aero-physics division briefing for edgar … division briefing for " edgar m. cortright ......
TRANSCRIPT
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AERO-PHYSICS DIVISION BRIEFING
FOR "
EDGAR M. CORTRIGHT
JUNE 24, 1968
.• J._.r......:._..Li. ......... ~~.- ... -..1...1"
PEN00059c ' .,
NASA L- 64-1000
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OVERVIEW OF ORGANIZATION AND
JOHN v. B EC KER
PROGRAMS
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.. -~----:------~------------- ----
r--Hypersonic
Fluid :Mechanics
Branch of.
-I Reentry Physics Branch
24 Res. Prof.
-- --~------ - - --- --- --~--~-
AERO - PHYSICS DIVISION
~.--
Division Office
J. V. Becker, C h hit E. S. Love, Asst. Ch.
l. I. Turner, Asst. Ch.
I i
I I Hypersonic Vehicle
Aerodynamics' Research Branch Branch
II Res. Prof. 18 Res. Prof. 29 Res. Pr M. H. Bert ram .R. L Trimpi W. J. Nelson C. H. McLellan
,TOTAL RESEARCH PROFESS IONAlS -Doctors - 9 Masters - 49 Bachelors - 71
: (NCR Associates, not included above - 7) , Supporting Professionals -. Non-professionals -
TOTAL
129
15 23
T6-7 -
0' -----------------------
o •• ... .0 o.
I I Hypersonic Magneto-Propulsion Plasma-
Branch Dynamics Branch
12 Res. Prof. 32 Res. Prof. J. R. Henry M~· C. Ellis, Jr.
('
Res. Prof.
20
15
10" .-""-x -2, K-3 IOO-Series A C
M . 2 Cont. Study Missiles
Boost Glide"
APD CONFIGURATION RESEARCH
\ I. I I 1-
YEAR
______ TOTAL ~ ___
Entry,
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APD PROPULSION AERODY~{AMICS
Res. Prof.
40
30
20 Superson ic Compr, Compr. &- Tu rb. Aero."",
---"--~"'-·'·· __ --:::;;;;,.·-;;:.cc·--.:,c-:--""=';'-:: ,---- ,/' I nternal Flow""'"
10 -
__________ /S. S. Inlet M<3
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L
/HYP. Inlet _~ NOZ~les. Etc.
, /HRE
.,~~_.L_1_L,~~:-=-c~mbU:.~ 6065 70
YEAR
(
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APe FLUID MECHANICS
~ 777
1t ·8 Men'
1: I
., Transon ic Flows,
Airfoils
/'W /. ~/7///7////'/77r77J7~ 'Forces~ Pressures / ~ _/ He~tlng, for
-.~.......,..... ---'. ~"'-. ~:..- - ,;mn1e 'hanl"\s .. "'llIlpl .III .PG ..
<ZVJ7JZzZ@Zz?Z7-c 2 7777/ ~ <c:z 7 777
, , , , Z ? % ZV/7zz ? ZZ27/T~
Blunt Nose Heat Transfer
~ow Density.
Flowfields
Z7ZZZZ7IZW~ Viscous Interaction : Lam inar B. L.
. 27/§/2Z?? 2 2 ? ? z Transition .
?/ / 7 7 7 7 2 Z Z ? ? Z ? ? ? ? z~ Turpuient B. L.
~, , z ZZ7Z22:::t', , , , ~
~"'/"'7'/~~-r-r--r-. Jets
Plasma Sheath
'~ 'M.P.O. Aeeei.
~~.P.D. ~'HotGaS
• ; ~ Radiation
, I. '. I I I I '.' , I , , I I , I ' .. , , , ,
1947 49 51 53 55 57, 59 '. 61 6365 67 1969 I
Year , . '.
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APD CONTRIBUTIONS
(Since 1958)
Delta wings in hyperson ic flow - pioneering investigations of flow field shock detachment 'phenomena, heating, friction. ...... .
Helium tunnel development.
Fluid mechanics of secondary, jets.
Development of arc tunnel for fluid mechanics research - rotary arc heateraccelerator.
Hypersonic turbulent boundary-layer investigations - first precision research on fri'ction, heating, wall-cooling.
Original concept, theory, design and development of expansion tube.
