NASA NACA-RM-A8J21-1948 Wind-tunnel investigation of horizontal tails IV unswept plan form of aspect ratio 2 and a two-dimensional model《水平尾翼的风洞研究 IV 展弦比为2的二维飞机模型的非后掠翼平面图》.pdf

1、3 copy No. .- - - RM No. A8J2 1 RESEARCH MEMORANDUM WIND-TUNNEL INVESTIGATION OF HORIZONTAL TAU. IV - UNSWEPT PLAN FORM OF ASPECT RATIO 2- AND A TWO-DIMENSIONAL MODEL By Jules E. Dods, Jr. .“ . Ames Aeronautical Laboratory Moffett Field, Calif. NATIONAL ADVISORY COMMITTEE - FOR AERONAUTICS WASHINGTO

2、N December X, 1948 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-By Jules B. Ikds, Jr. The results of a wind-tunnel investigation of the lowaped aerodynamic characteristics of a horieontal-tail model of aspect ratio 2 having an “unswept “ phn f oml

3、 and of a two-dimsnsioml model are presented. These data supplement previously reported results of tests on =wept and swep-ack llhodels of aspect ratios 3, 4.5, - 6. The twc-dimansiond model, which has the stme airfoil section as dlthe models tested in this series (RAW and hinge-mmnt prsslaters by t

4、he liftmurface- theory procedure. Test results me presented for the Mels with esd without standard roughness applied to their leading edges, with sealed and unsealed radius-nose,eleVstors, esd for a Reynolds ntunnel tests of unsuept and 35O 6wept-back plan-.iorm mdels of aspect ratfos 3, 4.5, and 6

5、are presented tn references I, 2, bnd 3. me present report extends the experimental data to include an aspect ratio of 2 and, in addition, presents section data which are neceesary for the Ufting-surface-itheory computatfons. A comparison of the experimsn- tal and theoretical results for the wwept a

6、nd the swept+aok plan forms of aspect ratios 3 and 4.5 bas been presented ip reference 4. The coefficients and eymbols used throughout the repart are def fned ES follows: . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-mACA RM no. AM21 3 8 A b C -

7、C ce H h L 2 M 9 R s se v aspect ratio ( SP/S 1 span of the model, feet chord of the model, feet *O root-me-qusre elevator chord aft of .the hinge line measured pixallel to the plsne of symmstry, feet chord of the eleva- coefficient unaarrected section pitch-nt ccref f ioient RESUlXS ABD DISCUSSIOX

8、The results of tests of the del of aspect ratio 2 are presestea in figures 4 to 9 and those for the two-dimensional model are presented in figure$ 10 ta 18. The variati- of lift , -nt, and pit-nt coaf f i- cienta with augle of attack are given in figure 4 for the model of aspect ratio 2 and in f igq

9、 10 for the tu-aeional model at a Reynolds nmer of 3 .O X 10 . H-nt cueif iciercts are ale0 shown as a. function of the elevator angle for various angles of attack in figures 5 and II. Additional data obtained for ghe two-dlmsnaiondl model at.Reynolds nunibers of 4.0, 4.8, and 5.5 X 10 are presented

10、 in figures 12, 13, and 14. phe variation of the pressure coeffi- cient acrosa the elevator nose seal with angle of attack ia preagnted in figures 6 and 15. The effect8 of variations of the Reynold8 nuniber, standard lead-dge roughness, and removal of the elevstdr nose seal on the lift and hing-mnt

11、coefficients are shown in figures 7 to 9 for the model of aspect ratio 2 and in figurea 16 to 18 for the two-dimensianal model. Effectiveness and Hinge-Xonnmt Pmmneters The 1FfGeffectiveness and the hinge-mament p8ramsters are listed in table 11*. AB shown in the table, ch,: for the model of aspect

12、ratio 2 was -0.0002, and the sectlon was 4.00573 the value of % (-0.0072) for the del of aspect ratio 2 was like wise lower than the corresponding section c (4.0ll4). The elewtorceffectivenese psrarrYstcr age was higher for the model of -0 e 2The parameters for the tw No. Am21 Static Longitudinal St

