220.022
PROF0.0400.0280.0170.0180.0180.0220.0270.0290.0200.0190.020
29
TABLE VH. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(f) 90 Percent of design speed; reading number 982
RADIIRP
123&56789
1011
IN24.62824.06121.74019.95919.66019.35519.05318.74816.87114.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABS VELRP
1234567
89
1011
IN1G9.8174.8183.2187.1187.7187.7187.4187.8188.0183.3180.6
OUT186.6188.1194.4204.3204.2197.9190.0188.8219.4239.8245.2
ABS MACH NORP
123456789
10U
IN0.5110.5270.5550.5680.5690.5700.5680.5700.5700.5550.547
OUT0.5360.5430.5640.5920.5920.5730.5500.5460.6400.7020.717
ABSIN
-0.00.0
-0.0-0.0-0.0
0.0-0.0-0.0
0.0.0
-0.0
RELIN
411.9406.1378.6355. 6353.5349.3344.6341.1317.6282.9272.9
BET AMOUT23.923.224.528.028.429.330.130.929.935.037.1
VELOUT
340.2335.6305.1275.4271.4263.7255.8250.0244.3217.1209.2
REL MACH NOIN.240.225.146.082.072.060
U0451.0350.9640.8570.826
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN2.2.3.4.4.4.4.4.5.5.6.
35724567170
SS-0.4-0.6-0.5-0.7-0.7-0.8-0.8-0.8-1.2-1.5-1.5
OUT0.9780.9690.8850.7980.7870.7640.7400.7230.7130.6350.612
DEV
2.62.31.40.30.72.24.14.82.14.86.0
REL BETAMIN
65.664.561.158.457.957.557.156.653.749.648.6
MERIDIN
169.8174.8183.2187.1187.7187.7187.4187.8188.0183.3180.6
OUT59.959.054.649.148.549.150.049.638.925.220.8
VELOUT
170.6172.9176.9180.3179.7172.6164.4162.1190.2196.4195.7
TOTAL TEMPIN RATIO
288.8288.7288.2288.0288.1287.9287.9287.8288.0287.8287.9
TANGIN
-0.00.0
-0.0-0.0-0.0
0 . 0-0.0-0.0
0.0.0
-0.0
1.1031.0961.0911 . 1 0 01 .1011.0981.0951.0961.0991.1101.115
VELOUT75.674.280.696.097.096.795.396.9
109.4137.7147.8
MERID MACH NOIN
0.5110.5270.5550.5680.5690.5700.5680.5700.5700.5550.547
D-rACT
0.2430.2410.2650.3110.3160.3280.3400.3500.3330.3440.352
OUT0.4900.4990.5130.5230.5210.5000.4160.4690.5550.5750.572
EfF
0.7100.7550.8270.7980.7860.7520.7130.6990.9090.9120.908
LOSS coErrTOT0.1480.1190.0890.1210.1300.1500.1710.1820.0640.0820.094
PROP0.1070.0820.0600.0980.1080.1290.1510.1620.0530.0810.094
TOTALIN
10.0710.1110.1410.1410. .1410.1510.1510.1410.1410.1410.13
WHEELIN
375.2366.6331.3303.6299.5294.5289.2284.7256.0215.5204.7
MERIDVEL R1.0040.9890.9660.9640.9570.9200.8770.8631.0121.0711.084
PRESSRATIO1.2801.2771.2901.3091.3071.2841.2581.2551.3511.3961.415
SPEEDOUT
369.9361.8329.2304.1300.5296.1291.2287.4262.7230.1222.0
PEAK SSMACH NO
.407
.397
.399
.400
.404
.4061.4071.4111.3871.3011.271
LOSS PARAMTOT0.0280.0230.0170.0240.0260.0290.0320.0340.0130.0170.019
PROF0.0200.0160.0120.0200.0220.0250.0290.0310.0110.0160.019
30
TABLE Vn. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(g) 90 Percent of design speed; reading number 983
RADIIRP
123&56789
1011
IN24.62824.06121.74019.95919.66019.35519.05318.74816.87114.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABS VELRP
123456789
1011
IN163.1167.9176.2179.6179.6179.9179.7179.5178.9173.2170.5
OUT192.1192.3191.4200.6201.2199.3198.1194.7209.1228.7237.9
ABS MACH NORP
123456789
1011
IN0.4900.5050.5320.5430.5430.5450.5440.5430.5410.5230.515
OUT0.5420.5460.5480.5750.5770.5710.5680.5580.6030.6630.691
ABSIN0.0
-0.0-0.0
0.0-0.0
0.0-0.0-0.0-0.0
0.00.0
RELIN
408.2402.0374.6352.3348.6344.9340.8336.6312.5276.6266.4
BET AMOUT34.334.532.235.4
35.935.937.1
38.336.540.341.9
VELOUT
305.2297.4278.2248.8244.1241.0233.8226.0218.0193.1188.1
REL MACH NOIN
1.2261.2101.1321.0661.0541.0441.0311.0190.9450.8350.804
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN3.13.34.55.25.45.55.75.86.57.47.6
SS0.40.20.40.30.30.30.30.30.20.10.2
OUT0.8610.8440.7960.7130.7000.6910.6700.6470.6290.5600.546
DEV
1.31.11.20.10.21.01.52.62.74.94.9
REL BETAMIN
66.4
65.361.959.359.058.558.257.855.151.250.2
MERIDIN
163.1167.9176.2179.6179.6179.9179.7179.5178.9173.2170.5
OUT58.7
57.854.4
48.948.147.947.447.539.525.319.6
VELOUT
158.7158.5161.9163.6163.0161.4158.-1152.8168.2174.5177.2
TOTAL TEMPIN RATIO
288.9288.9288.1288.0288.0287.9287.9287.8287.9287.8287.8
TANGIN0.0
-0.0-0.0
0.0-0.0
0.0-0.0-0.0-0.0
0.00.0
1.147.133.119.122.122.121.121.119.114.120.124
VELOUT
108.2108.8102.1116.1118.0116.8119.4120.8124.3147.7158.8
MERID MACH NOIN
0.4900.5050.5320.5430.5430.5450.5440.5430.5410.5230.515
D-FACT
0.3520.3590.3480.3960.4030.4030.4180.4340.4090.4250.425
OUT0.4480.4500.4630.4690.4670.4630.4530.4380.4850.5060.514
Err
0.7500.8120.8730.8660.8590.8440.8330.8150.9150.9160.926
LOSS COEFFTOT0.1760.1250.0840.0980.1040.1160.1260.1410.0700.0880.085
PROF0.1340.0870.0540.0730.0810.0930.1040.1190.0590.0870.085-
TOTALIN
10.0710.11tO. 1410.1510.1510.1510.1410.1410.15•10.1410.13
WHEELIN
374.2365.2330.5303.1298.7294.2289.5284.7256.2215.7204.7
MERIDVCL R0.9730.9440.9190.9110.9080.8970.8800.8510.9401 . 0'081.039
PRESSRATIO1.4421.4331.4141.4211.4181.4071.4001.38*1.4141.4411.462
SPEEDOUT
368.9360.4
-328.4303.6299.7295.8291.6287.3262.9230.4222.0
PEA< SSMACH HO
1.4221.4111.4181.4251.4311.4341.4391.4461.4051.3141.281
LOSS PARAMTOT0.0350.0250.0160.0200.0210.0230.0250.0280.0140.0180.017
PROF0.0260.0170.0110.0150.0160.0190.0210.0230.0120.0180.017
31
TABLE VH. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(h) 90 Percent of design speed; reading number 984
RADIIRP
123A56789
1011
IN24.62824.06121.74019.95919.66019.35519.05318.74816.87114.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABS VELRP
123t56/
8S
13M
RPt23t56/
89
1011
IN148.7153.3161.5163.7164.0164.0163.5163.4162.2156.4153.8
ABSIN
0.4450.4590.4860.4930.4940.4940.4920.4920.4880.4700.462
OUT196.1197.8190.3197.1196.5194.9193.4191.0198.6222.1230.1
MACH NOOUT
0.5460.5550.5400.5610.5590.5550.5500.5430.5680.6400.664
ABSIN0.00.00.00.00.00.0
-0.0-0.0
0.00.0
-0.0
RELIN
401.9395.6367.3343.8340.2336.0331.5327.6302.6266.0256.1
BET AMOUT41.741.138.440.240.741.643.244.743.244.745.9
VELOUT
279.0273.9257.2231.2226.6220.3211.7204.0192.0174.2170.0
REU MACH NOIN
1.2021.1851.1051.0351.0241.0120.9980.9870.9110.7990.769
PERCENT INCIDENCERP
123i567
89
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN5. 05.26.57.7.7.8.8.9.
10.10.
56701015
SS2.22.12.42.52.52.52.62.72.72.83.0
OUT0.7770.7690.7290.6580.6450.6270.6020.5800.5490.5020.491
DEV
1.00.31.40.61.11.72.43.44.34.64.8
REL BETAMIN
68.367.263.961.661.260.860.460.157.654.053.1
MERIDIN
148.7153.3161.5163.7164.0164,0163.5163.4162.2156.4153.8
OUT58.457.054.649.448.948.648.348.341.125.019,5
VELOUT
146.4149.0149.2150.5148.9145.7141.0135.8144.7157.9160.2
TOTAL TEMPIN
289.4289.2287.9287.8287.8287.8287.7287.7287.8287.8287.8
RATIO.175.160.138.135.134.133.134.133.125.127
1.129
TANG VELIN0.00.00.00.00.00.0
-0.0-0.0
0.00 .0
-0.0
OUT130.5130.1118.2127.3128.2129.5132.4134.3136.0156.2165.2
MERID MACH NOIN
0.4450.4590.4860.4930.4940.4940.4920.4920.4880.4700.462
D-FACT
0.4270.4280.4070.4420.4490.4600.4800.4970.4860.4800.478
OUT0.4080.4180.4230.4280.4240.4150.4010.3860.4140.4550.463
EFF
0.7400.8130.8620.8730.8670.8540.8300.8120.8670.9190.926
LOSS COEFFTOT0.2160.1480.1060.1050 .1110.1230.1460.1640.1250.0960.094
PROF0.1700.1060.0720.0760.0820.0950.1180.1380.1140.0950.094
TOTALIN
10.0710.1110.1410.1410.1510.1410.1410.1510.1510.1410.13
WHEELIN
373.3364.7329.9302.4298.0293.2288.3284.0255.4215.2204.7
MERIDVEL R0.9840.9720.9240.9190.9080.8880.8620.8310.8921.0091.042
PRESSRATIO
.533
.533
.481
.477
.469
.459
.447
.434
.434
.473
.485
SPEEDOUT
368.1359.9327.8302.9299.0294.7290.4286.6262.1229.9222.0
PEAK SSMACH NC
1,4641.4561,4671,4871.4921.4981.5061.5001.4311.3321.300
LOSS PARAMTOT '0.0430.0300.0210.0210.0220.0240.0290.0320.0250.0190.019
PROF0.0340.0210.0140.0150.0160.0190.0230.0270.0230.0190.019
32
TABLE Vn. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(i) 90 Percent of design speed; reading number 985
RADIIRP
123456789
1011
IN2^.62824.06121.74019.95919.66019.35519.05318.74816.87114.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABS VELRP
123I56789
1011
IN134.0139.1146.4148.2148.2148.1148.1147.4147.3143.6141.5
OUT197.2198.1187.6191.7191.8189.9189.2189.0198.9219.8226.4
ABS MACH NORP
123456789
1011
IN0.3990.4150.4390.4440.4450.4440.4440.4420.4410.4300.424
OUT0.5470.5550.5300.5420.5430.5370.5350.5340.5670.6330.653
ABSIN
-0.0-0.0-0.0
0.0-0.00.0
-0.0-0.0
0.0-0.0-0.0
RELIN
396.4390.3360.4336.9332.9328.5324.3319.5294.7258.4248.5
BET AMOUT45.443.342.145.946.949.050.852.446.945.246.6
VELOUT
266.3266.3244.8212.3206.1195.9187.2178.6179.2171.3165.8
REL MACH NOIN
1.1791.1641.0801.0100.9980.9850.9720.9580.8840.7740.744
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN7.07.18.69.8
10.010.210.410.611.512.412.7
SS4.24.04.54.84.95.05.05.15.25.15.2
OUT0.7380.7440.6910.6010.5830.5540.5290.5050.5110.4930.478
DEV
1.30.52.22.32.63.64.44.93.95.05.4
RQ_ BETAMIN
70.269.166.063.963.663.262.862.560.156.255.3
MERIDIN
134.0139.1146.4148.2148.2148.1148.1147.4147.0143.6141.5
OUT58.657.255.4
51.150.550.550.349.840.725.4
20.1
VELOUT
138.6144.2139.2133.3131.1124.5119.6115.4135.9154.8155.6
TOTAL TEMPIN
290.1289.6287.9287.7287.6287.4287.8287.5287.6287.6287.7
RATIO1.1841.1691.1451.145
.145
.145
.146
.146
.134
.129
.130
TANG VELIN
-0.0-0.0-0.0
0.0-0.00.0
-0.0-0.0
0.0-0.0-0.0
OUT140.4135.9125.8137.8140.1143.4146.7149.7145.2156.1164.4
MERID MACH NOIN
0.3990.4150.4390.4440.4450.4440.4440.4420.4410.4300.424
D-FACT
0.4610.4450.4370.4960.5090.5350.5570.5780.5230.4760.478
OUT0.3840.4030.3930.3770.3710.3520.3380.3260.3870.4450.449
EFF
0.7300.7920.8210.8040.7940.7760.7570.7440.8270.9260.922
LOSS COEFFTOT0.2380.1750.1480.1760.1880.2080.2300.2470.1790.0920.105
PROF0.1860.1280.1080.1380.1510.1740.1990.2190.1670.0910.105
TOTALIN
10.0710.1110.1410.1410.1510.1510.1410.1410.1410.1510.13
WHEELIN
373.0364.6329.3302.5298.1293.2288.6283.4255.4214.9204.3
MERIDVEL R1.0341.0360.9500.9000.8840.8410.8080.7830.9241.0781 . 1 0 0
PRESSRATIO
.555
.552
.484
.469
.464
.452
.4421.4341.4461.4831.485
SPEEDOUT
367.8359.8327.2303.0299.0294.7290.6286.0262.1229.5221.5
PEAK SSMACH NC
1.5131.5041,523.557.565
1.5551.5451.5361.4631.3491.314
LOSS PARAMTOT0.0470.0350.0280.0340.0360.0400.0430.0470.0360.0180.021
PROF0.0370.0250.0200.0270.0290.0330.0380.0410.0330.0180.021
33
TABLE VH. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(j) 90 Percent of design speed; reading number 986
RADIIRP
123I56789
1011
IN24.62824.06121.74019.95919.66019.35519.05318.74816.87114.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABS vaRP
123456789
1011
IN117.3122.6130.7132.0132.3132.3132.6132.8134.2133.2131.4
OUT196.8199.1189.5194.1193.7191.0188.8188.5200.7219.6227.2
ABS MACH NORP
123456789
1011
IN0.3470.3640.3900.3950.3950.3950.3960.3970.4010.3980.393
OUT0.5420.5520.5320.5460.5450.5380.5310.5310.5710.6320.655
ABSIN
-0.00.
