Publications Of The NACA

The following is a list of afew of the publications of theNACA, with excerpts from theirSummaries. The informationpresented in them is of value tothose people interested in de-signing their own airplanes orstudying airplane design. NACATechnical Reports, TechnicalNotes are available for a per-iod of about 5 years after publi-cation. Technical Notes andMemorandums can be obtainedfrom the National AdvisoryCommittee for Aeronautics, 1512H Street, Washington 25, B.C.Technical Reports can be pur-chased from the Superintendentof Documents, - GovernmentPrinting Office, Washington B.C.who can also supply a list ofAviation Publications. PublicLibraries in many of the largecities have NACA Reports onfile. Out-of-print publicationsof the NACA can usually be ob-tained on a loan basis from theNACA, and photostat copies canbe purchased from the Photo-duplication Service of the Li-brary of Congress, Washington,B.C.

NACA Technical Note 2440,Wind Tunnel Investigation andAnalysis of the Effects of EndPlates on the AerodynamicCharacteristics of an UnsweptWing, by Bonald R. Riley, Au-gust, 1951.

A wind tunnel investigationwas made to determine the ef-fects of end plates of variousshapes and'areas on the aero-dynamic characteristics of anunswept and untapered wingof aspect ratio 4. A theoreti-cal analysis indicates that theuse of end plates may provide

relatively large increases in theli t-dr?g ratio at the higher liftcoefficients but that end platescannot be expected to providesubstantial increases in themaximum lift-drag ratio of thewing. The increase in lift-dragratio obtained by using endplates is not likely to be as largehowever, as that which wouldbe obtained by using the endplate area as a simple additionto the wing tips 'o increase thewing span and the wing aspectratio.

The use of end plates wouldseem to be of primary import-ance when it is desired to keepthe wing span as small as possi-ble. The heights of end platestested varied from a minimumof 2V2 times the wing thick-ness to a maximum of about 12times the wing thickness. Onepch of the 15 types of end platestested the maximum lift-dragratio was less than that of thewing alone.

NACA Te-hnical No'e 1$71:^light Measurements of the Fly-ing Qualities of Five Light Air-planes, By Paul A. Hunter, May19^8.

Results are presented of aninvestigation made to determinemeasurements of stability, con-trollability, and stalling charac-•"eristics of five light airplanes.The results are based on dataobtained from photographic re-cords of continuously recordinginstruments supplemented bypilots' observations.NACA Technical Note 1945,Aerodynamic Characteristics of15 NACA Airfoil Sections atSeven Reynolds Numbers from700,000 to 9 Million, By Laur-ence K. Loftin, Jr., and Hamil-ton A. Smith, October, 1949.

The airfoils investigated con-sisted of 10 NACA 6-series sec-tions and 5 NACA 4- and 5-

digit-series sections. The air-foils were selected to show theeffect upon the resultant aero-dynamic characteristics of sys-tematic variations in thickness,camber, and thickness distribu-tion. Lift, drag, and pitchingmoment data are presented foreach of the plain, smooth airfoilsand a sufficient amount of datais also included to show the ef-fects of leading-edge roughnessand split flaps upon the charac-teristics of the airfoils.

NACA Technical No'e 8'C,Cooling and Performance Testsof a Continental A-7 ~> Engine,by Herman H. Ellerbrock, Jr.and Robert O. Bullock, 1941.

An investigation was startedby the NACA to determine theperformance of a small airplanewith two Continental A-75 air-cooled engines enclosed in t"iowings. The object of the report-ed tests was to determine thequantity of air and the pressuredifference required for satis-factory cooling of the engine atsea level and at altitude. Theengine cylinders were complete-ly baffled and the steps takento obtain a satisfactory set ofbaffles are described. A mod-ified intake and oil system whichdecreased the thickness of theengine was tried and descrip-tions and test results are givenof three modified intake mani-fold systems.

NACA Research MemorandumL54B12a,Flight Tests of a Man Standingon a Platform Supported by aTeetering Rotor, by Paul R. Hilland T. L. Kennedy, March, 1954.