13、ability Phe variation of pitching+mmnt owfficiat with angle of attaok (fig. 4( c) indicates that the I elevator sealed Model Condition Model with standard roughness; elevator sealed - Model smooth; elevator seal removed. I cha Aspect ratio 2; R, 3.0 X 10 -0.0002 -m72 . .Ob0 .029 -0 73 TwcAiimensioml

14、 R, 4.0 X lo6 -0.0057 -. 0114 .lo8 .065 -. 60 4.0002 -. 0074 .040 .029 -0 73 4.0057 4.0057 -.0108 -. 0112 .lo8 .lo4 4 -. 60 -. 60 -qpjg7 8 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking per

15、mitted without license from IHS-,-,-. . - Aspect mtio 2 Two-dimsnsiona/ fiper mtio a5 - Ele wtor area 3.025 #“? Z142 ft C 3.293ft 3.500fi AM /OD83 ft 23,807ft 5 02?0 ft 1.050 ft - Drawing djmensions In inches (6) Two-dimens/onal. Figure 1.- Plan forms of the unswept hodzontal tail model of aspect mt

16、io 2 and the tm-dlmemhnal moM. G Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. ? Provided by IHSNot for ResaleNo reproduction or networking permitte

17、d without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . (b) Three-quader rea Hew. Figure 3.- !Che two-dlnemional model mounted in the 7- by la-fwt wind tunnel. Provided by IHSNot for ResaleNo reproduction or networking pe

18、rmitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . . . “ I Fjgure 4.- Lift blnge-moment andpjfcbing-momenf coeffldents forthe model of ospeef rafio 2. R. 3.010. 6 Provided by IHSNot for ResaleNo reproduct

19、ion or networking permitted without license from IHS-,-,-22 NACA RM Mo. A8J21 ,%) Hhgs-moment coefficfant. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-figm 4.- Conchded. Provided by IHSNot for ResaleNo reproduction or networking permitted without

20、 license from IHS-,-,-24 -24 -20 46 -/2 -8 -4 0 4 8 E/eVUtOf d8f/CtiOfl, 88 d8g .-. . figure 5.- Variotion of hinge-moment coefficient with elevator def/ection for vorious ong/es of uttock for the mode/ of ospect ratio 2. 6 3.0 x 106: Provided by IHSNot for ResaleNo reproduction or networking permit

21、ted without license from IHS-,-,-RACA RM no. A8J21 25 6 $ % cr, LO .8 .6 r 4 .2 0 4 .2 0 72 4 .2 0 :2 -I -.6“i“ -4 0 4 8 12 16 20 24 28 32 L,AA / %*/ Angle of aftack, (I, deg (0) 8, = 6: O,*- 4: Figure 6.- Variation of pressure coefficient across e/evotor nose sea/ w angle of attack for the mode/ of

22、 aspect rotio 2. R, 3.0 x /Ob: Vfb Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-26 NACA RM No. Am1 . “- , - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No. A-1 (01 Lift coeff.c/enf. Fig

23、ure Z- Comparison of fhe /iff and hinge-momenf coefficients for various va/ues of the Reyno/ds number for fhe mode/ of aspect ratio 2. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-28 NACA RM No. Am21 .24 .20 . /6 . /2 & -08 4. C .04 g % 80 E e -.0

24、4 8, & -.08 -. /2 -% 0 $ -. /6 -20 -.24. -4 0 4 8 /2 16 20 24 28 32 Angle Of aftock, deg “537 (&,I Hingemoment coefficient Figure z- Concluded. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No. Am21 29 116 1.4 .8 O“ .6 72 -4 -.6 -.8 -110 Angle of attack, Q, deg =-z57 fa/ Lift coefficient. Figure 8.- Compurison of the /iff and hinge-moment coefficients for the mode/.of aspect rutio 2 with andwithout /euding-edge roughness, RJ 3.0 x IO. - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-