-0.0-0.0-6.0-0.0
0.0-0.0
0.00.0
-0.0
RELIN
391.0385.0354.4329.7326.1321.9318.3314.0289.2253.0243.3
BET AMOUT52.849.649.052.653.254.455.656.647.945.646.8
VEUOUT
242.1245.2222.4189.7184.7178.7172.4166.3176.3170.2165.6
REL MACH NOIN
1.1571.1421.0580.9850.9740.9620.9510.9380.8650.7560.727
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN9.9.
11.12.12.12.12.13.
34035790
13.814.414.7
SS6.56.46.87.37.47.57.57.67.57.17.2
OUT0.6660.6800.6240.5340.5200.5030.4850.4680.5020.4900.477
DEV
3.21.52.82.83.34.65.96.53.55.05.2
REL BETAMIN
72.571.468.466.466.165.765.465.062.458.257.3
MERIDIN
117.3122.6130.7132.0132.3132.3132.6132.8134.2133.2131.4
OUT60.658.256.051.551.151.551.851.34(K325.420.0
VELOUT
118.9129.1124.4117.9116.0111.3106. 5103.9134.5153.7155.7
TOTAL TEMPIN
290.9290.1287.8287.4287.4287.5287.5287.4287.4287.4287.5
RATIO.196.185.161.158.158.156.155.154.139
1.1301.132
TANG VELIN
-0.00.
-0.0-0.0-0.0-0.0
0.0-0.0
0.00.0
-0.0
OUT156.9151.6143.0154.1155.2155.3155.8157.3149.0156.8165.6
MERID MACH NOIN
0.3470.3640.3900.3950.3950.3950.3960.3970.4010.3980.393
D-FACT
0.5310.5070.5070.5690.5790.5900.6040.6170.5280.4700.469
OUT0.3270.3580.3490.3320.3260.3130.3000.2920.3830.4420.449
EFF
0.6840.7260.7440.7390.7350.7240.7160.7110.8190.9350.929
LOSS COEFFTOT0.2950.2510.2330.2580.2660.2800.2890.2990.1990.0850.100
PROF0.2350.1940.1840.2130.2230.2410.2530.2650.1840.0840.100
TOTALIN
10.0610.1110.1410.1410.1510.1410.1510.1510.1410.1410.14
WHEELIN
373.0364.9329.4302.1298.0293.5289.4284.5255.2215.2204.8
MERIDVEL R1.0141.0530.9520.8930.8760.8410.8030.7821.0021.1551.184
PRESSRATIO1.5521.5541.4871.4731.468
.455
.444
.438
.460
.494
.498
SPEEDOUT
367.8360.1327.3302.6299.0295.0291.4287.1262.9229.8222.1
PEAK SSMACH NO
.574
.567
.590
.616
.609
.601
.593
.582
.4981.3701.334
LOSS PARAMTOT0.0550.0490.0440.0500.0510.0520.0530.0540.0400.0170.020
PROF0.0440.0380.0340.0410.0430.0450.0460.0480.0370.0170.020
34
TABLE VH. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(k) 80 Percent of design speed; reading number 987
RADIIRP
123456789
1011
IN24.62824.06121.74019.95919.66019.35519.05318.74816.87114.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABSIN0.0
-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0
ABS VEL RaRP
123456I
89
1011
RP123456789
1011
IN103.0107.5112.8114.5114.8115.2115.1115.2116.7115.91U.3
ABSIN
0.3040.3190.3350.3410.3410.3430.3420.3430.3470.3450.340
OUT174.5172.3169.3173.4173.8171.6170.1169.3180.6196.1203.2
MACH NOOUT
0.4860.4830.4800.4930.4940.4880.4840.4810.5180.5660.588
IN347.3342.4314.5292.7289.1285.9282.2278.6256.3224.2215.2
BET AMOUT56.550.049.048.949.050.552.353.747.045.146.3
VELOUT
205.5218.8198.1179.8176.8170.2162.6155.8160.0153.5149.3
REL MACH NOIN
1.0271.0150.9350.8710.8600.8510.8390.8290.7630.6670.640
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.00
MEAN9.59.7
11.612.13.13.13.13.14.15.
95.00 15.
90246303
SS6.76.67.57.98.08.08.18.18.07.77.9
OUT0.5730.6130.5610.5110.5030.4840.4620.4430.4580.4430.432
DEV
4.72.92.71.91.93.24.35.22.95.15.2
REL BET AMIN
72.871.769.067.066.666.265.965.662.958.957.9
MERIDIN
103.0107.5112.8114.5114.8115.2115.1115.2116.7115.9114.3
OUT62.059.655.950.749.850.150.250.039.725.519.9
VELOUT96.4
110.7111.1114.0114.1109.1104.1100.1123.2138.5140.4
TOTAL TEMPIN
289.8289.0287.9287.8287.9287.8287.9287.9287.7287.7287.8
RATIO1.159
.149
.127
.122
.121
.120
.119
.118
.110
.1041.105
TANG VELIN0.0
-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0
OUT145.5132.0127.7130.7131.2132.4134.6136.5132.1138.9147.0
MERID MACH NOIN
0.3040.3190.3350.3410.3410.3430.3420.3430.3470.3450.340
D-FACT
0.5650.5020.5060.5240.5270.5440.5650.5840.5130.4580.456
OUT0.2690.3100.3150.3240.3240.3100.2960.2850.3530.4000.406
EFF
0.6470.6810.7440.7710.7730.7610.7510.7430.8350.9380.927
LOSS COEFFTOT0.3210.2810.2240.2160.2180.2310.2440.2560.1780.0800.103
PROF0.2910.2520.2050.2070.2100.2240.2380.2510.1770.0800.103
TOTALIN
10.1010.1310.1310.1410.1410.1410.1410.1410.1410.1410.13
WHEELIN
331.7325.1293.6269.3265.4261.7257.7253.6228.2191.9182.3
MERIDVEL R0,9371,0300,9850,9950,9940,9480,9040.8691.0561.1951,229
PRESSRATIO1.4071.4011.3721.3681.3671.3581.3501.3431.3601.3831.382
SPEEDOUT
327.0320.8291.7269.8266.2263.1259.5255.9234.2205.0197.8
PEA< SSMACH NO
.502,504,487.445.437
1,4301.4221.4141.3371.2231.189
LOSS PARAMTOT0.0570.0520.0420.0420.0430.0440.0460.0480.0360.0160.021
PROF0.0510.0470.0390.0400.0410.0430.0450.0470.0360.0160.021
35
TABLE Vn. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(1) 70 Percent of design speed; reading number 988
RADI IRP
',234567
89
1011
IN24.6382*.06i21.74019.95919.66019.35519.05318.74816.87114.20113.492
CUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABS VELRP
123z561
89
1011
RPt234567e9
t o11
IN132.4137.3142.3144.8145.0144.8144.9144.8144.9141.7139.6
ABSIN
0.3950.4100.4260.4340.4340.4340.4340.4330.4340.4240.418
OUT146.2150.7152.2157.7158.9159.8159.7157.9174.4195.1200.0
MACH NOOUT
0.4270.4410.4460.4630.4660.4680.4670.4610.5120.5740.588
ABSIN
-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0
RELIN.
320.9316.7294.8277.7275.1271.4268.6265.2247.2220.2212.3
BET AMOUT19.818.517.219.420.822.124.726.825.631.533.6
VELOUT
275.5273.9256.6237.4231.8226.0216.8208.1204.3183.8178.1
REL MACH NOIN
0.9570.9460.8820.8310.8240.8130.8040.7940.7400.6590.635
PERCENT INCIDENCERP
123t56789
ID11
SPAN MEAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
2.2.3.4.4.4.4.5.5.6.6.
33756790513
SS,-0.4-0.8-0.4-0.5-0.5-0.5-0.5-0.5-0.8-1.2-1.2
OUT0.8040.8020.7530.6970.6800.6620.6340.6080.6000.54!0.524
OEV
2.71.82.32.42.32.22.12.52.84.75.9
RELIN
65.664.361.158.658.257.857.356.954.149.948.9
HER IDIN
132.4137.3142.3144.8145.0144.8144.9144.8144,9141.7139.6
BETAMOUT
60.158.655.551.250.249.148.047.339.625.220.6
VELOUT
137.6142.9145.4148.8148.5148.1145.1141.0157.4166.4166.7
TOTALIN
288.6288.5288.2288.1288.0287.9288.0288.1288.0287.9287.9
TEMPRATIO1.049
.047
.044
.046
.047
.050
.053
.056
.055
.0651.069
TANG VELIN
-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0
OUT49.547.945.052.356.560.066.671.175.2
101.8110.6
MERID MACH NOIN
0.3950.4100:4260.4340.4340.4340.4340.4330.4340.4240.418
i\D-FACT
0.1990.1910.1810.2040.2200.2340.2660.2940.2550.2710.276
'OUT0.4020.4180.4260.4360.4360.4340.4250.4120.4620.4890.490
Err
0.7320.8070.8850.8920.8840.8450.7790.7130.9020.9190.920
LOSS COEFFTOT0.0960.0670.0420.0460.0510.0720.1120.1530.0590.0700.077
PROF0.0950.0670.0420.0460.0510.0720.1120.1530.0590.0700.077
TOTALIN
10.0910.1310.1310.1410.1410.1310.1410.1410.1410.1410.13
WHEEL• IN292.3285.4258.1237.0233.8229.5226.1222.1200.2168.5159.9
MERIDVEL R1.0391.0411.021
.027
.024
.022
.001
.974
.086
.174
.194
PRESSRATIO1.1311.1381.1431.1521.1541.1551.1531.1461.1861.2261.239
SPEEDOUT
288.2281.6256.4237.4234.5230. 7227.7224.2205.5180.0173.4
PEA< SSMACH NO
1.1881.1711.1641.1421.1401.1321.1281.1211.0761.0080.983
LOSS PARAMTOT0.0180.0130.0080.0090.0100.0140.0220.0300.0120.0140.015
PROF0.0180.0130.0080.0090.0100.0140.0220.0300.0120.0140.015
36
TABLE Vn. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(m) 70 Percent of design speed; reading number 989
RADIIRPI23456789
1011
IN24.62824.06121.74019.95919.66019.35519.05318.74816.87114.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABS VELRP
123456
^89
1011
RP123456789
1011
IN123.5127.6132.5134.4134.5134.4134.5134.4133.8133.0127.9
ABSIN
0.3670.3800.3950.4010.4020.4010.4010.4010.4000.3680.381
OUT146.8149.7149.2152.6154.4156.1157.1155.7165.8186.8194.1
MACH NOOUT
0.4240.4340.4340.4440.4500.4540.4560.4520.4830.5460.567
ABS BETAMIN
-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0
OUT27.727.025.827.929.230.432.334.132.236.538.4
REL VELIN
317.1312.9290.1272.1269.4266.0263.2260.1240.9213.1205.2
RELIN
0.9440.9320.8660.8130.8050.7940.7860.7770.7190.6360.612
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN3.83.95.46.36.56.66.87.07.78.58.9
SS1.00.91.3.3.4.4.4.5.4.3
1.4
OUT255.3252.2234.0213.7208.3202.9195.8188.6182.9165.3161.2
MACH NOOUT
0.7370.7310.6800.6220.6060.5900.5690.5470.5330.4830.471
DEV
2.01.31.82.11.81.51.42.03.14.44.7
REL BETAMIN
67.165.962.860.460.159.659.358.956.352.451.5
MERIDIN
123.5127.6132.5134.4134.5134.4134.5134.4133.8130.0127.9
OUT59.458.155.050.849.748.447.346.839.924.819.4
VELOUT
130.0133.4134.3134.9134.8'134.7132.8129.0140.4150.1152.1
TOTAL TEMPIN
288.5288.4288.1288.1288.0288.1288.2288.1287.9287.9288.0
RATIO1.0721.0671.0601.0611.0611.0631.0661.0681.0651.0721.076
TANG VELIN
-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0
OUT68.267.864.871.375.479.084.087.288.2
111.2120. 6
MERID MACH NOIN
0.3670.3800.3950.4010.4020.4010.4010.4010.4000.3880.381
D-rACT
0.2760.2730.2680.2960.3120.3270.3510.3730.3380.3440.344
OUT0.3750.3860.3910.3930.3920.3920.3860.3740.4090.4390.444
EFF
0.7650.8250.8980.8940.8950.8760.8330.7860.8960.9240.9U
LOSS COEFFTOT0.1230.0870.0520.0600.0610.0760.1080.1440.0770.0760.097
PROF0.1210.0860.0520.0600.0610.0760.1080.1440.0770.0760.097
TOTALIN
10.0910.1310.1410.1410.1410.1410.1410.1410.1410.1410.12
WHEELIN
292.1285.7258.1236.6233.5229.5226.3222.7200.2168.9160.5
MERIDVEL R1.0531.0461.0141.0041.0021.0020.9870.9601.0491.1541.189
PRESSRATIO1.2061.2071.2021.2031.206
.208
.208
.201
.219
.253
.266
SPEEDOUT
288.0281.9256.4237.0234.2230.7227.9224.8205.5180.4174.1
PEA< ssMACH NO
1.2231.2111.1951,1681.1651.1581.1551.1501.0981.0261.001
LOSS PARAMTOT0.0240.0170.0100.0120.0120.0150.0220.0290.0150.0150.019
PROF0.0230.0170.0100.0120.0120.0150.0220.0290.0150.0150.019
37
TABLE VH. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(n) 70 Percent of design speed; reading number 990
RADIIRP
123456789
1011
IN24.62824.06121.74019.95919.66019.35519.05318.74816.87114.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABS VELRP
123456789
10« 1
IN115.1117.9122.6124.1124.0124.2124.0123.8123.2119.9118.2
OUT146.7150.4145.3150.9152.9155.3153.4152.3160.6181.5188.3
ABS MACH NORP
123456789
1011
IN0.3420.3500.3650.3700.3690.3700.3690.3690.3670.3570.352
OUT0.4200.4330.4200.4360.4420.4490.4430.4400.4660.5280.549
ABSIN
-0.0-0.0-0.0-0.0-0.0
0.0-0.0-0.0-0.0-0.0-0.0
RELIN
314.6309.5286.4268.2264.6261.7258.5255.2235.8207.5199.6
BET AMOUT35.734.533.234.635.536.439.140.637.840.441.6
VELOUT
235.3232.8215.3196.7191.8187.3177.6171.1166.6152.0149.1
REL MACH NOIN
Q.9350.9200.8530.7990.7880.7800.7700.7600.7030.6180.594
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10 .0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN5.5.7.8.8.8.8.9.9.