Theory for shock-tube boundary-layer attenuation effects.
Original contributions to analysis of hot-gas radiation phenomena.
Development of J x B linear accelerator .
. Reentry communications blackout - original theory and experiments, first . quantitative evaluation of signal loss, analytical frameworl< for RAM
fI ight projects. .
Hall accelerator and MPD arc - diagnostics and evaluations including studies of instabilities and turbulence.
Proposal for and contributions to Barium cloud geomagnetospheric experiment •.
I~
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APD CONTRIBUTIONS (CONTINUED)
Development of magnetic compression device for identification spectral Ilines previously seen only in sun's corona.
X-20 (Dyna Soar) configuration development, aerodynamics, heating.
First comprehensive investigation of realistic hypersonic cruise vehicle configurations.
Lifting capsules for planetary probes - concept, analysis of weight advantages, and mission implications.
Development, promotion, and -support of the HRE Project.
Supersonic mixing research - improved correlation formula.
- First hypersonic inlet studies.
Development of -HL -10 manned LID"'" I entry veh icle.
Extensive operational and vehicle analyses of advanced entry systems including; high LID, decoupled modes, propulsive lift, hypersonic aerodynamic e~aluations-, unmanned systems.
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APD CONTRIBUTIONS (Since 1958)
Developmental investigations for specific
pro j e c t s (15 per c en t 0 f A PO r e se arc h
rna n power)
24 DOD 33 NA SA 57 TOTAL
.-" .
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AP D Oi37 PROF J i !
APD TECHNICAL INFORMATION OUTPUT
(DATA SOURCE RESEARCH REPORTS DIV. FOR FY 1967)
NASAREPTS. , ARTICLES, " PRESENTATIONS AND SPEECHES
39.7 22.3 40.7
CENTE~ (845 PROF J (7 RES. DIV J
224 50.5 194.6
I
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UNPUBLISHED MATERIAL NOT INCLUDED: WORKING PAPERS CONTRACTOR"S PROGRESS
REPORTS, AND SO FORTH
PUBL. DOC. PER MAN'
0.75
.55
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OTHER INDEXES OF APD TECHNICAL VITALITY
CURRENT M'EMBERSH I PS ON MAJOR TECHNICAL COMMITTEES:
National Professional Societies 8
NASA Research Advisory Subcommittees 4
NASA/DOD, NASA/USAF 5 (2 Chairmen)
NASA Space Science Subcommittee I
NASA I ntercenter Program, or Steering " Committee'
LRC Long-Term Committee
ANN UAl TECHN I CAL V IS ITOR S (1967)
REQUESTS OF OTHER AGENCIES FOR APD CONSULTANTS
TOTAL
FOREIGN TECHNICAL PRESENTATIONS
NATIONAL MEETING SESSION CHAIRMAN OR PANEL MEMBER (1967)
3 (I Chairman)
361
33 .',' .
3/VR,
4
/
RESEARCH RESPONS (B (L1TIES OF THE BRANCHES
-~----------- -
.. J .
HYPERSONIC FLUID MECHANICS BRANCH
MITCHEL H. BERTRAM
....•. _-_._ .. -... _ ... - ... _ ... -.............. -.. - ........ -- ...... - .... - .. _._-_ .. __ ....... __ ._ .. _-._ .. ---_ .............. _._. .. .... -... _.. .. .... .,.. .... ..
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F'L(M ANALYSIS SECTION (ART HENDERSON)
APPLIED FLUID MECHANICS SECTION (BOB STE:RRl!.:rT)
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HYPERSONIC FLUID MECHANICS BRANCH
B.S.
2
5
', .. ~ ,:'.
M.S.
3+ J.
:5+2
Ph.D
1* + 2
.........
other "Total
•• _-- .9
--_.-,/
22-INCllHELIUM M ... 20 ,and 40
20 INCH HYPERsora ,1
TUNNEL " M= 6 and 8.5
HIGH TEMPERNruRE FWID MECHANICS SECTION
(BmL BMl'RIGHT)
......... : 1** 11 FOUR FOOT HYPERSO C .ARC TUl\ll'l11'L
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* NAS T:&~SEARCH ASSOCIATE: ** ENGINEERING TECHNICIAN'
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" M=12to18
30 (29 permanent)
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FLUID MECHANICS AND BASIC AERODYNAMICS
, CONFIGURATIo.i\rS
.... , .' . < .,', ,-
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.' ]'ACILITY DEVELOPMENT I " : OPERATIONS AND ' .,' " INSTRUMENTATION ,
;.
