1、.m*o0By.,.(. RESEARCH MEMORANDU-”TESTS IN THE AMES 40- BY 80-FOOT WIND TUNNEL OF AN AIRPLANECONFIGURATION WITH AN ASPECT RATIO 3 TRIANGIJLARJ WINGAND AN ALL-MOVABLE HORIZONTAL TAIL - LONGITUDALAND LATERAL CHARACTERBTICSBy David G. KoenigAmes Aeronautical Laboratory. .-.-.y A()Ty J . W. C!RORLRYKCHAN
2、GE #1621 CATE 32-1-53 TcC. F., . . . . E OF Oktt- -.r,t u .Hnri Gc) “ . Jb plp.,b). cLAasmrmEATNATIONAL ADVISORYCOMMITTEEFOR AERONAUTICSWASHINGTONApril 13, 1953,_=P/Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo repro
3、duction or networking permitted without license from IHS-,-,-INA.NACA RM A52L15NATIONAL ADVISORY COMMITTTW FORRXSEARCH MEMOFUNI)UMTECHLIBRARYKAFB,NMIillllllllllllllllllllllulllllllllni435zLAERONAUTICSmsm IN mm MS 40- “BY80-FoOT mm -L OF m AmmumCONJ?IGURATIONWITH AN ASPECT RATIO 3 TRIANGULAR WINGAND
4、AN AIL-MOVABLE HORIZONTAL TAIL - LONGITUDINALAn investigationhasIATERAL cHARAcTEKcEmccsBy David G. KoenigsuMMARYbeen made to determine the low-speed large-scale characteristicsof sm aspect ratio 3 triangular-wing airplanemodel. The complete model consisted of the wing in combination with a fuselage
5、of fineness ratio 12.; a thin, triangular vertical tail witha71 a constant-chordrudder; and a thin, unswept, all-movable tail (aspectratio of approximately 4). The wing had an NACA 0 (modified) sec-tion and was equipped with partial-span, slotted, trailing-edge flaps*of constant chord. Tests of the
6、model at zero sideslipwere made withthe horizontal tail at each of three vertical positions (O, 0.21, and0.41 wing semispan above the extended wing-chord plane) at one fixedlongitudinal distance behind the wing. The characteristics of themodel in sideslip were investigatedwith the tail in the extend
7、ed ting-chord plane. In addition, a limited investigationwas made on the useof flaps or the horizontal tail as a lateral-control device. The aver-age Reynolds number, based on the wing mean aerodynamic chord, wasH.8 million and the Mach nuniberwas 0.13.INTRODUCTIONWind-tunnel tests at subsonic aud s
8、upersonic speeds have been made “.for small-scale, aspect ratio 3 triangular wings. Ih order to extendthe scope of data on the aspect ratio 3 triangular-wingplsm form tothat of large scale, an investigationhas been conducted in the Ames.k)- by 80-foot wind tunnel.mProvided by IHSNot for ResaleNo rep
9、roduction or networking permitted without license from IHS-,-,-2 MICA RM A52L15For purposes of paralleling previous investigationsof airplaneconfigurationswith aspect ratios 2 and 4 triangularwings in the40- by 80-foot wind tunnel (refs.1, 2, and3), en aspect ratio 3 tri-qwingtith RuWCA 0005 (modifi
10、ed)section equippedwithtrailing-edgepqrtial-span slotted flaps of constant chord was testedin combinationwith a fuselage, vertical tail, and horizontal tail.This combinationwas identical to that used in the previo,usinvesti-gations. In addition to symmetricalcontrol deflections, the flaps andhorizon
11、tal tail were deflected asymmetricallyand a limited investi-gation of their use as lateral-controldevices was made.The results are presented herein without analysis in order toexpedite publication.NOTATIONFigure 1 shows the sign conventionused for presentation of thedata. All control-surfacedeflecti
12、ons are measured in a plane perpen-dicular to the hinge or pivot line of the control surface.bbfbtcECD(2ZcLcmCnCywing span, ftwing-flap span (movable),ft *horizontal-tail span, ft -.bwing chord, measured parallel to wing center line, ftmean aerodynamic chord of wing, measured parallel to wingJob/2 C
13、%ycenter line, , ftobi C dydrag coefficient,drag/qSrolling-momentcoefficient,rolling moment/qSblift coefficient,lift/qSpitching-moment coefficient,pitching moment/yawing-moment coefficient,yawing moment/qSbside-force coefficient, side force/qSProvided by IHSNot for ResaleNo reproduction or networkin
14、g permitted without license from IHS-,-,-NACA M A521J5 3total drag, lbhorizontal-tail incidence relative to the wing-chord plane, degdistance from moment center to pivot line of the horizontaltail, fttotal lift, lblift-drag ratiorate of rolling, radians/seewing-tip helix angle, radiansfree-stream dy