10.11.
36335790981
ss2.52.53.13.43.43.43.53.63.63.63.6
OUT0.6740.6690.6220.5690.5550.5420.5130.4940.4830.4430.435
DEV
2.21.12.42.01.61.22.02.73.64.24.6
REL BETAMIN
68.567.664.762.462.161.761.361.058.554.753.7
MERIDIN
115.1117.9122.6124.1124.0124.2124.0123.8123.2119.9118.2
OUT59.657.855.650.849.548.147.947.540.424.619.3
VELOUT
119.1123.9121.6124.3124.6125.1119.1115.6126.9138.2140.7
TOTAL TEMPIN RATIO
288.6288.5288.2288.0288.1288.0288.0288.0287.9287.9287.9
TANGIN
-0.0-0.0-0.0-0.0-0.0
0 .0-0 .0-0.0-0.0-0.0-0.0
.090
.082
.072
.073
.074
.075
.076
.077
.072
.077
.078
VELOUT85.785.379.585.688.792.196.799.198.4
117.6125.0
MERID MACH NOIN
0.3420.3500.3650.3700.3690.3700.3690.3690.3670.3570.352
D-FACT
0.3540.3490.3410.3650.3780.3900.4240.4430.4050.3970.391
OUT0.3410.3560.3510.3590.3600.3620.3440.3340.3680.4020.410
EFF LOSS COEFF
0.7250.8070.8660.8620.8600.8610.8190.7930.8760.9290.928
TOT0.1770.1180.0820.0950.0990.1020.1370.1610.1040.0800.088
PROF0.1750.1170.0820.0950.0990.1020.1370.1610.1040.0800.088
TOTALIN
10.1110.1310.1310.1310.1310.1410.1310.1310.1410.1310.12
WHEELIN
292.8286.1258.9237.7233.8230.3226.8223.2201.1169.4160.8
MERIDVEL R1.0341.0510.9921.0011.0041.0070.9610.9341.0291.1531.190
PRESSRATIO1.2471.2531.2351.2381.2401.2441.2361.2301.2401.2731.279
SPEEDOUT
288.7282.3257.2238.1234.5231.6228.4225.2206.3180.9174.4
PEAK SSMACH NO
1.2601.2511.2311.2031.1951.1911.1851.1791.1251.0441.016
LOSS PARAMTOT0.0340.0230.0160.0180.0200.0200.0270.0320.0210.0160.017
PROF0.0330.0230.0150.0180.0200.0200.0270.0320.0210.0160.017
38
TABLE VII. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(o) 70 Percent of design speed; reading number 991
RADIIRP
123456789
1011
IN24.62824.06121.74019.95919.56019.35519.05318.74816.87114.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABS VELRP
123A5618<i
1011
IN103.3107.3110.7111.4111.6111.3111.4111.3110.9109.0107.3
OUT144.5149.7145.9150.5151.5150.5149.2149.1157.2176.8180.6
ABS MACH NORP
123456789
10\ \
IN0.3060.3180.3290.3310.3310.3310.3310.3310.3300.3240.319
OUT0.4110.4270.4190.4330.4360.4330.4290.4290.4540.5130.525
ABSIN0.0
-0.0-0.0
0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0
RELIN
310.2305.8281.6261.9259.0255.9252.6249.1229.3200.8192.7
BET AMOUT42.940.239.040.340.241.744.846.443.143.044.3
VELOUT
217.5218.5200.5181.2179.1172.9162.4155.8151.3142.3137.7
REL MACH NOIN
0.9190.9070.8370.7780.7700.7600.7510.7400.6810.5960.572
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN7.7.
34
9.510.10.11.H.11.12.13.13.
79245536
SS4.54.45.35.85.86.06.06.06.26.06.1
OUT0.6190.6240.5760.5210.5160.4980.4670.4480.4370.4130.400
DEV
3.51.72.41.91.92.53.43.93.94.35.4
REL BETAMIN
70.669.566.964.864.564.263.863.561.157.156.1
MERIDIN
103.3107.3110.7111.4111.6111.3111.4111.3110.9109.0107.3
OUT60.958.455.650.749.849.449.348.740.724.720.2
VELOUT
105.8114.4113.4114.8115.7112.4105.8102.9114.8129.3129.3
TOTAL TEMPIN
288.6288.5288.1288.0288.1288.0288.0288.0288.0288.0288.0
RATIO1.1021.0961.0851.0821.0821.0831.0831.0841.0791.0791.080
TANG VELIN0.0
-0.0-0.0
0 .0-0.0-0.0-0.0-0.0-0.0-0.0-0.0
OUT98.496.591.897.397.8
100.2105.1107.9107.4120.6126.1
MERID MACH NOIN
0.3060.3180.3290.3310.3310.3310.3310.3310.3300.3240.319
D-FACT
0.4180.4010.3970.4230.4240.4420.4810.5010.4650.4290.429
OUT0.3010.3270.3250.3300.3330.3240.3040.2960.3310.3750.376
EFF
0.6950.7600.8110.8350.8370.8210.7940.7770.8490.9270.920
LOSS COEFFTOT0.2230.1720.1380.1310.1320.1480.1740.1940.1440.0890.105
PROF0.2200.1700.1370.1310.1320.1480.1740.1940.1440.0890.105
TOTALIN
10.1110.1310.1310.1410.1310.1310.1410.1310.1410.1310.13
WHEELIN
292.5286.4258.9237.0233.8230.3226.7222.9200.7168.7160.0
MERIOVEL R1.0241.0671.0241.0301.0371.0100.9500.9241.0341.1861,204
PRESSRATIO1.2701.2801.262.26!.262.258.251.246.254.282
1.281
SPEEDOUT
288.4282.6257.3237.4234.5231.6228.3224.9206.0180.1173.5
PEA< SSMACH NO
.305
.253
.271
.235
.230
.226
.218
.2101.1511.0581.027
LOSS PARAMTOT0.0410.0330.0260.0260.0260.0290.0340.0370.0290.0180.021
PROF0.0400.0330.0260.0260.0260.0290.0340.0370.0290.0180.021
39
TABLE VH. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(p) .70 Percent of design speed; reading number 992
RADIIRP
1234567e9
1011
RP123I56•?
89
' 0f <
IN24.62824.05121.74019.95919.66019.35519.05318.74816.87114.20113.492
ABSIN
91.394.198.8
100.7100.9101.0101.2101.21 0 1 . 5 -1CG.598.9
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
VEXOUT
157.9150.4147.0150.6151.1150.2148.2148.3155.7174.2179.4
ABS MACH NORP
t23t56~
89
10u
5°i2345o7
35
* ^* *
IN0.2700.2780.2930.2990.2990.3000.3000.3000.3310.2980.293
PERCENTSPAN5. CO
i:.:o3;.::45. CO47.5;5:.-.052.5:55.::
• T:.:O9 I .CS55. 55
OUT0.4440.4250.4210.4320.4340.4310.4250.4250.4490.505Q.521
ABSIN
-0.0-0.0
0.0-0.0
0.00.0
-0.00.0
-0.0-0.0
0.0
RELIN
306.9300.9276.2257.5254.3251.1248.1244.9224.7196.5188.7
BET AMOUT59.852.844.044.745.246.549.150.947.144.745.7
VELOUT
171.8186.0186.9169.6165.8160.0151.2144.4140.1136.7133.4
REL MACH NOIN
0.9080.8910.8190.7640.7540.7450.7J60.7260.6670.5830.559
INCIDENCEKEA
9.9.
' 1.12.13.13.13.13.14.15.15.
K4879'•
24
^G48
SS6.76.77.57.98.08.08.18.28.38.18.3
OUT0.4830.5260.5350.4870.4760.4590.4340.4140.4040.3960.387
DEV
5.14 .02.42.02.22.94.24.84.14.65.4
RELIN
72.771.869.067.066.666.365.965.663.159.258.4
MERIDIN
91.394.198.8
100 .7100.91 0 1 . 0101.2101.2101.5100.598.9
BETAMOUT
62.560.755.650.850.049.850.149.640.925.120.1
VELOUT79.390.9
105.7107.1106.5103.496.993.5
106.0123.9125.2
TOTALIN
288.6288.5288.1288.0288.1288.1288.0287.9288.0288.0288.0
TANGIN
-0.0-0.0
0 .0-0.0
0 .00.0
-0.00.0
-0.0-0.0
0.0
TEMPRATIO1.1311.1191.0921.0881.0881.0881.0881.0881.0831.0801.081
VELOUT
136.5119.8102.1105.8107.1108.9112.1115.1114.1122.5128.4
MERID MACH NOIN
0.2700.2780.2930.2990.2990.3000.3000.3000.3010.2980.293
D-FACT
0.6070.5280.4470.4680.4770.4930.5250.5480.5120.4470.443
DOT0.2230.2570.3020.3070.3060.2970.2780.2680.3050.3590.364
EFF
0.6120.6380.7810.8090.8080.7970.7740.7630.8230.9320.929
LOSS COEFFTOT0.3560.3150.1770.1660.1700.1830.2070.2230.1830.0880.099
PROF0.3500.3110.1760.1660.1700.1830.2070.2230.1830.0880.099
TOTALIN
10.1110.1310.1310.1310.1310.1310.1410.1310.1410.1310.13
WHEELIN
293.0285.8257.9237.0233.4229.9226.5223.0200.5168.8160.7
MERIDVEL R0.8690.9671.0701.0641.0561.0230.9580.9251.0441.2321.266
PRESSRATIO1.3111.2921.2751.2731.2721.2671.2591.2561.2601.2881.289
SPEEDOUT
288.8282.0256.2237.4234.2231.1228.1225.0205.7180.3174.2
PEAK ssMACH NO
1.3551.3391.3041.2671.2601.2531.2461.2401.1731.0761.048
LOSS PARAMTOT0.0620.0570.0330.0320.0330.0350.0390.0420.0360.0180.020
PROF0.0610.0560.0330.0320.0330.0350.0390.0420.0360.0180.020
40
TABLE VH. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(q) 60 Percent of design speed; reading number 993
RADIIRP
123456789
1011
IN24.62824.06121.74019.95919.66019.35519.05318.74816.871U.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABS VELRPI23&56T
89
1011
RP123456789
1011
IN74.377.181.483.083.182.882.983.183.582.881.7
ABSIN
0.2190.2280.2410.2460.2460.2450.2450.2460.2470.2450.242
OUT135.0128.6124.0127.5127.7126.8125.8125.3132.3146.7152.2
MACH NOOUT
0.3840.3670.3580.3680.3690.3660.3630.3620.3830.4270.443
ABSIN
-0.0-0.0
0.00.0
-0.0-0.0-0.0-0.0-0.0-0.0
0.0
RELIN
259.4254.8234.2217.9215.1211.6209.320B.4189.4165.5158.6
BET AMOUT59.252.743.4
43.944.546.4
48.650.747.744.445.3
VELOUT
146.5157.8160.5146.0142.4135.8129.6122.8117.6116.4114.0
REL MACH NOIN
0.7650.7520.6920.6440.6360.6260.6190.6100.5600.4890.469
PERCENT INCIDENCERP
123456789
1011
SPAN
5.0010.0030.0045.0047.5050.0052.5055.0070.00dO. 0095.00
MEANt o .10.12.13.13.13.14.14.15.16.
. 16.
14357923314
SS7.37.38.28.58.68.78.88.89.08.88.9
OUT0.4170.4510.4630.4220.4110.3920.3740.3540.3410.3390.332
OEV
4.53.72.72.22.43.04.14.93.95.35.4
REL BETAMIN
73.372.469.7
67.667.367.066.7
66.363.860.059.0
MERIDIN
74.377.181.4
83.083.182.882.983.183.582.881.7
OUT61.860.4
55.951.050.249.950.049.740.725.720.1
VELOUT69.277.990.091.991.187.4
83.379.389.1
104.9107.0
TOTAL TEMPIN
288.6288.4288.1288.1288.1288.1288.0288.1288.0287.9288.0
RATIO.096.087.066.064.063
1.0631.0631.0631.0611.0581.058
TANG VELIN
-0.0-0.0
0.00.0
-0.0-0.0-0.0-0.0-0.0-0.0
0.0
OUT116.0102.485.388.389.691.894.397.097.8
102.6108.2
MERID MACH NOIN
0.2190.2280.2410.2460.2460.2450.2450.2460.2470.2450.242
D-FACT
0.6030.5280.4360.4550.4650.4890.5150.5430.5170.4390.431
OUT0.1970.2220.2600.2650.2630.2530.2400.2290.2580.3050.3.12
EFF
0.6200.6440.7870.8120.8120.7980.7820.7650.8190.9340.932
LOSS COEFFTOT0.3430.3040.1650.1600.1630.1790.1960.2170.1880.0840.095
PROF0.3430.3040.1650.1600.1630.1790.1960.2170.1880.0840.095
TOTALIN
10.1110.1310.1310.1310.1310.1310.1310.1310.1310.1310.13
WHEELIN
248.6242.8219.6201.4198.4194.7192.2189.0170.0143.3136.0
MERIDVEL R0.9301.0101.1071.1071.0961.0571.0040.9541.0681.2671.310
PRESSRATIO1.2231.210
.194
.193
.192
.188
.184
.180
.184
.2011.203
SPEEDOUT
245.0239.6218.2201.7199.0195.7193.6190.7174.5153.0147.4
PEAK ssMACH NO
•1.160I . f471.1171.0821.0771.0671.0641.0560.9990.9160.889
LOSS PARAMTOT0.0610.0550.0310.0310.0320.0350.0370.0410.0380.0170.019
PROF0.0610.0550.0310.0310.0320.0350.0370.0410.0380.0170.019
41
TABLE VII. - Concluded. BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 11
(r) 50 Percent of design speed; reading number 994
RADIIRP
123A56789
1011
IN24.62824.06121.74019.95919.66019.35519.05318.74816.87114.20113.492
OUT24.28023.74421.60019.99219.72319.45619.18718.92017.31315.16914.633
ABS VELRP
1234567891011
IN60.363.066.067.467.567.667.967.667.967.666.4
OUT113.0107.3103.2106 .-2106.4106.2105.4104.5110. 7122.8125.9
ABS MACH NORP
123456789
10U
IN0.1780.1860.1950.1990.1990.1990.2000.2000.2000.2000.19S
OUT0.3250.3090.2990.3080.3090.3080.3060.3030.3220.3580.368
ABSIN
-0.00.00.0
-0.00.00.0
-0.0-0.00.00.00.0
RELIN
216.4212.3194.6181.1179.0176.6174.8171.9157.3137.7131.6
BET AMOUT58.252.942.544.444.946.649.150.847.644.345.4
VELOUT124.0131.6135.6120.9118.4113.5107.7102.798.297.694.5
REL MACH NOIN
0.6380.6260.5740.5340.5280.5210.5160.5070.4640.4060.388
PERCENT INCIDENCERP
1234567891011
SPAN5.0010.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN10.10.12.