; ....
HYPERSONIC FLUID MECHANICS BRANCH
DISTRIBUTION OF RESEARCH
FLOW ANALYSIS APPLIED FLUID SECTION MECHANICS, ,SECTION
t .',
HIGH Tn1PERATURE FLUID MECHANI CS Sl!:CTION
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18% 28% "
,1~' 2%
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HYPERSONIC FLUID MECHANICS BRANcn . CURRENT RESEARCH
CONFIGURATIONS
HYPERSONIC CRUISE AND HIGH tiD ENTRY
BASIC AERODYNAMICS
FLCM FIELD ,ABOUT 6. WINGS INTERFERING FLCMS OPTIMIZATION
FLUID MECHANICS
TRANSITION TURWLENT BOUNDARY LAYER FUNDAMENl'AL GAS l''LOW STUDIES
Low Density High Enthalpy
INLET STARTING
IMPROVEMENT IN SIMULATION TECHNIQUES
RCYrARY ARC
it' . L 4 ! '''",
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HYPERSONIC FLUID MECHANICS BRANCH
WHAT IS· THE PROBLEM WITH DELTA WINGS IN HYPERSONIC FLOW ? ,
PREVIOUS DATA AT TOO LOW REYNOLDS NUMBERS (MOSTLY LAMINAR) HIGH REYNOLDS NUMBER CASE Nor TREATED (MOSTLY TURBULENT)
'~.,:,.", ',,,
COMPRESSION SURFACE TREATED EXTENSIVELY FOR SHARP SLENDER WINGS BUT LEE SIDE AND OVERALL FLOW FIELD GIVEN ONLY CURSORY TREATMENT... MINIMAL I<NOWLEOOE OF VORTEX SYSTEM ON UPPER SURFACE AT LOW ANGLES OF ATTACK
MOSTLY FLAT SURFACES TREATED -- LITTLE CONSIDEXL~TION OF PRACTICAL CROSS-SECTION SHAPES EXCEPl' FOR THICK SLABLIKE WINGS
FLCM ON WING·
SHOCK ~_~~
~" .
..
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AERO-PHYSICS DIVISION
TRANSITION STUDIES
CONVENTIONAL TESTS IN WIND TUNNELS HAVE BEEN MOSTLY CONCERNED WITH MODEL VARIABLES
('" '.
CORRELATION OF SUCH INFORMATION FROM SIMPLE SHAPES IS BEING DONE TO ANSWER IMMEDIATE NEEDS
PRESENT EMPHASIS IS, TO INVESTIGATE EFFEaI' OF ENVIRONMENTAL FACTORS IN WIND TUNNELS
FLIGHT TEST IS USED TO PROVIDE A BASIS FOR COMPARISON - REENTRY F HAD TRANSITION DETERMINATION AS A. SECONDARY BUT IMPORTANT OBJECTIVE OF A CLEAN EXPERIMENT
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AERO-PHYSICS DIVISION
C(JRR£NT TURBVLcNT !3oUNO/lRY L.A YE"R
I £ X ,PEA' / IVIENT/IL I I I
11/<;/-1 REYNOLDS NUM8eR
WilLI-
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WIU.L.
CORNER R.oW
PEI..T/I WINt;
ItND ,e-,RP
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7H£CJR£TICAL I ,
AlUM ER.I UU.
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SOLurlON
INTE<;RRt..
COMPRESS.
SOLt/rIO'"
eVI1LUf-l.rfON of
pOrlL#/?OS£N TYpe. /.1PP/2O,4C1!
I GV/lLUflrION OF COMPRESSIBLE
7RR/l/3F0;1MII TldN
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WALL TEMPERATURE EFFECT ON TURBULENT HEATING .
