NASA NACA-TR-781-1944 Wind-tunnel procedure for determination of critical stability and control characteristics of airplanes《测定飞机临界稳定性和控制特性的风洞程序》.pdf

1、, . , ,_ _. +,- +_=:=-+ _l_cf+ t2c-p_V.-7 7“/l-_l_tz _OPYI + “ “ +_ -. “+ _=:+ _- - I“ -._+ +. +, + . _ +_+ _-+ ,. _+- + + - + -,+ - _ - CO .O_g- + + . .+ _ . + + .NA_AL+ADVISORY +COMMITTEE+ ij + - +- + -.r, .: +-FOR AERONAUTICS-_+, _: +“ L “ “ I _ _ _ - _ + - .+ .+ _- _- _+ : + . _ - . r _ + . :-_

2、. “ - . .= + : :*. +. +,-_+ +_ +. +-+ . REPORT No. 781 ._- _ :. ; L-2- “ -+:,-WINDTUNNEL PROCEDURE FOR DETERMINATION_+OF CRITICAL STABILITY AND CONTROL + = +,- - . . . +. CHARACTERISTiCS OF AIRPLANES - -+-. _ +- . _ -+By HARRY J. GOETT, ROY r. -JAcKSON - - “ + .- - “ +-“-:. +: and STEVEN E.BELSLEY -

3、 - - _-:+- - _ + - - -+_- “=+-+“ -“ + + “ +_- +_ + L + - _ -. -. + + - :. + _ -_.- . + + _+ -= :+-+- :_+.-+:+:_ :I:-+,_+FIKE-OopY + “ + I_ film*f Uml_lJm_ + . +_, mmmm. + _+ : Wm#vm m a. - ; _ .- + - + _ ._+. _. =_+_: _._ _“ -.+_Y+!-+_?_!+j-z:A-.-+i- 1944 - - “:_-. _+ :-_-=_-+ _._+ _ . _ - . + = + _

4、 . +. _ - . . ,-+-= _ : -+- =+_+ =+_-_ +Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- _ _ L _4 _ _ “ _ _, . - “_-_- _ _ - _ -_- _ “ - AERONAUTIC SyMB()-L$ - - - - _ -. - I. FUNDAMENTAL AND-DER-IVED UNITS - -Metric - - “ English- Symbol -_ _ _ “ “

5、_ -_ , “ - . -_- uni_ “ Abbrevia- - Unit - - -:- Abbrevia-. . _ - “ -tion !- tion- Length_- . “ - t - I meter_.z:_-:_:-_-:_.:._| m foot (or mile) . ft (or-mi)Time t _e_ond. - . s second (orhour) see (orhr)Foroo F weight of 1 kilogram . kg weight of 1 pound . . lbPower . P, . hprsepower (metric) . -h

6、orsepower-_ hp - . _ i tr fkalometers per hour q_p_h miles per hour . =_ mph “_v 1 _ meters per second . mps - fee_ per second fps - -“ _ _. - 2. GENERAL SYMBOLS - - L _W Weight=rag , Kinematic viscosity - - - - - -g Standard acceIeration of gravity=9.80665 m/s _ p- Density (ma_s per unitvoiume) or

7、32.1740 ft/sec _ “ “ - - _tandard density of dryair, 0.12497 kg-m-ts _ at 15 C“ - M IV = -:- - -:_ - - and 760 mm;-or0.002378 _lb-ft-*sec _ , ,. ass-_- . Specific weight of “standard“ g_, i.2255 kg/m _ or-_ I Moment of inertja-_mkt (Indicate axis of 0.07651 lb/cuft _- _ -radius of gyratiOn k by prop

8、er Sub,script.) _-_ : _ _ _t_ Coeffieieaof viscosity-_ - _L. _ - _L-_-“i- _-“ :_ - _ _:_-Z- -:- _ 3, A_E_ROD_AMIC SYMBOLS -Area - i, Angle of setting of wings (relative-_0-thrust line)-_ - _Y_, -Areaofwlng . i, Angle-of Stabilizer setting (relative tothrusta Gap . _ line) b Span - - _ O _ Resultant