' 14.14.14.14.14.15.16.
6780357987
17.1
SS7.87.78.79.19.29.39.39.49.59.49.6
OUT0.3560.3790.3930.3510.3440.3300.3120.2980.2860.2850.276
DEV
4.03.82.72.32.53.04.25.13.85.36.1
REL BETAMIN
73.872.770.268.267.867.567.266.864.460.659.7
MERIDIN
60.363.066.067.467.567.667.967.667.967.666.4
OUT6t;460.555.851.150.450.050.149.940.625.720.8
VELOUT59.564.776.275.975.573.069.166.174.688.088.4
TOTAL TEMPIN
288.5288.4288.2288.0288.0288.0288.1288.0288.0288.0287.9
RATIO1.0671.0611.0461.0441.0441.0441 .0441.0441.0421.0401.040
TANG VELIN
-0.00.00.0
-0.00.00.0
-0.0-0.00.00.00.0
OUT96.185.569.774.375.177.179.681.081.885.789.6
MERID MACH NOIN
0.1780.1860.1950.1990.1990.1990.2000.2000.2000.2000.196
D-FACT
0.5930.5280.4230.4590.4670.4890.5190.5410.5140.4340.431
OUT0.1710.1860.2210.2210.2190.2120.2010.1920.2170.2570.258
Err0.6220.6440.7860.8160.8160.8070.7850.7640.8190.9350.928
LOSS COEFFTOT0.3360.2970.1620.1550.1550.1670.1910.2150.1870.0830.100
PROF0.3360.2970.1620.1530.1550.1670.1910.2150.1870.0830.100
TOTALIN
10.1210.1310.1310.1310.1310.1310.1310.1310.1310.1310.13
WHEELIN
207.8202.8183.1168.1165.8163.2161.1158.1141.9119.9113.6
MERIDVEL R0.9861.0271.154.127.118.081.0180.978.098.301.331
PRESSRATIO1.1541 . 1 43.132.132.131.130.127.124.127
1.1381.138
SPEEDOUT204.9200.1181.9168.4166.3164.0162.2159.5145.6128.1123.2
PEAK SSMACH NO0.9770.9620.9360.9080.9040.8990.8950.8880.8370.7690.746
LOSS PARAMTOT0.0610.0540.0300.0300.0300.0320.0360.0400.0370.0170.020
PROF0.0610.0540.0300.0300.0300.0320.0360.0400.0370.0170.020
42
TABLE Vm. - BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(a) 100 Percent of design speed; reading number 968
RADIIRP
12345&789
ID11
IN23,91923,45221,55720,11419,87319,62919,38819,14717.69115.75515.273
OUT23.90923.45921.63620.26720.03819.80919.58319.35518.00416.23815.806
ABS VELRP
123A56-T
8&
1011
IN243.4243.7238.6238.3227.2216.2210.6215.6251.5270.8276.2
OUT196.6205.7203.5196.6192.4185.0183.1182.9209.1228.7223.8
ABS MACH NORP!23456789
1011
IN0.6920.6970.6860.6830.6490.6180.6020.6170.7300.7900.805
OUT0.5510.5800.5780.5580.5460.5240.5200.5190.5980.6570.639
ABSIN
29.728.429.034.635.134.835.335.433.336.038.2
RELIN
243.4243.7238.6238.3227.2216.2210.6215.6251.5270.8276.2
BET AMOUT3.42.5
-0.61.20.6
-1.3-2.0-2.1-0.5-0.4
1.7
vaOUT
196.6205.7203.5196.6192.4185.0183.1182.5209.1228.7223.8
REL MACH NOIN
0.6920.6970.6860.6830.6490.6180.6020.6170.7300.7900.805
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN-0.-0.-0.4.4.4.4.4.1.0.1.
68179476067
SS-7.0-7.2-6.5-1.7-1.4-1.9-1.6-1.8-5.3-5.7-4.6
OUT0.5510.5800.5780.5580.5460.5240.5200.5190.5980.6570.639
DEV
13.011.57.69.28.66.65.95.97.47.79.9
RELIN
29.728.429.034.635.134.835.335.433.336.038.2
MERIDIN
211.5214.3208.7196.1185.9177.6171.9175.7210.3219.2217.1
BET AMOUT3.42.5
-0.61.20.6
-1.3-2.0-2.1-0.5-0.4
1.7
VELOUT
196.3205.5203.5196.5192.4185-.0183.0182.7209.1228.7223.7
TOTAL TEMPIN
337.1334.2329.3330.9330.6328.0327.0327.2327.2329.0331.2
RATIO0.9980.9980.9990.9920.9920.9970.9960.9960.9970.9950.996
TANG VELIN
120.5116.1115.5135.4130.6123.3121.7124.8138.1159.0170.7
OUT11.58.8
-2.24.12.0
-4.4-6.5-6.6-1.8-1.56.6
MERID MACH NOIN
0.6010.6130.6000.5620.5310.5070.4910.5030.6100.6390.632
D-FACT
0.3650.3230.3190.3540.3350.3310.3210.3400.3270.3050.335
OUT0.5500.5800.5780.5580.5460.5240.5190.5190.5980.6570.639
EFF
0.0.0.0.0.0.0.0.0.0.0.
LOSSTOT0.1420.0590.0480.0890.018
-0.011-0.043
0 .0100.0680.080
COEFFPROF0.1420.0590.0480.0890.018
-0.011-0.043
0.0100.0680.080
0.166 0.166
TOTALIN
15.2815.2815.0914.9014.4614.1313.9814.1215.0915.4715.63
WHEELIN0.0.0.0.0.0.0.0.0.0.0.
MERIOVEL R0.9280.95&0.9751.0021.0351.0421.0651.0400.9941.0431.030
PRESSRATIO0.9610.9840.9870.9760.9961.0021.0090.9980.9800.9730.943
SPEEDOUT0.0.0.0.0.0.0.0.0.0.0.
PEA< ssMACH NO
0,7960,7730,7630,8890,8510.7990.7840.8000.8450.9130.972
LOSS PARAMTOT0.0550.0220.0170.0290.006
-0.003-0.014
0.0030.0190.0200.041
PROF0.0550.0220.0170.0290.006
-0.003-0.014
0.0030.0190.0200.041
43
TABLE VIH. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(b) 100 Percent of design speed; reading number 969
RADIIR?
•23456789
1011
IN23.91923.45221.55723. ',1419.87319.62919.38819. '4717.69115.75515.273
C'jT
23.90923.45921.63523.25720.03819.80919.58319.35518.00416.23815.806
ABS VELRP
•,23455—89
15"'
IN249.0243.8233.7241.3235.4229.2222.322G. 2243.2255.6265.4
CUT190.5197.8187.9183.7180.0174.0171.3170.1183.4192.5184.7
ABS MACH NORP
123456789
1011
IN0.6950.6860.6630.6850.668
. 0.6500.6300.6240.6970.7370.766
OUT0.5240.5480.5250.5140.5030.4860.4790.4760.5160.5430.519
ABSIN
37. 035.735.538.539.039.640.440.938.540.642.3
RELIN
249.0243.8233.7241.3235.4229.2222.3220.2243.2255.6265.4
BETAMOUT4.94.90.42.11.80.4
-0.1-0.70.50.33.0
VELOUT
190.5197.8187.9183.7180.0174.0171.3170 .1183.4192.5184.7
REL MACH NOIN
0.6950.6860.6630.6850.6680.6500.6300.6240.6970.7370.766
PERCENT INCIDENCERPI23456789
1011
SPAN5.00
• 10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN6.6.6.8.8.9.9.
10.6.5.5.
74569391329
SS0.30.00.02.22.52.93.53.7
-0.1-1.1-0.4
OUT0.5240.5480.5250.5140.5030.4860.4790.4760.5160.5430.519
DEV
14.513.98.6
10.19.88.47.87.28.58.4
11.2
RELIN
37.035.735.538.539.039.640.440.938.540.642.3
MERIDIN
198.9198.0190.3188.7182.8176.6169.2166.5190.2194.2196.2
BETAMOUT4.94.90.4E.I1.80.4
-0.1-0.70.50.33.0
VELOUT
189.8197.1187.9183.6180.0174.0171.3170.1183.4192.5184.5
-TOTALIN
350.1343.8336.7337.4336.6335.5334.5333.9332.0331.4333.9
TANCIN
149.8142.3135.7150.3148.2146.1144.2144.1151.5166.2178.8
TEMPRATIO0.9911.0000.9990.9930.9940.9950.9950.9960.9960.9990.996
VELOUT16.117.01.46.75.61.2
-0.4-2.2
1.71.19.6
MERID MACH NOIN
0.5550.5570.5400.5360.5190.5010.4790.4720.5450.5600.566
D-FACT
0.4420.3830.3960.4320.4290.4410.4330.4330.4210.4100.460
OUT0.5220.5460.5250.5130.5030.4860.4790.4760.5160.5430.518
EFF
0.0.0.0.0.0.0.0.0.0.0.
LOSS COEFFTOT0.1670.0730.0560.1150.0870.0830.0420.0300.0780.0860.195
PROF0.1670.0730.0560.1150.0870.0830.0420.0300.0780.0860.195
TOTALIN
16.8716.7216.2316.2415.9615.7215.4615.3715.8815.9316.19
WHEELIN0.0.0.0.0.0.0.0.0.0.0.
MERIDVEL R0.9540.9950.9870.9730.9840.9851.0121.0220.9650.9910.940
PRESSRATIO0.9540.9800.9860.9690.9770.9790.990-0.9930.9780.9740.937
SPEEDOUT
0.0.0.0.0.0.0.0.0.0.0.
PEAK ssMACH NO
0.9900.9560.9070.9860.9680.9500.9340.9300.9480.9831.044
LOSS PARAMTOT0.0640.0270.0200.0370.0280.0270.0130.0090.0220.0220.049
PROF0.0640.0270.0200.0370.0280.0270.0130.0090.0220.0220.049
44
TABLE Vm. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(c) 100 Percent of design speed; reading number 970
RADIIRP
123456789
1011
IN23.91923. -»5221 .55720.IU19.87319.62919.38819. U717.69115.75615.273
OUT23.90923.45921.63620.26720.03819.80919.58319.35518.00416.23815.806
ABS VELRP
123456789
1011
IN250.1244.2230.4234.0230.5225.0219.7219.7237.3
• 2-44.0256.6
OUT186.8194.9177.4170.6167.9162.2159.6158.8167.0171.0161.9
ABS MACH NORP
123A567e9
10u
IN0.6880.6790.6470.6600.6500.6340.6180.6180.6760.6980.736
OUT0.5070.5330.4910.4730.4650.4490.4420.4400.4660.4780.451
ABSIN
42.940.039.842.042.243.244.945.142.243.644.9
RELIN
250.1244.2230.4234.0230.5225.0219.7219.7237.3244.0256.6
BET AMOUT5.55.21.52.51.90.80.50.31.80.93.9
VELOUT
186.8194.9177.4170.6167.9162.2159.6158.8167;0
171.0161.9
REL MACH NOIN
0.6880.6790.6470.6600.6500.6340.6180.6180.6760.6980.736
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN12.610.10.12.12.12.14.14.9.8.8.
8801943934
556.24.44.45.65.76.58.07.93.62.02.2
OUT0.5070.5330.4910.4730.4650.4490.4420.4400.4660.4780.451
DEV
15.214.29.7
10.59.98.88.58.39.79.0
12.2
REL BETAMIN
42.940.039.842.042.243.244.945.142.243.644.9
MERIDIN
183.2187.0176.9174.0170.8164.0155.5155.1175.8176.6181.7
OUT5.55.21.52.51.90.80.50.31.80.93.9
VELOUT
186.0194.0177.3170.5167.8162.2159.6158.8167.0171.0161.6
TOTAL TEMPIN
359.6351.3341.5339.9339.3338.6338.3338.1335.0333.3335.2
RATIO0.9871.0000.9990.9960.9970.9970.9960.9960.9971.0010.998
TANG VELIN
170.3157.1147.6156.5154.9154.1155.1155.6159.5168.3181.2
OUT17.817.84.57.45.52.21.40.85.32.7
11.1
MERID MACH NOIN
0.5040.5200.4970.4910.4820.4620.4380.4370.5010.5060.521
D-rACT
0.4880.4180.4460.4780.4800.4930.4920.4950.4810.4700.531
OUT0.5050.5310.4900.4720.4650.4490.4420.4400.4650.4780.450
EFT
0.0.0.0.0.0.0.0.0.0.0.
LOSS COEFFTOT0.1900.0840.0830.1290.114.0.1120.0790.0750.1030.0930.216
PROF0.1900.0840.0830.1290.1140.1120.0790.0750.1030.0930.216
TOTALIN
17.7317.4916.8216.6916.5116.2816. 0616.0016.2916.1416.47
WHEELIN0.0.0.0.0.0.0.0.0.0.0.
MERIDVEL R1.0151.0381.0030.9800.9830.9891.0261.0240.9500.9680.889
PRESSRATIO0.9480.9780.9800.9670.9720.9740.9820.9830.9730.9740.935
SPEEDOUT0.0.0.0.0.0.0.0.0.0.0.