SHARP FLAT PLATE; Moo =6
rMONAGHAN T' L "X rSOMMER a SHORT Tl
.6 •. ~ECKERT T' . ,··:t~ MODIFIED SPALDING B CHI ~~
AL ~~~ ••••••••• ~I ~~~'-&......... .~
.-.... -~-___ - - --rr .... -:::- - __ . ---...; :-:;;;;;-
L "'C'~;~;~ER B C~~\-HAN-K~-~'-"" .2r S Pr fL r
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~ ~~~ ----..~"""~(-,,' ~. - .-...... -.
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REENTRY PHYSICS BRANCH
ROBERT L. TRIMPI
- .- - .- --~ ~: ~'. ~-'- -- - ---:--:---- --:..:---
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REENTRY PHYSICS BRANCH RESEARCH AREA
~ Investigation of flow phenomena associated with high speed
flight in any planetary atmosphere
_ Primary: Radiative and convective heating
_ Secondary: Pressures, ·forces, stability, configurations
tt Hyperbolic speeds (principal effort)
- Planetary probes
• 50.000 fps Earth Reentry
- Apollo (Gemini, Mercury)
- (Fire)
at Suborbital speeds (smaller effort)
Reentry F
,
• Hypersonic transport, ramjet inlets. AICI3M, etc.
tt Wide range of Mach number, Reynolds number, total enthalpy,
and body shapes
.. Facility development to encompass above flight regimes
,
"
-~-.----'-~------..
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REENTRY PHYSICS BRANCH RESEARCH PHILOSOPHY
• To maintain. in the area of high speed flight, a flexiule
theoretical and experimental research capability which encompasses
the range from very advanced research problems down to those of
the "crash or brush fire" type.
- Example: Apo110-or1ented research
1960 early advanced studies of idealized shapes
1963 study of problems associated with realistic spacecraft - ~
(protuberances. cut-outs. reaction jet interference) " ,
. ~
1966 quick fix of heating problem ahead of umbilical on Apollo 201
, '
-:"";
---_._----..-, .. -.-'-
~
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REENTRY PHYSICS BRANCH RESOURCES '4
PH.D. t~S B Fad 1 i ties
Reentry Physics Branch Office 0 2 5 (CDC 6600)
Hyperveloc1ty Physics Section 0 3 1 HGRRF Expansion Tube (J. Jones) Pilot Expansion Tube
GIS Physics Section 1+2 1+1 0 HGRRF Shock Tube (\~. 01 s tad) 3.8 Inch Shock Tube
Gas Dynamics Section 0+1 4 5 MaB Variable Density (I. Beckwith) M-6 High Reynolds No.
Hypersonic N2 Tunnel CF4 Tunnel
Special Projects Section (F. Smith)
0 1+1 2 Hot Shot Tunnel
~
Totals m Ti+'2' ". "I
r'( \, Scientists 4 12 B
Mathematicians 0 1 5
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MYPERSONIC AERO DYNAM I C S BRANCH
WILLIAM J. NELSON
~:·:,~.'I"T;" ;:: .:·I~'~"·'''''·-~ " ....
\
HYPERSONIC AERODYNAMICS BRANCH
PROFE SS I ONAl PROGRAM MANPOWER
I •. Advanced Concepts for Manned Transport to Earth Orbit & Return 6.0
• ~eusable. System • Recovery Mode • Configurati6n Research
I I. Boundary-Layer Research 3.0 .,
• Problems Identified through I. • Correlation Studies
I I I. Miscellaneous 1.5
IV. Facility Support 1.5
'1]'.,
",' " TOTAL 12.0
........
. )
ADVANCE CONCEPTS FOR. MANNED TRANSPORT TO EARTH ORBIT AND RETURN
REUSABLE SYSTEMS
. '. MODULAR (GEMINI, APOLLO TYPE MATING)
-INTEGRATED LAUNCH AND ,ENTRY VEHICLES ·~t~
HEAD-END TIP-STEERING TANK
ADVANCED CONCEPTS FOR MANNED TRANSPORT TO EARTH. ORBIT AND RETURN
RECOVERY MODES ."., .......
• Conventional Runway L~nding • Fixed Geometry (HL-IO) • Variable Geometry
• Rigid Wings • Semi-rigid Wings
• Decouple~ Landing
• Propulsive Lift
• Deployable Rotors
• Parawing and Sail chutes
"
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___ .. __ . __ ._.'._-- . I ------- ------------------ -. ---- --- ~ ------------- -_.. I ...... -.--.-.---------.--.---------.• -.----•• ------- .-~--.. - .• --- .• --------••• --.- .. -. -•.•.••. -- ---.