9、moment- _- e- _ C/aord - _- _ -_ - _ ft_ -Resultant angular velocity -_: _- _ . _-A Aspect ratio, _ - R ReynoMs number, I7 whexe lis alinear dimen-/zV True air speed = - - “ :- _ sion(e.g., for an airfoil of 1.0 ft chord, 100 mph,_/ Dynamic pressure, _p_-I._. standard pressure at 15 C, the correspon

10、ding - Reynolds number Js 935,400; or for-an airfoil-L L_fg - _ L - of 1-0 m Chord, 100mps, the correspondingabsolute coefficient C_q-_ - “ “ “Reynolds number-is 6,866,000) , - - - D _- a Angle of attack - D Dra_, absolute coefficient C_=_-_i 3ingle of dowmvash - . -_- - _-_- . _, . Do- Angle of att

11、ack, infinite aspect ratioDo Profile dra_, absolute coefficient C_o-q-_ a0. _ _ Angle of attack, induced:=-=-_- D_- -Induced drag, abs_ute-coefficient C_t_,-D _ - -_,-_ Angle,_of .attack,. absolute (measured_rom zero-qS _ lift positron)-=-DiC-=:_=dlag,absolu-tecoeffi-cient_ D, _i Flight-pathangle -

12、.(“Dt _ “_ . L - C(7 Cro_._-wind force, abso_lute coefficient C_=_-S “Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-REPORT No. 781WIND-TUNNEL PROCEDURE FOR DETERMINATIONOF CRITICAL STABILITY AND CONTROLCHARACTERISTICS OF AIRPLANESBy HARRY J. GOETT,

13、 ROY P: JACKSONand STEVEN E_ BELSLEYAmes Aeronautical LaboratoryMoffett Field, Calif.74_i7:If; 47 !Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-National Advisory Conunittee for AeronauticsHeadquarters, 1500 ,_w Ilampsh_re Avenue NW., Wa._hi_gton 2

14、5, D. C.Created by act of CongTess approved March 3, 1915, for tit(, supervision and direction of tlle scientific studyof the prol)lems of flight (7. S. Code, title 49, sec. 241). Its membership was increased to 15 by act approvedMarch 2, 1929. The members are appointcd by the Preside,at, an(1 serve

15、 as such without compensation.JEROM_: C. tIUS.SAKER, Sc. D., Carol)ridge, Mass ChairmanLYMAN J. BRIGC, S, Ph.D., Vice Chairman, Director, NationalBureau of Standards.CHArtLES G. Am_oT, Sc. D., Vice Chairman, Executive Committee,Secretary, Smithsonian Institution.HEXRY II. ARNOI.D, General, United St

16、ates Army, CommandingGeneral, Army Air Forces, War Department.WII,LIAM A. _. BURDEN, Special Assistant to the Secretary ofCommerce.VANXF_VAR BI-sH, Se. D., Director, Office of Scientific Researchand Development, Washington, D. C.WILLIAM F. DURAND, Ph.D., Stanford University. California.OLIVER P. ECH

17、OLS, Major General, United States Army, Chiefof Maintenance, :Iat_riel, and Distribution, Army Air Forces,War Department.AImnEV W. FITCH, Vice Admiral, United States Navy, DeputyChief of Operations (Air), Navy Department.WIlmI,M LITTLEWOOD, M. E., Jackson IIcights, Long Island, N. YFRANCIS W. REICII

18、ELDERFER, So. D., Chief, United StatesWeather Bureau.LAWRENCE B. RICHARDSON, Rear Admiral, United States Navy,Assistant Chicf, Bureau of Aeronalttics, Navy Department.EDWAUD WARXEa, SC. D., Civil Aeronautics Board, Washing-ton, D. C.0RWLLE WBIC, IIT, Sc. D., Dayton, Ohio.THEODOnE P. WnIaIIT, Sc. D.,

19、 Administrator of Civil Aero-nautics, Del)artmont of Commerce.GEORr, E W. LEWIS, Sc. D., Director of Aerona!dical ResearchJOHN F. VICTORY, LL. _., SeerelaryHENRY J. E. REID, Sc. D., Engineer-in-Charge, Langley Memorial Aeronautical Laboratory, Langley Fieht, Va.SMITh J. DEFaAxCE, B. S., Engineer-itl