PEAK ssMACH NO
1.1191.0470.9831.0271.0131.0041.0111.0101.0041.0061.069
LOSS PARAMTOT0.0730.0320.0290.0420.0370.0350.0250.0230.0300.0240.054
PROF0.0730.0320.0290.0420.0370.0350.0250.0230.0300.0240.054
45
TABLE VIH. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(d) 100 Percent of design speed; reading number 975
RADIIRP
123456789
1011
IN23.91923.45221 .55720.11419.87319.62919.38819.14717.69115.75615.273
OUT23.90923.45921.63620.26720.03819.80919.58319.35518.00416.23815.806
ABS VELRP
123i56789
1011
IN242.0246.0230.7230.0228.6222.6219.7219.2231.9241.6253.3
OUT183.9190.1173.7161.7158.7155.7155.4154.3154.8161.8151.6
ABS MACH NORP
123456789
1011
IN0.6610.6790.6450.6470.6430.6250.6170.6150.6580.6910.726
OUT0.4960.5160.4770.4460.4380.4290.4280.4260.4290.4500.420
ABSIN
46.144.241.743.443.645.447.647.943.344.244.7
RELIN
242.0246.0230.7230.0228.6222.6219.7219.2231.9241.6253.3
BET AMOUT6.76.12.52.01.91.11.21.12.42.15.0
VELOUT
183.9190.1173.7161.7158.7155.7155.4154.3154.8161.8151.6
REL MACH NOIN
0.6610.6790.6450.6470.6430.6250.6170.6150.6580.6910.726
PERCENT INCIDENCERP
123456y
89
1011
SPAN5.00
10 .0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN15.15.12.13.13.15.17.17.11.8.8.
80654011092
SS9.48.56.27.17.08.6
10.710.74.72.61.9
OUT0.4960.5160.4770.4460.4380.4290.4280.4260.4290.4500.420
DEV
16.415.110.710.09.99.19.29.1
10.410.213.2
RELIN
46.144.241.743.443.645.447.647.943.344.244.7
MERIDIN
167.8176.3172.3167.1165.7156.4148.0146.9168.8173.2180.1
BETAMOUT6.76.12.52.01.91.11.21.12.42.15.0
VELOUT
182.6189.1173.5161.6158.6155.7155.3154.3154.7161.7151.0
TOTALIN
362.8356.5344.5341.3340.7340.1340.0340.3335.8333.6334.6
TANGIN
174.4171.5153.4158.1157.5158.4162.3162.7159.1168.4178.1
TEMPRATIO0.9891.0000.9990.9980.9980.9990.9980.9960.9991.0021.001
VELOUT21.420.17.65.65.13.13.33.16.66.0
13.1
MERID MACH NOIN
0.4580.4870.4820.4700.4660.4390.4150.4120.4790.4950.516
D-FACT
0.4840.4600.4670.5120.5190.5210.5190.5210.5200.5000.560
OUT0,4930.5130.4770.4450.4370.4290.4280.4260.4290.4500.419
Err
0.0.0.0.0.0.0.0.0.0.0.
LOSS COEFFTOT0.1930.1730.1270.1670.1620.1360.1050.0970.1300 . 1 1 10.224
PROF0.1930.1730.1270.1670.1620.1360.1050.0970.1300.1110.224
TOTALIN
17.8017.9717.1516.8616.7316.4916.3316.2616.3516.2616.52
WHEELIN0.0.0.0.0.0.0.0.0.0.0.
MERIDVEL R1.0881.0721.0070.9670.9580.9951.0491.0500.9160.9340.839
PRESSRATIO0.9510.9540.9690.9590.9610.9680.9760.9780.9670.9700.934
.SPEEDOUT
0.0.0.0.0.0.0.0.0.0.0.
PEAK SSMACH NO
1.1461.1431.0201.0371.0311.0361.0651.0631.0021.0081.049
LOSS PARAMTOT0.0740.0650.0440.0540.0520.0430.033
' 0.0300.0370.0280.056
PROF0.0740.0650.0440.0540.0520.0430.0330.030Q.Q370.0280.056
46
TABLE Vin. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(e) 100 Percent of design speed; reading number 978
RADIIRP
123A56789
1011
IN23.91923.45221.55720.11419.87319.62919.38819.14717.69115.75615.273
OUT23.90923.45921.63620.26720.03819.80919.58319.35518.00416.23815.806
ABS VELRP
123456789
1011
IN242.4246.4229.8227.2227.4222.5220.0221.2229.9242.9253.2
OUT184.0188.9173.0160.2157.8154.2153.8153.0152.6160.4151.6
ABS MACH NORP
12345&789
1011
IN0.6620.6800.6430.6390.6390.6250.6170.6200.6510.6950.726
OUT0.4960.5120.4760.4410.4350.4250.4240.4220.4230.4460.420
ABS!N
46.244.241.743.744.245.348.249.144.244.244.9
RELIN
242.4246.4229.8227.2227.4222.5220.0221.2229.9242.9253.2
BET AMOUT6.86.22.41.91.51.01.31.42.12.44.9
VELOUT
184.0188.9173.0160.2157.8154.2153.8153.0152.6160.4151.6
REL MACH NOIN
0.6620.6800.6430.6390.6390.6250.6170.6200.6510.6950.726
PERCENT INCIDENCERP
12345e7a9
1011
SPAN5.00
10 .0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN15.14.12.13.14.15.17.18.11.8.8.
99681063995
SS9.58.56.27.47.78.6
11.311.95.52.62.2
OUT0.4960.5120.4760.4410.4350.4250.4240.4220.4230.4460.420
DEV
16.515.210.69.99.69.09.39.3
10.010.513.1
REL BETAMIN
46.244.241.743.744.245.348.249.144.244.244.9
MERIDIN
167.7176.7171.6164.3163.0156.4146.7144.8164.9174.1179.2
OUT6.86.22.41.91.51.01.31.42.12.44.9
VELOUT
182.7187.8172.9160.1157.8154.2153.8152.9152.5160.3151.0
TOTAL TEMPIN
363.0357.2344.5340.9340.4340.4340.7340.9336.3333.9334.8
RATIO0.9890.9991.0000.9990.9990.9980.9970.9960.9991.0021.002
TANG VELIN
175.1171.7152.7157.0158.5158.2164.0167.2160.2169.4178.8
OUT21.720.57.25.24.22.63.43.75.66/8
13.0
MERID MACH NOIN
0.4580.4880.4800.4620.4580.4390.4110.4060.4670.4980.514
D-FACT
0.4850.4660.4670.5120.5230.5280.5290.5370.5280.5090.561
OUT0.4930.5090.4750.4410.4350.4250.4240.4210.4220.4460.419
EFF
0.0.0.0.0.0.0.0.0.0.0.
LOSS COEFFTOT0.2120.1980.1320.1600.1700.1480.1200.1230.1290.1290.221
PROF0.2120.1980.1320.1600.1700.1480.1200.1230.1290.1290.221
TOTALIN
17.8518.0117.1116.7516.7116.4816.3416.3116.2816.3216.51
WHEELIN0.0.0.0.0.0.0.0.0.0.0.
MERIDVEL R1.0901.0631.0070.9750.9680.9861.0491.0560.9250.9210.843
PRESSRATIO0.9460.9470.9680.9620.9590.9660.9730.9720.9680.9640.935
SPEEDOUT
0.0.0.0.0.0.0.0.0.0.0.
PEAK ssMACH NO
1.1501,1431.0151.0311.0391.0341.0771.0981.0111.0151.054
LOSS PARAMTOT0.0810.0750.0460.0520.0550.0470.0380.0380.0370.0330.055
PROF0.0810.0750.0460.0520.0550.0470.0380.0380.0370.0330.055
47
TABLE Vm. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(f) 90 Percent of design speed; reading number 982
RADIIRP
123456789
1011
IN23.91923.45221.55720.11419.87319.62919.38819.14717.69115.75615.273
OUT23.90923.45921.63620.26720.03819.80919.58319.35518.00416.23815.806
ABS VELRP
123A56789
1011
IN221.5221.6222.0228.9228.2219.4209.1207.0243.0260.8264.4
OUT193.2206.7211.4217.9216.4213.3212.2213.2239.8269.9249.3
ABS MACH NORP
123456789
1011
IN0.6440.6470.6500.6700.6670.6400.6090.6020.7160.7700.780
OUT0.5570.6000.6170.6370.6320.6230.6200.6230.7060.7980.729
ABSIN
20.319.821.324.625.025.926.827.626.130.532.4
RELIN
221.5221.6222.0228.9228.2219.4209.1207.0243.0260.8264.4
BETAMOUT2.21.3
-2.1-1.4
-1.5-2.1-2.4-2.2-1.7
1.65.5
VELOUT
193.2206.7211.4217.9216.4213.3212.2213.2239.8269.9249.3
REL MACH NOIN
0.6440.647 .0.6500.6700.6670.6400.6090.6020.7160.7700.780
PERCENT INCIDENCERP
123A56789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN-10.-9.-7.-5.-5.-4.-3.-3.-6.-4.-4.
14732482181
SS-16.5-15.9-14.1-11.7-11.6-10.8-10.2
-9.6-12.5-11.1-10.4
OUT0.5570.6000.6170.6370.6320.6230.6200.6230.7060.7980.729
DEV
11.810.36.16.76.55.95.65.76.39.7
13.7
REL BETAMIN
20.319.821.324.625.025.926.827.626.130.532.4
MERIDIN
207.8208.5206.8208.1206.9197.4186.7183.5218.1224.6223.3
OUT2.21.3
-2.1-1.4-1.5-2.1-2.4
-2.2-1.7
1.65.5
VELOUT
193.1206.7211.3217.9216.3213.2212.1213.1239.7269.8248.2
TOTAL TEMPIN
318.5316.3314.4316.9317.2316.2315.3315.4316.4319.4320.9
RATIO0.9981 . 0 0 00.9990.9940.9930.9950.9980.9970.9981.0051.005
TANG VELIN
76.7
75.180.895.4
96.395.994.395.8
107.1132.5141.6
OUT7.34.7
-7.9-5.2-5.7-7.9-8.8-8.3-7.07.6
23.9
MERID MACH NOIN
0.6040.6090.6060.6090.6050.5760.5440.5340.6420.6630.659
D-FACT
0.2490.1870.1870.1910.1950.1780.1390.1250.1470.0860.165
OUT0.5570.6000.6170.6370.6320.6220.6190.6220.7050.7980.725
EFT
0.0.0.0.0.0.0.0.0.0.0.
LOSS.COEFFTOT0.1900.0550.0710.0920.1050.0760 . 0 1 1
-0.0110.0650.0680.292
PROF0.1900.0550.0710.0920.1050.0760 .011
-0.0110.0650.0680.292
TOTALIN
12.8912.9113.0713.2813.2613.0212.7712.7313.7114.1614.33
WHEELIN0.0.0.0.0.0.0.0.0.0.0.
MERIDVEL R0.9290.9911.0221.0471.0461.0801.1361.1611.0991.2021.111
PRESSRATIO0.9540.9870.9820.9760.9730.9820.9971.0020.9810.9780.903
SPEEDOUT
0.0.0.0.0.0.0.0.0.0.0.
PEAK SSMACH NO
0.6440.6470.6500.6700.6670.6400.6090.6020.7160.7700.780
LOSS PARAMTOT0.0730.0210.0250.0300.0340.0240.004
-0.0030.0190.0170.072
PROF0.0730.0210.0250.0300.0340.0240.004
-0.0030.0190.0170.072
48
TABLE Vin. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(g) 90 Percent of design speed; reading number 983
RADIIRPI23456789
1011
IN23.91923.45221.55720.11419.87319.62919.38819.U717.69115.75615.273
OUT23.90923.45921.63620.26720.03819.80919.58319.35518.00416.23815.806
ABS VELRP
t23456789
1011
IN220.2218.2213.0219.2219.2216.62U.2209.3225.22^2.1255.4
OUT178.2184.6180.0182.3181.4180.2178.7177.9188.2203.3200.9
ABS MACH NORP
t23455789
1011
IN0.6270.6250.6140.6320.6320.6240.6170.6030.6540.7050.731
OUT0.5020.5230.5130.5200.5180.5140.5100.5080.5400.5840.576
ABSIN
29.930.328.731.832.332.333.534.832.736.037.4
RELIN
220.2218.2213.0219.2219.2216.6214.2209.3225.2242.1250.4
BET AMOUT4.03.3
-0.30.60.90.40.2
-0.1-0.5-0.42.1
VELOUT
178.2184.6180.0182.3181.4180.2178.7177.9188.2203.3200.9
REL MACH NOIN
0.6270.6250.6140.6320.6320.6240.6170.6030.6540.7050.731
PERCENT INCIDENCERP
123456789
1011
• SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN-0.
1.-0.
1.2.2.2.4.0.0.0.
41382090469
SS-6.8-5.4-6.7-4.6-4.2-4.4-3.5-2.4-5.9-5.7-5.3
OUT0.5020.5230.5130.5200.5180.5140.5100.5080.5400.5840.576
DEV
13.612.37.98.68.98.48.27.97.57.7
10.4
REL BETAMIN
29.930.328.731.832.332.333.534.832.736.037.4
MERIDIN
190.9188.4186.8186.4,185.3183.0178.7172.0189.5195.9198.9
OUT4.03.3
-0.30.60.90.40.2
-0.1-0.5-0.42.1
VELOUT
177.8184.3180.0182.3181.3180.2178.7177.9188.2203.3200.8
TOTAL TEMPIN
331.4327.5322.4323.1323.1322.9322.7322.2320.6322.4323.4
RATIO0.9940.9990.9990.9970.9960.9970.9960.9970.9990.9980.999
TANG VELIN
109.9110.1102.3115.4117.1115.8118.2119.4121.6142.2152.2
OUT12.310.7-1.02.02.81.40.7
-0.3-1.5-1.47.5
MERID MACH NOIN
0.5430.5390.5380.5380.5340.5280.5150.4950.5500.5710.581
D-FACT
0.3620.3270.3240.3360.3400.3350.3370.3260.3200.3100.339
OUT0.5010.5220.5130.5200.5170.5140.5100.5080.5400.5840.575
EFT
0.0.0.0.0.0.0.0.0.0.0.
LOSS COEFFTOT0.1160.0420.0500.0720.0760.0590.0520.0140.0440.0670.152
PROF0.1160.0420.0500.0720.0760.0590.0520.0140.0440.0670.152
TOTALIN
14.5214.4914.3314.4214.3814.2814.2014.0414.3514.6214.81
WHEELIN0.0.0.0.0.0.0.0.0.0.0.