------ --- _._-
.(:~.~ I' ....... •
\
ADVANCED CONCEPTS FOR MANNED TRANSPORT TO EARTH ORBIT AND RETURN
, ~.' "
CONFI'GURATION RESEARCH • Low to Mo de rat e H yp e r son ~ c LID ( 0 • 5 ~ L ID ~ 1 • 5 )
- Technology generally available for desi'gn -- Interference and second-order effects
must be resolved through specific contiguration testing
• H i 9 h H y per son i c LID ( L ID ~ 3 )
~ Applicability of theory not generally
established
Interference effects unknown Stability requirementsnot,understood
- Viscous effects large and unpredictable,
, INFORMATION EXCHANGE PATTERN·
MSFC.
I
"P '" i· '.i t,\ I": ;:, ·····r ':.> t . I
NASA-USAF WORKING GROUP LIFTING ENTRY· "
l
AIAA TECH. CO~IIM. ENTRY VEH.
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5
FACILITIES FOR CONFIGURATION DEVELOPMENT
Ames 3.5·Foot
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7
LRC 8-Ft. H.T.S.T. (Proposecl
8
M 9
L RC ~3 I _. Inc h
Continuous FloVJ Tunnel
10 11
I Mod.)
12
DL-4
.Apo11o
HL-IO
VEHICLE RESEARCH BRANCH
CHARLES H. Me LELLAN
VEHICLE RESEARCH BRANCH
Charles H. McLellan
Studies of advanced aircraft, entry vehicles" and spacecraft and their missions. · '
c."' .. , .• 1'.
!-. .1 ( .. '
MI SS IONS SECTION
E. Brian Pritchard
Professional Staff - 5
Advanced 'studies of both atmosphere and space missions. .,
- .. ,. , "
HYPERSONIC AIRCRAFT SECTION
David E" Fetterman
Profess ional Staff - 12.
Study of completE~ integrated hypers nic aircraft and their, potential missions
.' .,i
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EARTH ENTRY AND PLANETARY MISSIONS "
EARTH ENTRY STUDIES (Current effort - 20 % )
• Orbital recovery
• Manned entry maneuvers
• low Reynolds number effects on entry 11<;
• Special landing- foot-print requirements
PLANETARY MISSION STUDIES (Current effort - 80 % )
• Manned planetary missions
• Use of gravity turns
• Unmanned missions to Mercury and the moons of Jupiter and Saturn
• Unmanned Mars mission
1973 TITAN - MARS MiniON CONTRIBUTION,S ,Current Effort - 80 ~/o of Professionals)
Mission Mode to Maximize Landed Payload
Term inal Descent Studies lifting Capsule Concept· Entry Scienc~ Instrumentation Studies
I ,.,' I I I
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W~.,
Mass-Enthalpy Probe Concept
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HYPERSON I C A IRCRAFT PROGRAM
. M = 6 to 8 Transport M = 8 - 12 Military Ve icle
Research Vehicle
SUPPORTING STUDIES
Mission Analysis Component Interference Studies
Scale Effect Theoretical Analysis
Exhaust Flow S'imula t i on and Integrat ion Aerodynamic Cooling System Studies
'!
Coordi nat ion with SRp.,
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STUDY OUTLINE
Air Force" ' ;I' MAD . " /
" /
, ~"-.. ~~."'-.'''.-•. ~ ~ /
" Mission Selection ., /' -----=r'----~or'YAnaiysiS .
Aerodynamics' 1-----1
Coordination with Hyperson i
Propulsion Bra ch
(all speed ranges) ~ 1------:::::0.,----"
W----:.....-tConfiguration Definition 1--______ --'
Experimental Studies M=O to cruise ?ther configurations
System Study Contract /
i _____
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,HYPERSONIC PROPULSION BRANCH
JOHN R. HENRY
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BRANCH <:.-, . "", 'I' .~. }.;"
(TOTAL 12 P ROFES SIONAlS) , I
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~(~~I . IN-HoustRESEARC~,' 'I ( , I
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, Propujsion:"f\erodynamlcs' , ,
Hypersonic, Inlets'f~ :'~;;:~~,:)' SupersohicMi~lng" "
2-D~ Coaxial, :,transverse , Noz~les '
I .