20、-Chargc, Ames Aeronautical Laboratory, Moffett Field, Calif.EDWARD R. SHARP, IJ_. B., Manager, Aircraft Engine Research Laboratory, Cleveland Airport, Cleveland, OhioCARLTOX KE),rFER, B. S., Executive Engineer, Aircraft Engine Research Laboralory, Cleveland Airl)orl, Cleveland, OhioTECHNICAL COMMITT

21、EESAERODYNAMICS OPERATING PROBLEMSPOWER PLA._TS FOR AllCRAFT MATERIALS RESEARCH COORDINATION“AIRCRAFT CONSTRUCTIONCoordinalion of Rtsearch Needs of _IiIitary and Civil AviationPreparation of Research ProgramsAllocation of ProblemsPrevention of DuplicationLANGLEY _EMOBIAL AERONAI;TICAL LABORATORY AME

22、S AERONAVTICAL LABORATORYLangley Field, Va. Moffctt Field, Calif.AIRCRAFT ENGINE RESEARCH LABORATORY, Cleveland Airl)ort _ Cleveland, OhioConduct, under unified conlrol, for all agencies, of scientific research on the fundamental problems of flightOFFICE OF AERONAIYTICAL INTELLIGENCE, Washi,_glon, D

23、. C.Collection, classification, compilation, and dissemination of scientific and technical information on aeronauticsIIProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-REPORT No. 781WIND-TUNNEL PROCEDURE FOR DETERMINATION OF CRITICAL STABILITY AND CON

24、TROLCHARACTERISTICS OF AIRPLANESBy tlalmY J. GOETT, ROY P. JACKSON, ,_nd STEVEN E. BE,SLEYSUMMARYThis report outline,_ the flight comtitions that are usuallycritical i_ _ktermini_g the dcsig_ qf eompo_e_ds . an airplaJ_ewhich affect its stability a_d c,mtroI characteristics. Thewiml4unml tests neces

25、sary to determine the pertinent data Jorthese eomlitbms are imticated, amt the methods _ computationused to ba_slate these data i_do characteristics wMch lb,/sq, fl.(b) Computation ti_hle.o-_+i I Ii Lc_ _ i.I -,OP+ 0i 1 e+r 3 _ -;_ u - ,_ _:, . 8i-t_ /.0 -,_. 1.2:- 1 L _. L_.02 .03_,to) .“,To(let ch

26、ar;).etcri,stics eross-ploltcd.: l+.I I I I ,_,lane steady Hight characteristics240FW,UIIE 2. Variation of elevator angle and stick force with speed. Steady flight with flapsand gear down, SO-percent norm,ll rated power. Single-engine airphmc.Provided by IHSNot for ResaleNo reproduction or networkin

27、g permitted without license from IHS-,-,-WIND-TUNNELDETEH_INATIONOFCRITICALSTABILITYAND CONTROL CILkRACTERISTICS/2 x /6 “ 0 4 8 12 16Anq/e of o/tack, ct, c/eg(a) Model charaeteristics determined from wind-tunnel tests, e.g. at 16-percent MAC. I “ 1 t _ _ Tat . Iral TabCh, tolrimatl.t l_,_u, J Jno gr

28、ound, normal itwash e, ,_m- A in r I A t e _m,tt l wihtal _ ,_CL, I.n , mglei was m,g,e r_ c_e _(u_ b alch_ e incidence / CLeor C%eo i_resent i wi ln o downwa_h ! grounl f r t_la e mcrea:cdby respond- Vifor :espone/i wilff ent )f to _ : - _ Sti, k_, angle el oresence t f grou_ th no for, e_na 1 _.r.