MERIDVEL R0.9320.9780.9630.9780,9780.9851.0001.0350.9931.0381.009
PRESSRATIO0.9730.9900.9890.9830.9820.9860.9880.9970.9890.9810.955
SPEEDOUT0.0.0.0.0.0.0.0.0.0.0.
PEAK SSMACH NO
0.7270.7460.6740.7530.7620.7480.7620.7680.7400.8150.860
LOSS PARAMTOT0.0450.0160.0170.0230.0250.0190.0160.0040.0130.0170.038
PROF0.0450.0160.0170.0230.0250.0190.0160.0040.0130.0170.038
49
TABLE Vin. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(h) 90 Percent of design speed; reading number 984
RADIIRP
123456789
1011
IN23.91923.45221 .55720. 1U19.87319.62919.38819. H717.69115.75615.273
OUT23.90923.45921 .63620.26720.03819.80919.58319.35518.00416.23815.806
ABS VELRP
1234567
89
101!
IN218.9219.7207.9212.1210.7208.1205.2201.6209.1231.1238.3
OUT170.0176.9'164.6161.8160.9158.1156.2154.3154.5175.2168.5
ABS MACH NORP
123A56789
1011
IN0.6140.6210.5930.6070.6030.5950.5860.5750.6000.6680.690
OUT0.4720.4940.4640.4560.4540.4460.4400.4350.4370.4970.476
ABSIN
37.236.834.736.637.138.139.741.239.640.641.6
RELIN
218.9219.7207.9212.1210.7208.1205.2201.6209.1231.1238.3
BET AMOUT5.14.60.71.71.71.21.10.9
-0.30.82.9
VELOUT
170.0176.9164.6161.8160.9158.1156.2154.3154.5175.2168.5
REL MACH NOIN
0.6140.6210.5930.6070.6030.5950.5860.5750.6000.6680.690
PERCENT INCIDENCERP
123456789
10It
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN6.7.5.6.7.7.9.
10.7.5.5.
9677071&331
SS0.51.2
-0.70.30.61.32.74.00.9
-1.0-1.1
OUT0.4720.4940.4640.4560.4540.4460.4400.4350.4370.4970.476
DEV
14.813.69.09.79.79.29.18.97.78.9
11.1
REL BETAMIN
37.236.834.736.637.1
38.139.7
41.2• 39.6
40.641.6
MERIOIN
174.3175.9170.8170.2168.0163.8158.0151.7161.2175.5178.1
OUT5.14.60.71.71.71.21.10.9
-0.30.82.9
VELOUT
169.3176.3164.6161.7160.8158.0156.2154.3154.5175.2168.3
TOTAL TEMPIN
340.1335.3327.6326.7326.4326.2326.3326.1323.8324.4325.1
RATIO0.9910.9970.9980.9980.9980.9980.9970.9960.9981.0001.001
TANG VELIN
132.4131.7118.4126.6127.2128.3131.0132.7133.1150.4158.3
OUT15.214.32.14.84.83.43.02.5
-0.72.48.4
MERID MACH NOIN
0.4890,4970,4870.4870,4800.4680.4510.4330.4630.5070.516
D-FACT
0.4300.3970.4030.4230.4230.4310.4340.4340.4430.4040.446
OUT0.4700.4930.4640.4560.4530.4450.4400.4350.4370.4970.476
EFT
0.0.0.0.0.0.0.0.0.0.0.
LOSS COEFFTOT0.1310.0840.0680.0960.0880.0830.0710.0490.0750.0800.164
PROF0.1310.0840.0680.0960.0880.0830.0710.0490.0750.0800.164
TOTALIN
15.4415.4915.0214.9714.9014.7914.6814.5514.5614.9415..04
WHEELIN0.0.0.0.0.0.0.0.0.0.0.
MERIDVEL R0.9711.0020.9640.9500.9570.9650.9881.0170.9580.9980.945
PRESSRATIO0.9700.9810.9360.9790.9810.9820.9850.9900.9840.9790.955
SPEEDOUT
0.0.0.0.0.0.0.0.0.0.0.
PEAK SSMACH NO
0.8790.6900.7950.8330.8340.8380.8530.8630.8370.8920.923
LOSS PARAMTOT0.0510.0320.0240.0310.0280.0260.0220.0150.0220.0200.041
PROF0.0510.0320.0240.0310.0280.0260.0220.0150.0220.0200.041
50
TABLE vm. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(i) 90 Percent of design speed; reading number 985
RADIIUP
123456789
1011
IN23.91923.45221 .55720.11419.87319.62919.38819.14717.69115.75615.273
OUT23.90923.45921 .63620.26720.03819.80919.58319.35518.00416.23815.806
ABS VELRP
123456789
1011
IN217.5218.4202.6202.9202.2198.8196.9195.7207.2228.3233.8
OUT167.5173.8153.3143.9142.4140.4139.5138.4144.2165.3156.4
ABS MACH NORP
123456789
1011
IN0.6060.6140.5750.5760.5740.5640.5580.5540.5920.6590.676
OUT0.4630.4820.4290.4030.3980.3930.3900.3870.4050.4670.441
ABS BETAMIN
40.939.138.542.543.445.747.549.143.341.242.4
OUT5.36.2
.7
.8
.6
.3
.2
.2
.4
.33.2
REL VELIN
217.5218.4202.6202.9202.2198.8196.9195.7207.2228.3233.8
RELIN
0.6060.6140.5750.5760.5740.5640.5580.5540.5920.6590.676
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN10.9.9.
12.13.15.16.18.11.5.5.
68453393089
SS4.23.43.06.16.98.9
10.511.94.7
-0.5-0.4
OUT167.5173.8153.3143.9142.4140.4139.5138.4144.2165.3156.4
MACH NOOUT
0.4630.4820.4290.4030.3980.3930.3900.3870.4050.4670.441
DEV
15.015,29.99.99.79.39.19.29.39.4
11.4
RELIN
40.939.138.542.543.445.747.549.143.341.242.4
MERIDIN
164.3169.6158.6149.7146.8138.9133.1128.1150.8171.9172.7
BETAMOUT5.36.2
.7
.8
.6
.3
.2
.2
.4
.33.2
VELOUT
166.8172.8153.2143.8142.3140.4139.4138.4144.1165.2156.2
TOTALIN
343.5338.5329.7329.3329.3329.0329.7329.4326.3324.6325.0
TANGIN
142.5137.6126.1137.0139.0142.2145.1147.9142.1150.3157.6
TEMPRATIO0.9890.9991.0000.9960.9960.9960.9950.9940.9991.0011.002
VELOUT15.518.94.44.64.13.22.82.93.43.78.7
MERID MACH NOIN
0.4580.4770.4500.4250.4170.3940.3770.3630.4310.4960.499
D-FACT
0.4550.4100.4530.5020.5100.5150.5180.5210.4950.4380.486
OUT0.4610.4800.4280.4020.3980.3930.3900.3870.4050.4670.440
EFT
0.0.0.0.0.0.0.0.0.0.0.
LOSS COEFFTOT0.1450 . 1 0 00.1000.1450.1440.1310.1090.0900.1020.1000.171
PROF0.1450 . 1 0 00.1000.1450.1440.1310.1090.0900.1020.1000.171
TOTAL PRESSIN
15.6515.6915.0514.9014.8514.7314.6314.5414.6715.0515.05
WHEQ!N0.0.0.0.0.0.0.0.0.0.0.
MERIDVEL R1.0151.0190.9660.9610.9701.0101.0481.0810.9560.9610.905
RATIO0.9680.9780.9800.9710.9710.9750.9790.9830.9780.9750.955
. SPEEDOUT
0.0.0.0.0.0.0.0.0.0.0.
PEAK SSMACH NO
0.9450.9260.8460.9060.9180.9400.9600.9810.9020.8930.922
LOSS PARAMTOT0.0560.0380.0350.0470.0460.0420.0340.0280.0290.0260.043
PROF0.0560.0380.0350.0470.0460.0420.0340.0280.0290.0260.043
51
TABLE Vin. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(3) 90 Percent of design speed; reading number 986
SP•234•}
c7<jV
" ^"
S A D I :iK O'JT
23.91923.4522L55723.H419.873'9.02:1ii.36S19.147I 7.C->!'5. 75C15.273
23. 95923.45921.65523.25725.: 3819.8:919.58319.3551 8 . : 3415.23815.8:5
_A3S
48.745.545.549.350.351.252.653.544.341.542.6
ABS VEL RELV'
£?455—8'•t1 *
"
I N2' ' .92'5. i23' . :2:2. '.2:1.;l ' r .7.4' :"4. 31^5.32:8.6227.3254.5
OUT155.7153.9147.;137.5•37.1•35.:•54.4133.6141.6'63 . 9•51.9
ABS MAC" SOIJP
•25ln61"
89
1011
RP1234567
89
1011
I N3.5863.5990.5660.5-50.5670.5570.5480.5450.5950.6570.678
PERCENT' SPAN
5.001 0 . 0 030.0045.0047.5050.0052.5055.0070.0090.0095.00
cu'0.4260.4365.4380.3830.3810.3750.3740.3720.3960.4540.427
I N211.8215.12 5 1 . 02:2.02:i.:; 97.4194.3193.3258.6227.8234.5
BET AMOUT6.56.71.90.80.60.2
-0 .0-0.1
1.62.34.3
VELC'JT
155.7158.9147.0137.9137.1135.0134.4133.6141 .6160.9151.9
REL MAC" NOI N
0.5860.5990.5660.5700.5670.5570.5480.5450.5950.6570.678
INCIDENCEMEAN18.16.16.19.19.20.22.22.12.6.6.
43449901\21
SS12.09.9
10.013.013.514.515. e16.35:7
-0.1-0.2
OUT0.4260.4360.4080.3830.38!0.3750.3740.3720.3960.4540.427
DEV
16.215.71 0 . 18.88.68.28.07.99.5
10.412.5
REL BETAMIN OUT
48.745.545.549.350.051.252.653.544.341.542.6
KERIDI N
139.7150.71 4 1 . 0131.7129.2123.7! '8. 1115;0149.1170.6172.7
6.56.71.90.80.60.2
-0.0-0.1
1.62.34.3
VELOUT •
154.7157.8147.0137.9 '137.1135.0134.4133.6141.5160.8151.4
TOTALIN
347.9343.8334.2332.9332.8332.4331.9331 .6327.5324.8325.3
TANGIN
159.2153.5143.3153.2154.0153.9154.2155.5145.8151.0158.6
TEMPR A T I O0.9890.9971 . 0 0 10.9960.9960.9960.9960.9961 . 0 0 01.0031.002
VELOUT17.718.54.92.01.40.5
-0.0-0.34.06.4
11.5
M E R I D MACH NOI N
0.3860.4200.3970.3720.3650.349 '0.3330.3240.4250.4920.499
D-FACT
0.5230.4990.5080.5600.5620.5620.5570.5570.5150.4540.505 •
OUT0.4230.4330.4070.3830.3810.3750.3740.3720.3960.4540.426
EFF
0.0.0.0.0.0.0.0.0.0.0.
LOSS COEFFTOT0.2450.2330.1520.1890.1820.1570.1270 . 1 1 00.1290.1230.198
PROF0.2450.2330.1520.1890.1820.1570.1270.1100.1290.1230.198
TOTALIN
15.6215.7115.07
.14.9514.90U.7614.6514.5914.8115.1615.18
WHEELIN0.0.0.0.0.0.0.0.0.0.0.
MERIDVEL R1 . 1 0 71.0471.0431.0461.0611.0911.1381.1620,9490.9430.877
PRESSR A T I O0.9490.9500.9700.9630.9640.9700.9770.9800.9730.9690.948
SPEEDOUT0.0.0.0.0.0.0.0.0.0.0.
PEAK SSMACH NO
1.0691.0350.9671.0291.0341.0341.0391.0490.9270.8990.929
LOSS PARAMTOT0.0940.0880.0530.0610.0580.0500.0400.0340.0370.0320.049
PROF0.0940.0880.0530.0610.0580.0500.0400.0340.0370.0320.049
52
TABLE Vm. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(k) 80 Percent of design speed; reading number 987
RADIIRP
12345e7e9
10n
IN23.91923.45221.55720.11419.87319.62919.38819.14717.69115.75615.273
OUT23.90923.45921.63620.26720.03819.80919.58319.35518.00416.23815.806
ABS VELRP
123I56789
101!
IN185.6185.3179.2181.9182.0178.8176.2174.6187.8203.4209.6
OUT132.4135.5133.1127.6126.6125.3124.5124.2130.0U6.3140.6
ABS MACH NORP
t23456789
1011
IN0.5190.5210.5090.5180.5190.5090.5020.4970.5390.5890.608
OUT0.3670.3770.3740.3590.3560.3530.3510.3500.3680.4160.399
ABSIN
52.746.245.645.645.747.249.150.643.541.142.2
RELIN
185.6185.3179.2181.9182.0178.8176.2174.6187.8203.4209.6
BET AMOUT6.15.42.01.91.71.21.00.81.61.63.5
VELOUT
132.4135.5133.1127.6126.6125.3124.5124.2130.0146.3140.6
REL MACH NOIN
0.5190.5210.5090.5180.5190.5090.5020.4970.5390.5890.608
PERCENT INCIDENCERP
123A567e9
1011
SPAN5.00
- 10.0030.0045.0047.5050. CO52.50
'55.0070.0090.0095.00
MEAN22.416.916.515.715.516.918.519.811.25.85.7
SS16.010.510.19.39.2
10.512.113.44.9
-0.5-0.6
OUT0,3670.3770.3740.3590.3560.3530.3510.3500.3680.4160.399
DEV
15.814.410.29.99.79.29.08.89.59.7
11.7
RELIN
52.746.245.645.645.747.249.150.643.541.142.2
MERIDIN
112.4128.3125.5127.2127.2121.4115.4110.8136.3153.2155.3
BET AMOUT6.15.42.01.91.71.21.00.81.61.63.5
VELOUT
131.7134.9133.0127.5126.6125.2124.5124.2129.9146.3140.3
TOTALIN
335.8331.9324.5322.8322.7322.4322.1321.9319.3317.5317.9
TEMPRAT 1.000100000111
TANGIN
147.7133.7128.0129.9130.2131.2133.2134.9129.3133.7140.8
.990
.998
.000
.998
.998
.998
.998
.998
.000
.001
.002
VELOUT14.212.84.74.23.72.52.21.73.64.18.5
MERID MACH NOIN
0.3140.3610.3560.3630.3630.3460.3290.3160.3910.4440.450
D-FACT
0.5640.5160.4970.5230.5270.5270.5260.5240.4990.4410.483
OUT0.3650.3750.3740.3590.3560.3530.3510.3500.3680.4160.398
Err0.0.0.0.0.0.0.0.0.0.0.