, . Propulsion Aerothermodynami¢$ .........., -. LJ'
Performance Prediction Ign it ion Theory Combustor Theory ,Piloted /Ign ltioh Experiment
! .
Administration. Special Probl~h1~~, ... facilities ·
!1'1 .' . ,
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PROF. M. s. Oeg. Completed In Progress
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1.0
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HYPERSONIC RAMJET ENGINE PROJ ECl
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Ass~ssment ,Contractor's 'Performance "
Proposals, .Results,Progress Plans for Engine Development. Technical literature Engine Design and Analysis
Experimental and Analytical support -Inlet - M 1114 and 6 Starting Experiments,
Boundary ,Layer Growth (Exp. and Anal. , Cycle. Analysis "~
Vitiation Effeds' Boundary layer .Predictions
"
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SUPPORT
Prof. , M. Completed
. ,
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4 2
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SUPERSONIC COMBUSTOR J
:<; -Fuel I njection and Mixing, '
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Coaxial and 2-D Mixing ..
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Transverse I njecti.Qn - " . . f ,.j
Empirical Design Method
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RELATIONSHIPS
NASA Headquarters, Aero Vehicles Division,
Propulsion Branch,' N. F.Rekos' (RAP)
··lewis -Hypersonic Propul'sion Section, E. A. lezberg,
Ames' -Air B'reathingProptllsion' Brahch; E. W. Perkins . '
Air Force 'Aero Propulsi'on ,labotatory, WPAFB
Private Organ izations
~. A. S.L. , '·U. A. C.:Research labs, G. E." ,
Marquardt"Republic, , General Dynamics,'
. Applied Physics laboratory, louisiana State
University, New York University, CETEC,
Nielsen Engineering and Research
NASA Research and Technology Advisory Subcommittee
on Air' Breathing Propulsion
AIAA Technical Committee on Air Breathing Propulsion
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PROBLEMS
Needed Research"
Scramjet Nozzle Aerodynamics .: ' " .
Fuel Injection, ,Mixing with Reaction' (Scramjet) , . . .'
. , ' Hypersonic Inlet Aerodynamics
New Equ ipment"·, .. ' ,.:' ...
Vitiated Heater for, Combustion Tests Moo '. 4 to 9
Arc Powered Heater for Combustion Tests , Moo • 8 to 12
Data Pick-up and Recording Units
Personnel Shortage
Combustion Experts
Hypersonic Inlet Experts
Computer
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MAGNETOPLASMADYNAMICS BRANCH'
MACON C. ELL I S, JR. " .
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MEASURES OF' HOW WELL WE ARE DOING
- Acceptance of our papers by journals
- References to our work
- Top-scientist visitors to our group
- Invitations to present papers and speak
- Heliance on us by NASA to review and monitor plasma research
- Our membership on committees
... Attainment of leading position in research on (a) Plasma accelerators
Jb) Entry communications (c) Numerical computer e~riments on plasmas (d) EM and ES forces on satellites (e) Plasma diagnosUcs including plasma spectroscopy
- Key contributions to projects, for example, ECHO I and IT, EXPLORER IX,TRAILBLAZER, MERCURY, GEMINI, APOLLO, FIRE, PACEMAKER, REENTRY F, RAM, PLANErrARY -PROBE studies
~-"',
NATURAL PLASMAS
M01'ION--GENERATED PLASMAS AND
DISTURBED NATURAL PLASMAS
MAN-MADE
PLASMAS
PLASMA AREAS OF COGNIZANCE TO NASA
- STELLAR PLASMAS - INTERPLANETARY AND INTERSTELLAR PLASMAS - INTERGALACTIC PLASMAS - PLANETOMAGNETOSPHERIC PLASMAS - PLASMA THEORY APPLICATIONS TO GRAVITATING STAR SYSTEMS
(-~-
/~ -
PLASMA EFFECTS GENERATED BY PLANETARY ENTRY OF SPACECRAFT ELECTROMAGNETIC AND ELECTROSTATIC FORCES ON SATELLITES;
SATELLITE WAKES CHARGES ON SATELLITES
I CONTROLLED THERMONUCLEAR FUSION ROCKETS GASEOUS-CORE FISSION ROCKETS
- PLASMA ACCELERATORS FOR
a. PROPULSION I
,{
[ \ '-..
h. c. d. e.