A series of flight tests weremade to determine the flyingqualities of a man standing ona platform supported by a tee-tering rotor. The rotor was 7feet in diameter and was drivenby air jets at the rotor tips fed

by hollow olades and air hosesconnected to an external air sup-ply. The machine was tested in-doors in hovering and in limit-ed translational flight and out-,doors in light and in strong gustywinds.

NACA Technical Note 2404,•An Analytical Investigation ofEffect of High-Lift Flaps onTake-Off of Light Airplanes,by Fred E. Weick, L. E. Flana-gan, Jr. and H. H. Cherry, 1951.

Various phases of the prob-lem of improving take-off per-formance by the use of flapswere considered. Existing high-lift and control-device data werestudied and compared to deter-mine which combinations of suchd^-''ces appeared to offer the• o:t suitable arrangements forlig'it ai~cra rt. A typical mech-anism to provide for actuationof the movable surfaces for bo'hhigh lift and lateral control ispresented. Working charts wereprepared for the prediction oftake-off distance and for thedetermination of take-off speedand the resultant lift coefficientdesired. Calculations indicatethat reductions of approximately25 per cent in the distance re-quired to take off and climb to50 feet are possible by the useof suitable high-lift flaps.

Technical Report 824 Sum-mary of Airfoil Bata, by Ira H.Abbott, Albert E. Von Boenhoffand Louis S. Stivers Jr., 1945.

Bata for both flight and windtunnel tests have been collectedand correlated. The report in-cludes an analysis of the lift,drag, pitching-moment, and crit-ical speed characteristics of theairfoils, together with a discus-sion of the effects of surfaceconditions. Bata on high liftdevices are presented. The or-dinates for a large number ofairfoils are tabulated.

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Publication Of The NACA

Jack McRaeThe following is a continua-

tion of the list of Publicationsof the NACA, with a short sum-mary of each one. The informa-tion presented in these reportsalthough published some timeago, is in many cases of a funda-mental nature that is of valueto those people interested indesigning their own airplanes orstudying airplane design. Muchof the technical informationpublished in the 1920's and1930's is directly applicable topresent day light-plane design.Although these reports are outof print, they can in most casesbe obtained on a loan basis fromthe National Advisory Commit-tee for Aeronautics, 1512 HStreet, N. W., Washington 25,D. C. Photostat copies can bepurchased from the Photodupli-cation Service, Library of Con-gress, Washington 25, D. C., andmany Public Libraries in largecities and colleges have themin their files.

Technical Report No. 345The Design of Airplane Wing

Ribs, by J. A. Newlin andGeorge W. Trayer. 1930.

This report gives informationon the design of truss type andplywood web type wood wingribs. Static load tests weremade on a large number ofwing ribs of 48 inch and 96 inchchord to show the relative efficiency of different types ofwood construction. The efficien-cy is based on the rib strengthcompared to its weight. Withideal construction the trusscomes first; second is a lighten-ed and reinforced plywood type;third is a full plywood web typewith stiffeners; fourth is a ply-wood web with lightening holes;fifth is a full web with no stiff-eners. In general vertical facegrain in plywood webs givesgreater strength when a fullweb is used, but longitudinalface grain is better when light-ening holes and stiffeners areused. The report also containsother comments on various de-signs and much useful informa-tion regarding types of rib fail-ures.Technical Report No. 408

General Formulas and Chartsfor the Calculation of AirplanePerformance, by Bailey Oswald,1932.