LOSS COEFFTOT0.2540.2130.1230.1610.1650.1460.1170.0910.1200.1130.166
PROF00000000000
.254
.213
.123
.161
.165
.146
.117
.091
.120
.113
.166
TOTALIN
14.2114.1913.9013.8713.8613.7713.6813.6113.7914.0214.01
WHEELIN0.0.0.0.0.0.0.0.0.0.0.
MERIDVEL R1.1721.0511.0601.0020.9951.0321.0781.1210.9530.9550.903
PRESSRATIO0.9570.9640.9800.9730.9720.9760.9820.9860.9780.9760.963
SPEEDOUT0.0.0.0.0.0.0.0.0.0.0.
PEAK SSMACH NO
1.0190.9120.8710.8700.8690.8770.8920.9060.8250.7970.825
LOSS PARAMTOT0.0980.0800.0430.0530.0530.0470.0370.0280.0350.0290.041
PROF0.0980.0800.0430.0530.0530.0470.0370.0280.0350.0290.041
53
TABLE VHI. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(1) 70 Percent of design speed; reading number 988
RADIIRP
123456789
1011
IN23.91923.15221.55720.11419.87319.62919.38819.14717.59115.75615.273
OUT23.90923.45921.63620.26720.03819.80919.58319.35518.00416.23815.806
ABS VCLRP
1234567
89
1011
IN170.8175.2172.6176.4177.1177.5176.2173.2191.72!!. 3215.3
OUT152.4164.8168.2173.6174.7175.9176.5177.6191,2217.3218.1
ABS MACH NORP
t2345e789
10U
IN0.5020.5160.5090.5210.5220.5230.5180.5080.5660.6250.637
OUT0.4450.4840.4950.5120.5150.5180.5190.5230.5650.6440.645
ABSIN
17.116.115.217.118.519.622.023.922.627.629.5
RELIN
170.8175.2172.6176.4177.1177.5176.2173.2191.7211.3215.3
BET AMOUT
1.40.6
-2.2-2.4-2.1-2.1-1.5-1.2-2.3-0.9
1.2
VELOUT
152.4164.8168.2173.6174.7175.9176.5177.6191.2217.3218.1
REL MACH NOIN
0.5020.5160.5090.5210.5220.5230.5180.5080.5660.6250.637
PERCENT INCIDENCERP
123456789
10U
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN-13.-13.-13.-12.-11.-10.-8.-6.-9.-7.-7.
22987869770
SS-19.6-19.6-20.3-19.2-18.1-17.2-15.0-13.2-16.1-14.0-13.3
OUT0.4450.4840.4950.5120.5150.5180.5190.5230.5650.6440.645
DEV
11.19.66.05.66.05.96.56.85.77.29.4
RELIN
17.116.115.217.118.519.622.023.922.627.629.5
BET AMOUT1.40.6
-2.2-2.4-2.1-2.1-1.5-1.2-2.3-0.9
1.2
MERID VELIN
163.2168.3166.6168.6168.0167.2163.4158.3177.0187.1187.4
OUT152.4164.8168.0173.4174.6175.8176.4177.6191.1217.3218.0
TOTAL TEMPIN
302.7301.9300.8301.4301.7302.3303.3304.1303.9306.6307.7
RATIO1.0011.0011 . 0 0 01 . 0 0 01 . 0 0 00.9990.9980.9971 .0001 . 0 0 01.001
TANG VELIN
50.248.545.152.056.159.565.970.373.698.0
106.0
OUT3.71 .7
-6.5-7.4-6.3-6.3-4.6-3.6-7.6-3.34.5
MERID MACH NOIN
0.4800.4960.4910.4970.4960.4930.4800.4650.5220.5540.554
D-FACT
0.2130.1600.1300.1260.1270.1270.1240.1060.1230.0930.102
OUT0.4450.4840,4950.5110,5150.5180.5190.5220.5640.6440.645
Err0.0.0.0.0.0.0.0.0.0.0.
LOSS COEFFTOT0.1580.0620.0560.0560.0580.0520.040
-0.0050.0540.0380.108
PROF0.1580.0620.0560.0560.0580.0520.040
-0.0050.0540.0380.108
TOTALIN
11.4111.5311.5811.6811.7011.7111.6811.6212.0212.4212.55
WHEELIN0.0.0.0.0.0.0.0.0.0.0.
MERIDVEL R0.9340.9791 .0091.0291.0391.0511.0801.1211.0801.1611.163
PRESSRATIO0.9750.9900.9910.9910.9900.9910.9931.0010.9890.9910.974
SPEEDOUT0.0.0.0.0.0.0.0.0.0.0.
PEAK SSMACH NO
0.5020.5160.5090.5210.5220.5230.5180.5080.5660.6250.637
LOSS PARAMTOT0.0610.0240.0190.0180 .0190.0170.012
-0.0020.0160.0100.027
PROF0.0610.0240.0190.0180.0190.0170.012
-0.0020.0160 . 0 1 00.027
54
TABLE vm. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(m) 70 Percent of design speed; reading number 989
RADIIRP
123A56789
1011
IN23.91923.45221 .55720.11419.87319.62919.38819.14717.69115.75615.273
OUT23.90923.45921.63620.26720.03819.80919.58319.35518.00416.23815.806
ABS VELRP
123456789
10'.1
IN168.5170.6166.2167.7169.0170.2170.3167.9178.8198.6235.2
OUTU3.8151.3150.1152.0153.4154.4154.6154.6163.1184.4177.5
ABS MACH NORP
123A56789
1011
IN0.4890.4970.4860.4900.4940.4970.4960.4890.5230.5830.602
OUT0.4150.4390.4370.4420.4470.4490.4490.4490.4750.5380.516
ABSIN
24.323.723.025.026.327.429.230.928.932.634.3
RELIN
168.5170.6166.2167.7169.0170.2170.3167.9178.8198.6205.2
BET AMOUT2.42.1
-1.8-1.8-1.6-0.9-0.5-0.5-1.90.43.0
VELOUT
143.8151.3150.1152.0153.4154.4154.6154.6163.1184.4177.5
REL MACH NOIN
0.4890.4970.4860.4900.4940.4970.4960.4890.5230.5830.602
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN-6-.-5.-6.-4.-3.-3.-1.0.
-3.-2.-2.
05099041472
SS-12.4-11.9-12.4-11.3-10.2-9.3-7.7-6.3-9.8-9.0-8.5
OUT0.4150.4390.4370.4420.4470.4490.4490.4490.4750.5380.516
DEV
12.111.16.46.26.47.07.57.56.08.5
11.2
REL BETAMIN
24.323.7
23.025.026.327.4
29.230.928.932.634.3
MERIDIN
153.6156.2153.0151.9151.5151.2148.7144.1156.6167.3169.5
OUT2.42.1
-1.8-1.8-1.6-0.9-0.5-0.5-1.9
0.43.0
VELOUT
143.6151.2150.0151.9153.4154.4154.6154.6163.0184.4177.3
TOTAL TEMPIN
309.3307.7305.4305.6305.7306.4307.3307.8306.6308.7310.0
RATIO0.9981 .0000.9990.9990.9990.9990.9980.9970.9991.0021.002
TANG VELIN
69.368.765.070.974.878.383.186.286.4
107.0115.6
OUT6.15.7
-4.7-4.8-4.4-2.5-1.4-1.3-5.51.39.2
MERID MACH NOIN
0.4460.4550.4470.4440.4430.4410.4330.4190.4580.4910.497
D-FACT
0.2910.2530.2430.2400.2420.2430.2480.2400.2340.2060.261
OUT0.4150.4380.4360.4420.4460.4490.4490.4490.4750.5380.515
EFF
0.0.0.0.0.0.0.0.0.0.0.
LOSS COEFFTOT0.1070.0380.0430.0490.0470.0510.0520.0220.0440.0530.182
PROF0.1070.0380.0430.0490.0470.0510.0520.0220.0440.0530.182
TOTALIN
12.1812.2212.1812.2012.2212.2412.2412.1712.3612.7012.82
WHEELIN0.0.0.0.0.0.0.0.0.0.Q.
MERtDVEL R0.9350.9680.9801.0001.0121.0211.0401.0731.0411.1021 .046
PRESSRATIO0.9840.9940.9940.9930.9930.9920.9920.9970.9930.9890.961
SPEEDOUT0.0.0.0.0.0.0.0.0.0.0.
PEAK SSMACH MO
0.4890.4970.4860.4900.4940.4970.5080.5440.5230.5830.602
LOSS PARAMTOT0.0410.0150.0150.0160.0150.0160.0160.0070.013O.OU0.045
PROF0.0410.0150.0150.0160.0150.0160.0160.0070.0130.0140.045
55
TABLE Vm. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(n) 70 Percent of design speed; reading number 990
RAP!!RP
123A56789
1011
IN23.91923.45221 .55720. 1U19.87319.62919.38819.14717.69115.75615.273
OUT23.90923.45921 .63620.26720.03819.80919.58319.35518.00416.23815.806
ABS VELRP
123456789
10!1
IN164.7168.2159.2163.2164.9167.0163.6161.6170.6190.6196.8
OUT135.7142.6136.0137.4138.0137.8137.0136.4141.8160.8158.6
ABS MACH NORP
123456789
1011
IN0.4740.4860.4610.4730.4780.4840.4740.4680.4960.5560.575
OUT0.3880.4090.3920.3960.3980.3970.3950.3930.4090.4660.458
ABSIN
31.930.930.031.432.333.135.837.334.436.537.5
RELIN
164.7168.2159.2163.2164.9167.0163.6161.6170.6190.6196.8
BET AMOUT3.33.8
-0.30.30.51.00.90.8
-0.90.42.0
VELOUT
135.7142.6136.0137.4138.0137.8137.0136.4141.8160.8158.6
REL MACH NOIN
0.4740.4860.4610.4730.4780.4840.4740.4680.4960.5560.575
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN1.1.1.1.2.2.5.6.2.1.1.
66051825110
SS-4.8-4.8-5.4-4.9-4.3-3.6-1.2
0.1-4.3-5.2-5.3
OUT0.3880.4090.3920.3960.3980.3970.3950.3930.4090.4660.458
DEV
13.012.87.98.38.59.08.88.87.18.5
10.2
REL BETAMIN
31.930.930.031.432.333.135.837.334.436.537.5
MERIDIN
139.9144.4137.8139.3139.5139.8132.8128.6140.8153.3156.1
OUT3.33.8
-0.30.30.51.00.90.8
-0.90.42.0
VELOUT
135.5142. 2136.0137.4138.0137.8137.0136.4141.8160.8158.5
TOTAL TEMPIN
314.5312.2308.9309.'309.3309.6310.0310.2308.8310.0310.5
RATIO0.9971.0000.9990.9980.9980.9980.9970.9970.9990.9991.000
TANG VELIN
87.086.379.685.188.091.395.798.096.3
113.2119.8
OUT7.99.4
-0.80.61.22.42.01.9
-2.21.05.4
MERID MACH NOIN
0.4020.4170.3990.4040.4050.4060.3850.3720.4090.4480.456
D-rACT
0.3620.3260.3220.3260.3320.3430.3410.3390.3330.3050.336
OUT0.3870.4080.3920.3960.3980.3970.3950.3930.4090.4660.458
EFT
0.0.0. '0.0.0.0.0.0.0.0.
LOSS COEFFTOT0.0820.0440.0370.0550.0620.0900.0600.0380.0540.0670.133
PROF0.0820.0440.0370.0550.0620.0900.0600.0380.0540.0670.133
TOTALIN
12.6112.6912.5212.5512.5712.6112.5312.^712.5712.9012.95
WHEELIN0.0.0.0.0.0.0.0.0.0.0,
MERIOVEL R0.9690.9850.9870.9860.9900.9861.0321.0611.0071.0491.015
PRESSRATIO0.9880.9930.9950.9920.9910.9870.9910.9950.9920.9870.973
SPEEDOUT
0.0.0.0.0.0.0.0.0.0.0.
PEAK SSMACH NO
0.5870.5910.5350.5570.5760.5960.6260.6390.5970.6550.679
LOSS PARAMTOT0.0310.0170.0130.0180.0200.0290.0190.0120.0150.0170.033
PROF0.0310.0170.0130.0180.0200.0290.0190.0120.0150.0170.033
56
TABLE Vm. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(o) 70 Percent of design speed; reading number 991
RADIIRP
123456789
1011
IN23.91923.45221 .55720.11419.87319.62919.38819.14717.59115.75615.273
OUT23.90923.45921.63620.26720.03819.80919.58319.35518.00416.23815.806
ABS VELRP
125456/
89
1011
IN158.9164.8157.7160.6161.6159.8157.0156.1164.8184.1187.1
OUT124.1131.1125.7124.3123.7122.4121.9121.0125.9143.3140.9
ABS MACH NORP
1 •23456789
1011
•IN0.4540.4750.4540.4640.4660.4610.4520.4500.4770.5360.545
OUT0.3520.3730.3600.3560.3540.3500.3490.3460.3610.4120.405
ABSIN
38.936.435.737.036.938.441.543.139.639.140.2
RELIN
158.9164.8157.7160.6161.6159.8157.0156.1164.8184.1187.1
BETAMOUT4,2
- 3.80.31.61.51.51.31.20.61.02.7
VELOUT
124.1131.1125.7124.3123.7122.4121.9121.0125.9143.3140.9
REL MACH NOIN
0.4540.4730.4540.4640.4660.4610.4520.4500.4770.5360.545
PERCENT INCIDENCERP
123456789
10It
SPAN5.00
10.0030.00-»5.0047.5050.0052.5055.0070.0090.0095.00
MEAN8.7.6.7.6.8.
11.12.7.3.3.