SOLAR-WIND SIMULATION HYPERSONIC AND ENTRY-FLIGHT SIMULATION FLUID-MECHANICAL POPULATION INVERSION BASIC PLASMA-PHYSICS STUDIES REQUIRING HI-VELOCITY PLASMA, etc.
- DEVICES FOR GENERATION OF InCH-TEMPERATURE PLASMAS FOR RADIATION STUDIES
- MHD-POWER GENERATORS - PLASMA DIODES FOR THERMIONIC POWER CONVERSION - GASEOUS LASERS AND OTHER PLASMA DEVICES FOR GENERATION OF
EM (INCLUDING RF) RADIATION - HIGH-CRITICAL FIELD SUPERCONDUCTORS APPLIED TO PLASMA DEVICES, etc.
- L'asic phenomena associated with plasmas in cros8ed eh,ctrie ',-fvl rnaqnctic fields
- TherliJodynarnk and transport prOpE~f't)e~3 of plasmas
- Basic atomic: physic:s of high-temper'ature <lnd l.tlgh-donshy pl;:J.Sraas
- Intern,ction of (:C'lectrOl::1llgnctic radiationvJiUl plasrGas
- ~~olution of plasrna problems by numerieal coynputc:r eXperiments
- trnpl'oved models of planebry atmospheres
AREAS OF RE8EAHCH EXPANmON • t • •
WTTII MORE PKmX)NNEL , ----
_ ('JJENJlC"AL K.ri"ffiTrC~~ OF PLAN'E'CAHY -ENTT·(Y PL,ASMAS
MAJOR OPERA'TING PROBLEMS . ,
1. - Adyancement to top grades of senior scientific personnel
II. - Obtainment of highly-trained specialists
III. - Obtainment and retention of laboratory-technician help
IV. - Obtainment of "small and urgent!! jobs from centralized technical services
v,. - Obtainment of "Math-Aide" type help
DISCUSSION OF SPECIAL PROBLEMS
'r
JOHN V. BECKER , .
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PROBLEMS
1.. ACHIEVEMENT OF A STIMULATED RESEARCH PROGRAM ..
2. INCREASING LAYERS OF MANAGEMENT ABOVE THE DIVI SION.
3. INCREASING TREND OF LRC TOWARD PROJECT CONTRACTING AND MANAGEMENT, RATHE THAN RESEARCH .
. ~"".~ I
4. LARG(AND IMMEDIATE REWARDS FOR SUCCESSFUL PROJECT HARDWARE: . HARD TO PR MOTE REWARDS FOR ADVANCED RESEARCH.
5. RATIO OFTECH SERVICE AND MATH AID PERSONNEL TO RESEARCH 'PERSONNEL HAS BECOME TOO LOW.
6. LONG, DI SCOURAGING,AND UNNECESSARY TIME DELAYS:
TECHNICAL EDITING OFFICE RESEARCH STAFF OFFICE
.,' . DES I GN AND PROCUREMENT
TEST MODELS RESEARCH EQU I PMENT
7. lNCREASING ADMINISTRATIVE AND RESEARCH MANAGEMENT PAPER WORK WITH LlTIL .REAL VALUE TO OUR OPERATION.
8. LRC HOUSING FOR PROFESSIONALS GENERALLY INFERIOR TO ALL OTHER MAJOR NASA ENTERS.
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APD FACILITIES
MAG N ETO PLA SMA DY NAM I'C S FACILITIES
. CONTINUOUS FLOW HYPERSONIC
TUNNEL
"
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HOT GA S RADIATION RESEARCH FA C I L I TY
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APD PHASED-OUT EQUIPMENT AND FACILITIES I
Air-I nduction Laboratory
4-lnchSupersonic Jet
. 24-lnch High-Speed Tunnel
4xl9-lnch Transonic Tunnel
. 9'~:1 n c h Supersonic Tunnel
Cascade Aerodynamic Laboratory (High ... Speed Cascade.s,· .Supersonic Compressor Test Rig, Etc., given to NATO Von-Karman Training Center,. Belgium)
I 2 - Inc h Mach I. 4 . Jet
20-lnch Variable-Mach Jet (M • 1.4 - 4.5)
Free-Piston~Compressor Tunnel
12-lnch Mach 13 Pebble-Heated Jet (given to NYU)
'\ Low D·ensity Mach 6 Tunnel
Five Jets~ 8 Inch to 12 Inch, Mach 2 - 5
Mac h3 Boundary Layer facility
T h r e e S hoc 1< Tub e s (g i ve n to un i ve r s it i e s )
M • 4 Tunnel (given to VPI)'
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FACILITIES ON STAND-BY .