This report develops formulasfor the determination of all ma-jor airplane performance char-

acteristics such as maximumspeed, maximum rate of climbspeed for best climb, maximumlift-drag ratio, speed for maxi-mum lift-drag ratio, absoluteand service ceilings, time toclimb to various altitudes, andspeed for minimum power re-quired. A correction is madefor the variation of parasitedrag with angle of attack and thenon-elliptical lift distribution byusing the airplane efficiencyfactor "e". In order to make theformulas easier to use a seriesof performance charts is pre-sented for airplanes with un-supercharged engines and fixedpitch propellers operating atvarious altitudes. The resultsobtained by using this methodof performance calculation havebeen found to give very goodagreement with flight test data,and this report has been usedsuccessfully in predicting per-formance on many new airplanedesigns.Technical Note No. 212

Simplified Propeller Designfor Low Powered Airplanes, byFred E. Weick, 1925.

This report furnishes the de-signer and builder of small air-planes a simple system for thedesigning of a propeller andmaking a layout drawing. Apractical design method is pre-sented based on tests of modelpropellers in wind tunnels andfull scale tests of propellers inflight. The actual designing isaccomplished by means of chartsand involves very little calcu-lation. The layout and draw-ing of the propeller is also re-duced to simple operations bythe use of a basic or master pro-peller with dimensions given interms of the diameter. Use ofthe information presented al-lows the choice of pitch and di-ameter of a propeller for a newdesign with a minimum of work.Technical Memorandum No. 261

Light Airplanes Which Par-ticipated in the Contest atL y m p n e, England, October,1923.

This report, and the followingone, are reprints of material thatappeared in the British maga-zine "Flight" and "The Aero-plane". It presents a descrip-tion, with outline drawings, oftwelve of the most practical ofthe ultra-light single-seat air-planes taking part in the con-test at Lympne, England. En-gines were limited to a displace-ment of less than 46 cubic inch-es. Features of particular in-terest of the various airplanesare described with reference tostructural a n d aerodynamiccharacteristics. Also included is

a set of drawings and ordinatesof six propellers designed bythe U. S. Bureau of Aeronau-tics, Navy Department, for thistype of airplane.Technical Memorandum No. 289

Two Seat Light AirplanesWhich Participated in the Con-test at Lympne, England, 1924.

This report gives descriptionsand outline drawings of thirteentwo seat light airplanes whichcompeted in the contest atLympne, England. The purposeof the contest was to develop alight airplane suitable for dualinstruction use. The airplaneswere judged on their flight char-acteristics including s p e e drange, take off and landing overan obstacle, and reliability. Inaddition it was required thateach airplane be disassembled orfolded in such manner so as tobe stored in a shed 10 feet wide.The airplane was then requiredto be reassembled by two peopleonly, within a period of twohours. Engines were limited toa displacement of less than 67cubic inches.Technical Memorandum No. 311

The Light Airplane, by IvanH. Driggs. Reprinted from "TheSlipstream Monthly" magazine,1924.

Part I is a brief review of theresults obtained in the develop-ment of light airplanes. A sum-mary is given of dimensions andperformance of a number ofAmerican and foreign light-planes built up to 1924. Part IIis a description of the applica-tion of theoretical aerodynamicsto light airplane design. The In-duced Drag is discussed and theimportance of span loading onlow powered airplanes is point-ed out. Some examples are giv-en of performance calculationsfor a lightplane and recommen-dations for propeller design arepresented. Formulas are shownfor calculating the total powerrequired for an airplane includ-ing the effects of Induced Dragand Parasite Drag.Technical Memorandum No.326

The Light Airplane, by IvanH. Driggs.

Part III presents a series ofcharts by which it is possibleto predict the performance char-acteristics of a 500 pound light-plane with various wing spansand engine power. Charts aregiven for take-off run, angle ofclimb, time to climb to 5000feet, maximum speed, and abso-lute ceiling. The importance oflarge wing span for low poweredairplanes is shown with exam-ples of the effect of differentspan loadings. Part IV and Vgive the application of the pre-

viously developed ideas to thedesign and layout of a singleplace monoplane powered witha Henderson motorcycle engine.A method is presented for calcu-lating the required tail surfacearea and for making a weightand balance estimate. Consid-erable information on actualweight of aircraft materials andhardware is given. A three-viewdrawing of the proposed designis shown with a balance diagramlocating the center of gravity.

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