29、_; I am., efal _( I nerement ngto ,_ ._ ngto “,ear- ,_ _ _,-a T.S t equaltoAct_ t_of _/_._“ (f,A_q 1.4 l:,toH C,. r . TabC,. !equal_tF/qC;, =ct cor._resp _ tmg _,o.m._ lm;_,.s _J frmn I of,._ an:l I from I , _._ I f,_,a_ d from I and m,_ I equals I _4-_refcrenecline From pa_rtI_,pnJ.)C/vr_“tCLuiandP

30、ndi_grest mlin :“tq . Fret C r of_,_ _e_Voo,.g. t _ _, _I ,faun “,1_“h angle I rmhftln _-_sm“-_.! f_of_Frorr “ i part(c_.=.,q,(c).Itf frm : - c“f_purl (e) I _-_ I 23.!1P:t _frr f nqualsf_ tainel. effet eqt ls_“_ttaek“ rc_rver_of(_ tamect from, |/sq ft. _art O) parta_“=I(a)(a) +,)t, tai, rt Ca) Ob re

31、fined4 _mofn,s, rerrrm-t n _o,usfez I_“_“W-t,o-:_I I t .9 f. 1 I. 1-2_ -790 /-Lg/ 6.0 -_,5 l. t8 81.4 I ?_ 4141bI puThe above computations arc for the three point atlitude. Computations for lan(ling at greater speeds arm made by interpolating bet wcen tire i_ limits of part (a).The results of refl,

32、rence 5 indicale a smaller increase in C;._ at a constant attilmle du, m ground effect. Hmn H_al computed by reference 4. Reference .5 also indieales a ptchingmoment Increment on the wing, (lrle to grounrl effect that tends o stall the airplane. The eompllla| hi15above do not allow for the ground cf

33、feets noted in reference 5. This procedureresults in a conservative estimate of _+and stick force to land (with respect to r_4(,renee 5).(b) Computation table.- o .“._)“ -2to) “-, ;-.0-_-0 LlO _-4-_.3d -20-E/evolor deflechom, 6_, degN a, , e9 - f,_o an _? “II-,2-I0 0(c) ModeI characteristics cross-p

34、lotted./o|bjO - _ _0_o . o75 80 85 90 35Ind/cofed a_rsrecd, I_, _ph(d) Airplane landing characteristics.FIC_L*R_;3.-Variation of elevalor angle and stick fl)rec in landing. Flaps and gear down, prnpellcr windmilling. Single-engine airplane.Provided by IHSNot for ResaleNo reproduction or networking p

35、ermitted without license from IHS-,-,-6 REPORT NO. 7$1-:NATIONAL ADVISORY COSf_TITTEE FOR AERONAUTICS.GConslomt_II.8 1.0 Z2Lift coeff/c/ent, CLa) Model charaeterlslirs determined from vind-ltmncl tests, c.g. at 26-percent MAC.2_!_/ C ,for/ n w lues/ _“1 0 1482 -_3 , 4444 . 5925 7406 888 - *, tobalan

36、ce C. due !to static ! stahilit y, if IFromcrosst)h)t _0. l _-1.1 3/2-2. 2 , 83-3.5 15,/4-4.8 24/5-5.9 35/6A_r; (fileto ctlrvi-linearflight0o0. 31 .5.5 77 I. 03 1.20 A_, 1o tl. for I Neulral tabmlane. C_=O C_, for C_L.in I withset foriabeiirvll llcdr m17_ du_ lln.eurw! _ an,l m Ch due o II I tn tito

37、 Aa flight from cross- Aa equalsg t_ n or Iequals (_ Idol plus Iplus (_ o I0_ 0,1 -0.00g. 0 -0. 0062 +0. 0062-0.54 -1.6 -. 0048 I -.0002 -. 00:,0 +. 0062-. 96 -3. 2 -. 0034 -. 0003 -, 0037 + 0062-1.34 -4.9 -.0018 -. 0004 -.0022 +.0062-1.70 -6.6 (_ +. 0018 -.0005 +.0013 +. 006212.o_ -s.o o +.0_,_ I -

38、.o_ +oo49 I +o_2 :I lStickforceF from!.39. _i .58. 0l d C=.I,=294 m. p.h. at 9,(W.Oft.,wing loading=a2.6 Ib/_qft.(b) Computation tahle.dC_,= Aa,( t 3ot= -OOOO. Aat_, dL_ /Ac_t0.575.020-4 0 -/2 -eElevator deflection, 6, deq(c),Iodel characteristics cross-plotted.6ONor-real occe/e:ohom, _, q(d) Airlfl