DOWTHERM AIR HEATING EQUIPMENT
II-INCH HYPERSONIC TUNNEL
12-1 NCH AR C TUNNEL
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AERO - PHYSICS DIVIS
Divis ion Offic~
J. V. Becker, Ch iet , E. S. Love, Asst.. Ch.
L. I. Turner, Asst. Ch.
_f
ION
Hypersonic Fluid
Mechanics Branch
Reentry Physics Branch
Hypersonic Aerodynamics
Branch h
Vehicle Researc Branch
1------
Res~ proi M. H. Bertram
24 Res. Prof. R. L. Trimpi
\I Res. Prof. W. J. Nelson
TOTAL RESEARCH PROFESS IONALS -Doctors - .11 Masters - .sf If 'f Bachelors - IJJ 7 I
(NCR Associates, not included above - 7) Supporting Professionals -Non-professionals -
TOTAL
, ,
129
15 23
JW" II, 7
18 Res. P C. H. Mcl
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I I Hypersonic Magneto Propulsion Plasma
Branch Dynamic~
I .... "\ ':l.-Bra nch ~Res. Prof. ..arRes. P of •
J. R. Henry M. C. Ell is Jr. '.
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APD FLlJff) I1£Cf/ANICS
~8+N T~ANS~NJC FJ.DWS, AIRfOILS
~FOI?CfSJ PRESSURES
.' ~//2Z7///7ZZ/ZZZZ2 ~:~~i~(Ts:;~:S ..... -:::9ZZ27ZZ~/Z2 z < 8Lr:..~ -%"~ViFER :Z7ZZ772~ <:? Z Z 7 Z: LOW DENSITY
, • 2 Z Z Z Z ZV/ZZZZ z ZZ2Vft~ FloWFlELDS
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. ~.~711: M.P.D.
~HOT<TAS ...... . = RADIATION •• , l t , I • t t , ' l • , , , , t , I I • I
19'17 '1'1 SI 5J SS S7 51 &1 43 ,S' 47 196' YEAR
\ ' , . A iP 0 PRO P U l S \ 0 N A l: ROD Y N A M \ C 5 -- ---
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APD CONFIGURATlON BESEARCH
"'" '. -,--" .-"'-'
. X-2, X-3 < lOO-Series A ,C M ·2 Canf. Study
._. __ .Ml?~.!\ es _-----.
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( jAdV. En ry, i
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AERO - PHYSICS DIVISION ___ ---.-.---w--~---·--·----
\~?~yj~~~~~~ehi'f . \ E. S. Love, Asst. Ch. I L. I. Turner, Asst. CIl.
~" __ J---" --..--"~r_-, __ -==;~~l-:~--\~~=~-~~~::::~-_------:-~I Hyper son ic R een\ ry Hype rson ic Vc h icl e Hyp¢r son i c
Fluid Physics Aerodynamics Research Propulsion
MagnetoPlasma
Dynamics
Mechanics Branch Branch Branch Btanch --.~ .. ------.---.-.-.. -- 13 Res. Prof.
J. R-;Henry Branch ---_ ..... -_ ..... 28 Res~ Prof.
M. H. Bertram
f--"---24 Res, Prof. R. L. Trimpi
\I l~es. Prof. w:-I-Neh6-n
I '
TOTAL RESEARCH PROFESS IONALS - 129 , Doctors - 6
Masters - 32 ", Bachelors - 91
(NCR Associates, not included above - 7) supporting Professionals - 15 Non-professionals _ ' 23 TOTAL 166
18 Res. Prof. C. H,-McLellan-
Branch -.-.. ~-.-.
31 Res. Prof. M. C. Ellis, Jr.