61718103477
SS2.20.70.20.70.41.74.65.91.0
-2.6-2.6
. OUT0.3520.3730.3600.3560.3540.3500.3490.3460.3610.4120.405
OEV
13.912.88.59.69.69.49.39.28.69.1
II. a
REL BETAMIN
38.936.435.737.036.938.441.543.139.639.140.2
MERIDIN
123.6132.8128.1128.3129.2125.2117.5114.0126.9142.9142.9
OUT4.23.80.31.61.51.51.31.20.61.02.7
VELOUT
123.7130.8(25.7124.3123.7122.4121.8121.0125.9143.3140.7
TOTAL TEMPIN
318.0316.3312.6311.7311.8311.8311.9312.1310.6310.8310.9
RATIO0.9981 .0000.9980.9990.9980.9980.9970.9971.0001.0001.001
TANG VELIN
99.997.792.096.797.199.3
104.1106.6105.1116.1120.8
OUT9.08.70.73.53.33.12.82.51.42.46.8
MERID MACH NOIN
0.3530.3810.3690.3700.3730.3610.3390.3280.3670.4160.416
D-rACT
0.4400.4090.4050.4140.4200.4250.4250.4310.4150.3770.396
OUT0.3510.3720.3600.3560.3540.3500.3490.3460.3610.4120.404
EFT
0.0.0.0.0.0.0.0.0.0.o.
LOSS COEFFTOT0.1060.0970.0710.0940.1080.1010.0710.0520.0690.0830.136
PROF0.1060.0970.0710.0940.1080.1010.0710.0520.0690.0830.136
TOTALIN
12.8412.9712.7912.7912.7912.7512.6812.6312.7112.9912.97
HHEELIN0.0.0.0.0.0.0.0.0.0.0.
MERIDVEL R1.0010.9850.9810.9690.9570.9771.0371.0610.9921.0030.985
PRESSRATIO0.9860.9860.9910.9870.9850.9860.9910.9930.9900.9850.975
SPEEDOUT
0.0.0.0.0.0.0".0.0.0.0.
PEA< SSMACH NO
0,6760.6690.6250.6430.6420.6550.6870.7030.6660.6860.701
LOSS PARAMTOT0.0410.0370.0250.0310.0350.0320.0220.0160.0200.0210.034
PROF0.0410.0370.0250.0310.0350.0320.0220.0160.0200.0210.034
57
TABLE Vm. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(p) 70 Percent of design speed; reading number 992
R A D I I ABS BETAM REL BETAM TOTAL TEMP TOTAL PRESS*f> ;\ G'JT IN OUT IN OUT IN R A T I O IN R A T I O
• 23.919 23.939 56.4 6.6 56.4 6.6 326.6 0.987 13.26 0.9592 25.452 23.459 49.2 6.0 49.2 6.0 322.8 0.994 13.09 0.9753456••
89
' 311
R°123456™
89
1011
21.55723. '1410.873i?.62910.38810.147
17.69115.75515.273
ABSIN
166.4160.3157.1159.2159.3157.6154.4153.7161.6180.5185.0
2L63623.26723 .33819.83919.58319.35518.00416.23815.836
VtLO'JT
115.6118.7118.9115.9115.1114.0113.5112.8116.4132.6131.6
ABS MACH NORP
123456789
1011
IN0.4690.4540.4510.4580.4580.4530.4440.4420.4660.5240.538
OUT0.3250.3340.3380.3300.3280.3250.3230.3210.3320.3800.377
43.741 .441.943.245.947.743.743.841 .7
RELIN
166.4160.3157.1159.2159.3157.6154.4153.7161.6180.5185.0
1 "J*
2^32.61.81.51.51.21.73.3
VELCUT
115.6118.7118.9115.9115.1114.0113.5112.8116.4132.6131.6
REL MACH NOIN
0.4690.4540.4510.4580.4580.4530.4440.4420.4660.5240.538
PERCENT INCIDENCERP
123456789
1011
SPAN5.00
10.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN26.19.11.11.11.12.15.16.11.5.5.
19647949442
SS19.713.55.25.05.46.59.0
10.55.1
-0.9-1.1
OUT0.3250.3340.3380.3300.3280.3250.3230.3210.3320.3800.377
DEV
16.315.09.9
10.310.69.89.69.49.19.8
11.5
40.741 .441.943.245.947.743.740.841.7
MERIDIN
92.1104.8119.2119.5118.6114.9107.4103.5116.9136.6138.2
1.72.32.61.81.61.51.21.73.3
VELOUT
114.9118.1118.8115.8115.0113.9113.4112.7116.4132.5131.4
314.7313.4313.4313.4313.3313.3311.9311.2311.3
TANGIN
138.6121.3102.4105.2106.3107.9110.9113.7111.6117.9123.0
1 .0000.9990.9990.9990.9980.9981.0001 .0011 . 0 0 1
VELOUT13.312.33.64.75.33.63.22.92.43.97.5
MERID MACH NOIN
0.2600.2970.3420.3440.3410.3300.3090.2970.3370.3970.402
D-FACT
0.5960.5170.4620.4770.4810.4860.4830.4890.4720.4250.441
OUT0.3220.3330.3380.3300.3280.3250.3230.3210.3320.3800.377
EFF
0.0.0.0.0.0.0.0.0.0.0.
LOSS COEFFTOT0.2920.1910.0990.1260.1280.1210.0800.0690.0760.1020.162
PROF0.2920.1910.0990.1260.1280.1210.0800.0690.0760.1020.162
12.9212.9012.8912.8412.7612.7312.7713.0513.05
WHEELIN0.0.0.0.0.0.0.0.0.0.0.
MERIDVEL R1.2481.1270.9970.9690.9690.9921.0561.0890.9950.9700.951
0.9870.9830.9830.9840.9900.9910.9890.9830.971
SPEEDOUT
0.0.0.0.0.0.0.0.0.0.0.
PEA< ssMACH NO
0.9850.8420.6970.7030.7080.7180.7400.7600.7160.7030.721
LOSS PARAMTOT0.1120.0720.0340.0410.0410.0380.0250.0210.0220.0260.040
PROF0.1120.0720.0340.0410.0410.0380.0250.0210.0220.0260.040
58
TABLE Vm. - Continued. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(q) 60 Percent of design speed; reading number 993
RADIIRP1234567891011
IN23.91923.45221 .55720. 11419.87319.62919.38819. U717.69115.75515.273
OUT23.90923.45921.63520.26720.03819.80919.58319.35518.00416.23815.806
ABS VELRP123A567891011
IN142.4136.9132.4134.7134.6132.9131.1129.9137.1151.9156.9
OUT99.0101.4101.098.697.996.395.795.398.6113.4111.8
ABS MACH NORP123456789
1011
IN0.4060.3920.3820.3900.3890.3840.3790.3750.3970.4430.458
OUT0.2810.2890.2900.2840.2810.2770.2750.2740.2840.3270.323
ABSIN
55.849.240.240.741.343.245.447.644.340.641.4
RELIN
142.4136.9132.4134.7134.6132.9131.1129.9137.1151.9156.9
BET AMOUT7.87.92.02.82.62.22.01.91.81.93.7
VELOUT99.0101.4101.098.697.996.395.795.398.6113.4111.8
REL MACH NOIN
0.4060.3920.3820.3900.3890.3840.3790.3750.3970.4430.458
PERCENT INCIDENCERP
123i567891011
SPAN5.0010.0030.0045.0047.5050.0052.5055.0070.0090.0095.00
MEAN25.519.11.10.11.12.14.16.12.5.4.
9272988029
SS19.113.54.74.34.86.58.410.45.7
-1.1-1.4
OUT.0.2810.2890.2900.2840.2810.2770.2750.2740.2840.3270.323
DEV
17.516.910.210.810.610.210.09.99.710.011.9
REL BETAMIN
55.8-49.240.240.741.343.245.447.644.340.641.4
MERIDIN
80.189.4101.2102.2101.196.992.187.698.1115.4117.8
OUT7.87.92.02.82.62.22.01.91.81.93.7
VELOUT98.1100.4101.098.597.896.295.795.298.5113.3111.6
TOTAL TEMPIN
316.2313.4307.2306.5306.3306.3306.2306.3305.4304.5304.7
RATIO0.9900.9951.0000.9990.9990.9990.9990.9980.9991.0011.001
TANG VELIN
117.7103.685.587.888.991.093.395.995.798.8103.7
OUT13.414.03.54.94.43.83.43.23.13.77.2
MERID MACH NOIN
0.2280.2560.2920.2960.2920.2800.2660.2530.2840.3360.344
D-FACT
0.5870.5070.4520.4670.4740.4830.4840.4870.4730.4110.437
OUT0.2790.2860.2900.2830.2810.2770.2750.2740.2840.3270.322
EFF
0.0.0.0.0.0.0.0.0.0.Q.
LOSS COEFFTOT0.3040.2080.1000.1280.1320.1230.0970.0730.0870.0850.158
PROF0.3040.2080.1000.1280.1320.1230.0970.0730.0870.0850.158
TOTALIN12.3712.2612.1012.0912.0812.0412.0011.9612.0012.1712.19
WHEELIN0.0.0.0.0.0.0.0.0.0.0.
MERIOVEL R1.2261.1230.9980.9640.9680.9941.0391.0871.0040.9820.947
PRESSRATIO0.9670.9790.9900.9870.9870.9880.99k0.9930.9910.9890.979
SPEEDOUT0.0.0.0.0.0.0.0.0.0.0.
PEAK SSMACH NO0,8430.7260.5850.5890.5950.6090.6260.6450.6190.5910.608
LOSS PARAMTOT0.1160.0780.0350.0420.0430.0390.0300.0230.0250.0220.039
PROF0.1160.0780.0350.0420.0430.0390.0300.0230.0250.0220.039
59
TABLE - Concluded. BLADE-ELEMENT DATA AT BLADE EDGES FOR STATOR 4
(r) 50 Percent of design speed; reading number 994
R A D I IRP
125456789
1011
IN23.91S23. 45221.55720.H415.87319.62919.38819.14717.69115.75515.273
OUT2323212020191919181615
.909
.459
.636
.267
.038
.809
.583
.355
.004
.238
.806
ABS YD.*P
123456789
10\ \
RP123456789
1011
I N119.2114.0110.3H2.0112.0111.2109.7158.2114.5127.0129.6
ABSIN
0.3430.3290.3200.3260.3250.3230.3190.3140.3330.3710.379
O'JT83.385.184.281.881.380.279.979.182.59*.992.4
MACH NO
00000000000
PERCENTRP
123456789
1011
SPAN5.00
10 .0030.0045.0047.5050.0052.5055.0070.0090.0095.00
OUT.239.245.244.237.235.232.231.229.239.276.268
ABSI N
54.949.439.341.241.743.446.047.744.340.541.5
RELI N
119.2114.0110 .3112.0112.01 1 1 . 2109.7108.2114.5127.0129.6
BETAMOUT8.07.82.03.22.72.22.72.12.21.93.8
'VELOUT83.385.184.281.881.380.279.979.182.594.992.4
REL MACH NOI N
0.3430.3290.3200.3260.3250.3230.3190.3140.3330.3710.379
INCIDENCEMEAN24.520.210.311.311.613.115.416.912.15.25.0
SS18.113.83.84.95.26.79.0
10.55.7
-1.1--1.3
OUT0.2390.2450.2440.2370.2350.2320.2310.2290.2390.2760.268
DEV
17.716.810.211.210.710.210.710.110.110 .012.0
REL BETAMIN
•54.949.439.341.241.743.446.047.744.340.541.5
MERIDI N
68.774.185.384.283.680.776.272.981.996.697.1
OUT8.07.82.03.22.72.22.72.12.21.93.8
VELOUT82.584.384.281.781.280.179.879.182.494.992.2
TOTAL TEMPIN
307.9305.8301.5300.8300.7300.7300.9300.8300.3299.6299.5
R A T I O0.9920.9961.0001.0000.9990.9990.9980.9980.9991.0011 .001
TANG VELIN
97.586.669.873.874.576.578.880.080.082.585.9
OUT11.611.62.94.63.83.03.72.93.23.26.1
M E R I D MACH NOI N
0.1970.2140.2480.2450.2430.2350.2210.2120.2380.2820.284
D-FACT
0.5790.5030.4470.4700.4760.4880.4850.4890.4700.4100.437
OUT0.2370.2420.2430.2360.2350.2320.2310.2290.2390.2750.267
EFT
0.0.0.0.0.0.0.0.0.0.0.
~
LOSS COEFFTOT0.3090.1950.0900.1310.1340.1320.1070.0800.0890.0830.149
PROF0.3090.1950.0900.1310.1340.1320.1070.0800.0890.0830.149
TOTALIN
11.6811.5811.4711.4711.4611.45.11.4211.3911.4211.5311.53
WHEELIN0.0.0.0.0.0.0.0.0.0.0.
MERIDVEL R1.2021.1370.9870.9700.9710.9921.0471.0851.0060.9830.950
PRESSRATIO0.9760.9860.9940.9910.9910.9910.9930.9950.9930.9920.986
SPEEDOUT
0.0.0.0.0.0.0.0.0.0.0.
PEAK SSMACH NO
0.7010.6120.4800.4990.5020.5150.5320.5410.5190.4940.505.
LOSS PARAMTOT0.1180.0730.0320.0430.0430.0420.0340.0250.0250.0210.037
PROF0.1180.0730.0320.0430.0430.0420.0340.0250.0250.0210.037
60
Station 1Station 2
Station 3
„- 16-
Flow path coordinates
Axial distance,2, cm
-35. 560-30.480-25.400-20.320-15. 240-1£700-10. 160-7.620-5.080
a-2.54004.064
a5.0807.620
10. 973a!2. 700
15.24017. 78020. 320
Radius,
Inner
7.3027.3027.4938.2559.1449.589
10.09610. 51511.04911.74712.66813.97014.33614.73215.240
!
r, cm
Outer
25.400
25.33624.63824.46024.384
I Measuring station.
-24 -16 -8 0 8 16 24Axial distance from rotor hub at blade leading edge, Z, cm
Figure 1. - Flow path for stage showing axial location of instrumentation.
-Inlet throttle valves-Orifice
Flow -*im ii
-*+.... A IMIZI3sy\Nfc. T
-^
Drivemotor—.
Atmospheric exhauster piping
CD-10916-11
Figure 2. -Test facility.
61
62
,7-Two null-balancing/ pressure taps for
flow angle measurement
C-69-1280
(a) Combination total pressure, total temperature,and flowangle probe (double barrel).
(b) Static pressure probe.
Figure 5. - Survey probes.
63
47°30'
• Wall static pressure tap-G Combination probe_D Wedge static pressure probe
Station 1
32°30'64°0'
Station 2 Station 3
Figure 6. - Circumferential locations of measurements (looking downstream;clockwise rotation).
64
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90 NASA-Langley, 1973 1 E~7205
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