39、ane arceleratcd flight stick-force characteristics.FIGURE 4. Variation of elevator stick force with norma! acceleration in steady turning flight.Flaps and gear up, propeller windmilling. Single-engine_airplane.4 5 6Provided by IHSNot for ResaleNo reproduction or networking permitted without license

40、from IHS-,-,-_IND-TUNNEL DETER_:INATION OF CRITICAL STABILITY AND CONTROL CTTARACTERTSTICS 7 at t_ I .L _ I _r, dego Run 8a 0.04 _ _. _ , ,gb 201-8c_0_Cn-.02 - . =-,-.0. r- I- _A/Te,-on fined r-oll/l?q momenf.02 -coefficient foi _ C_ e_ uo_ Zel“O ,_ _ _c_=_ _ -c_-_ :_i ._.o,-.II-I_ -12 -8 -4 0 4 8 1

41、2An_/e of VOW, _ , degFIGURE :=:L ce,-e;on-.04 -.08 -.t2 -./6 -.20Czp , per- codlbn(b) Divergence characteristics of airplane.FIGURE pl* = full upfl“ “do_ = down; _ = 3/, upI I tRun I0o 0 0“ lob 15 - 15 to , IOc 20 -20iCondii ionHigh-speed lLow-speed _ _! .Iaz._ 0.051 ).109 0.91-_UUUI“-_,_* ZO_._ _

42、-. _I- ; .“13_“ i _097Full 050 .116 ,80I ,Dj)! .,=_. _O.09_ i 30-:_1 _- 40-7-I.o7_ I _o 09I i 40 I2O“t_ =0.8 V_,_266 mph; Ct.=0.IS, a=0.2 .1.2 V, tsu C/.=0.86, a_10.4 .a Cz_=-0.47 at high sI)eed and -0.43 at low speed (from ref. 6).Believed to bc representative of modern high performance airplanes.

43、(Assumes a rigidwing.)(b) Computation table, flaps up.08- l- / _ /_.-Low speed0 20 40 _0Tofol oileron deflection, d_r deg(e) Airplane rolling characteristics with flaps up.Flc, uaE 7. Aileron control characteristics (pb/2V against aileron deflection) Flaps and gear up. Single-engine airplane.-20 -10

44、 0 I0 . ZO 30Aileron deflection, 6a, de9(a) Hinge-moment characteristics determined from wind-tunnel tests.Note: Hinge-moment coefficients obtalnod from two-dimensional data.(c).20 .24Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-V/IND-TUNNEL DETER

45、S, IINATION OF CRITICAL STABILITY AND CONTROL CHARACTERISTICS 9, _ for i. : O./ -.2 _ ,L_-30 -_0 -/0 0 /0 20 30Angle of yov_, ,/i, deg(a) %Iodcl charaeieristies delermined from wind-tunnel tests.Rudderangle,$,-25 R-20 R-15 R0o15 L20 L25 L for C.equalsZCFO28.5 21.5 10. 5-6.7 -17. 2-20. 7-23.0# for C,

46、=0equals-,k for C,=028. 5 L21.5 I,10. 5 L6.7 e R17.2 R20. 7 R25.0 R _ _- ICh r for eda force. _and0.030 26.6.040 26.6 070 26.6.010 I 26.6-.050 26.6-.057 26.6-.055 I 26.6Pedalforce,b25 R34 R59 RR42L48 L46 LVi=lll mph q=31.5 lb/sq ft., wing loading=32.6 lb/sq ft.(b) Computation table.2_ zoLeftI00 _10

47、/0 20 30R/ghfAng/e of s/des/_o_ /Y, deg(c) Airplane stead:,“ sideslip characteristics.FIGURE 9.-Variation of rudder angle and pedal force with sideslip at low speed. Flaps andgear up, normal rated power. Single-engine airplane.o4 1 I 1IA_L ix. “.,- !_ _oRudderangle,0) 5 L25 _,for C_equalszero-9. I -16.4 - 18. 4-29.