15、namic pressure, lb/sq ftwing area, sq fttrailing-edge-flaparea (totalmovable), sq fthorizontal-tail area, sq ftfree-stream velocity, ft/seclongitudinal coordinateparallel to model center line, ft “lateral coordinateperpendicular to plane of symmetry, ftvertical coordinateperpendicular to wing-chord
16、plane, ftangle of attack of the wing-chord plane with reference to freestresm, degrate of change of wing-section angle of attack with control-surface angle for constant section liftangle of sideslip of the model plane of symmetrywith referenceto free stream, degaverage flap deflection with reference
17、 to the wing-chord plane,degdifference in deflection between a pair of control surfaces usedas lateral controlsPositive when left-hand control has morepositive deflection, deg(Sub-subscriptsdenote the control used: f, flaps; t, hori-zontal tail.)Provided by IHSNot for ResaleNo reproduction or networ
18、king permitted without license from IHS-,-,-NACA W A52L15br rudder deflection, dege av average effective downwash, deg*. .DESCRIPTION OF MODELPertinent geometric data are presented in table I and figure 2,and a photograph of the model is shown in figure 3. uThe wing had an actual aspect ratio of 2.9
19、9 andNACA 00 (modified)sectionsparallel to the model center line. The modification to theNACA 00 sections consisted of a straight line fairing from the F, fuBelage;V, vertical. tail; HL, EM, HH, horizontaltail at low, middle, and high positions, respectivelyControl yB ;ZK!(a), (b) H+F+V+EL o 0 0 0 0
20、 0,6,2.2 -2 ta 29 CL % cDj cmcl, , Cyis(a), (b)(c)0,6, xw.8,H+F+V+HL % %;y%B ;1 %o 0 0 0 0 -2t0z2 2kcL VS U., , ,lk(a), (b) U+F+V ho o 4 0 0 0,6,12 -2t025 ZJ % CYlfla), CL? % % cu(b), (c) W.IJ+VWL 40 0 -6 0 0 -2tax20,6,12,18, cm Cy Vs p2416(a), (b) ; moment center, (?.4362.a71 , .Provided by IHSNot
21、for ResaleNo reproduction or networking permitted without license from IHS-,-,-a71 a15 b .Iiiiiiiiiil1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 I I I I I I I I I I I I I I I I I I I 1 I II -j“4 O 4 8 12 B 20.W B H .12.08# O-O4JX-.I2-.E.4eddtact, u, g Rw71hg- lllLWWlt G7MffMt, Cmo 1 2 3 .45.8L7 weffkim Hgur
22、e Z- Longltuo%d characteristics of the model with the horizontol tail in the middleposition. H, 0.2/; moment center, O. 44fZj 8f, 0?Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Angk of attack. a. (kgFigure 8.- LongifudinoiRkk.l?kmd c#iwwe cmo ./ 2
23、.3 4 .5.6w ca?ff moment center, 0. 485E; i+, P, .a71 a15Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-, c . .Angle cf atfack, a, d6w tikhhlg-t meffb%nt, Cmo .1 .2 3 456.7Chg LveffliAMt, CD(d #f, 0Fiy.ue 9.- 7he eti%ct of* hon&Wul W h % bw .LVS#rbn
24、on t% kwgittiilmx$# I& tnv fbp Mkwtii.nzs. +, Oj nwnB7t amhr, 0.436E.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . t .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-, ,At?#e d attack, a, &g )?d
25、chii)g- Inmn?nt Cueffkxknt, cmo .1 .2.3.4.56.7.6#ug Gveffm( coFgum 10. cho7KUYWsl%s & t% /lW&l Wil%xd #k? I%W12CY71W W d #lrw C7ngks of sMkTl,IW?kWt mm, CM3&5.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-_.20-2-.4-lx.m Om -.04 -.O. Y-. .0 0 .01 .&
26、 m .04 . -.12 -.Ch9 -.04 0 .04 # .1PIWllhg -mment cvefficimf, C$ Y*. nnuneni &f&n Gn SWe-fcme cc#itif, Gy. ,(3) QKScj. Cn, CyFlgum /0. - CbwM?if.tom1Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NAC!ARM A52LL51e, deg , deg0U6.?: 12.6 0 18.7 0k 24B
27、O 0.4 40 6.7 404 12.8 40Q 19.O 40%26.0 40(d CL, CD Vs /eFigure Il.- Churucteristics of the model Insioeslip without the horlzontol fail.Moment center, 0.4365.27Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-28 NACA RM A52L15I A II +I+t.Q -.04 I I I I I I I II 1. ILI-.08 k n dd-./2 k “ n-.16 ccd. r (k1 I I I I I I I I I 1 I Iw. 02 1,11 I t1 I u+=! !.#Angle of sideslip, /, deg(b) Gm, C VS /?Figure /- ContinuedProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
