NASA NACA-RM-A7J22-1948 High-speed aerodynamic characteristics of a model tail plane with modified NACA 65-010 sections and 0 degrees and 45 degrees sweepback《带有改装NACA 65-010剖面和0至4.pdf

1、I LqJy do. t .- us RM No. A7J22 RESEARCH MEMORANDUM- HIGH-SPEED AERODYNAMIC! CHARACTERISTICS OF A MODEL TAIL PLANE WITEI MODIFIED NACA 65-010 SECTIONS AND 0 AND 45 StiEPBACK Joseph L. Anderson and Andrew Martin Ames Aeronautical Laboratory Moffett Field, Calif. NATIONAL ADViS6RY COiujMlTTEE FOR AERQ

2、NAUTICS WASHINGTOrY January 12,1948 . i . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Nafioml Asro%Ucsad Soac8Mmmsramn . Lmngley Rw6lrahCenlw HRCoaticn action ampl,emnts ctilier sctions by the Naticxml Archives and Record8 Sewlo+ (#lurs) and by t

3、he HASA Security Cla!4eifiuatfos Officrr Wco). In Dmalasmifiaatioh B Ocaqruu 60XKMr therefore, no oorreotlons uem applied to the data. The Eeynolda nmibers for both tail planes me data at the higher Mauh nunibera were obtained firat when the air stream ua8 oooleet and ooaeequentQ the deaeity hlgheet

4、. The aeroaJnamio ohazacterlatloe am preeented for the undpttsilelmrpreeeatedin figure 14. Ngurealthroutfeatlvtmee (a, fig. 16); abore 0.80 the deoreaee in w wm the result of a more rapid 10s in flap effeotlvenees than atabillzer effeotlvenese. For at 0.875 Mach number, 125 and 600 pounds, respectiv

5、ely, are required. The drag increment of the horizontal tails is shown in figure 24 for varioue Mach numbere. The drag. of the swept tail is about 3.5 times greater than for the unswept tail at 0.60 Mach number, but this is largely due-to the greater area for the swept tail. At 0.875 Mach number, th

6、e drag of the swept tail is considerably . lower than that for the unswept tail plane. coNcLIIsIoIB The results of the high-eased wind-tunnel tests of a aemiepan horizontal tail ewept and unswept indicate the following: 1, The Mach number of lift diver-ace f 3r the unswept tail wan approximately 0.8

7、0, while that for the sweptcback tail was above 0.875. 2. Above a Mach number of 0.80, and at low angles of attack, the unewept tail plane showed a decided 10s in stabilizer and flap effectiveness and an increase in flap hingeinoment coefficient; whereas in campariaon the awept+ack tail showed littl

8、e change with Mach number to 0.875. 3. For the two hypothetical airplanes assumed in this report, one having an unswept and the other having a swept-back-horizontal tail, more area would be required for the swept horizontal tail plane than for the unswept tail for equal airplane static longitudinal

9、stability at low speed. The airplane with the swept tail would have higher stick forces and tail drag at the Mach number8 below the Mach number of lift divergence than the airplane with the unswept tail, J Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-

10、,-,-percent+hord line, degrees . . . . . o . . . o . . . Tail-plane area, square feet . . . . Span,Peet . . . . . . . . . . . . . Mean aerodynamic chord, feet . 0 . . Aspect ratio (baeed on full span) . Blap span station 4 Ordinate 00.767 -923 1.154 1.5% 2.175 2.642 3-a 3.664 4.142 4.500 i-s 5:m 4 .

11、g62 4.800 to?2 31652 3.115 2.597 2.087 1.577 1.066 -556 .046 11 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No. A7J22 Tunne/ wUMIl-TEE FOR AERONAUTICS Provided by IHSNot for ResaleNo reproduction or networking permitted without license fr

12、om IHS-,-,-NACA RM No.- A7J22 Fig. 2 Figurs 2.- Modal. mounted in the tind tunnel. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No. A7522 Fig. 3 8 6 I I I I I Swepf -3 .4 .5 .6 .7 .8 .9 Mach number, M Rgure 3- Varhfim of Reyno/ds number wi

13、fh Much number. Unswepf and swepf buck 455 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 4 a NACA RM No. A7522 1 .8 -.6 -8 -4 0 4 8 /2 Angie of attack, a, deg. 16 20 la) h-f, 0.40 F/gure 4.- Vtviation of /ft coefflcienf w/fb angle of affack. U

14、nswept i 6t, OS Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-8 NACA RM No. A?JZZ . Fig. 4 b I t I t I t twnoiacs. mhsotw . COMMITTEE FOR AERONAUTICS 43 -4 0 4 8 /2 16 Angie of affack, a, deg. Provided by IHSNot for ResaleNo reproduction or network

15、ing permitted without license from IHS-,-,-Fig. 4 c NACA RM No. A7522 .8 .6 -.6 -.8 I I I NATtONAL AOVISORY -8 -4 0 4 8 12 16 Angle of attack, a, deg. fc) M, 0.70 Figure 4. - Continued. c - Provided by IHS Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No.

16、 A7J22 Fig. 4 d .8 .6 -. 4 -.6 -.8 T/I/ I/ I 0 -5 I I t I Q 0 l-l -8 + -4 0 4 8 12 16 Ang/e of ffffack, a, deg. w at, 0.75 . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 4 e NACA RM No. A7J22 I .8 .6 -.6 -.8 I P I con I NATIONAL AUVKWRT IMITT

17、E FOR +ERONA+iTICS -8 -4 0 4 8 Angle of of fock , a, deg. /2 (e) M, 0.80 Figure 4. - Conthued. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No. A7J22 If) R#, 0. 825 /sure 4. - Continued. f .8 I -.6 L NATlONAL ADVISOR -.8 COMMITTEE FOR AERO

18、N, I I I I -8 -4 0 4 8 12 Angie of uffock , Ci , deg. Fig. 4 f Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 4 g NACA RM No. A7J22 .8 .6 I I I I NATIONAL ADWSORY J I I COMMITTEE FOR AERONAUTICS t I I -8 -4 0 4 8 /2 Angie of afruck, CY, de g W

19、M, 0. 85 Figure 4. - Continued. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No. A7J22 Ffg. 4 h .8 .6 -4 0 4 8 Angle of offack, CT, deg (h/ M, 0. 875 Figure 4. - Concbded. . Provided by IHSNot for ResaleNo reproduction or networking permit

20、ted without license from IHS-,-,-Fig. 5 a NACA RM No. A7J22 h -5 -.6 I I / a,-60 - 5-r NATIONAL ADViSORY L COU,MITTEE FOI P AERONAUTtCS I I I -5 - a, -40 Much number, M (al a,-SO; -49 Figure 5-Vuriaiibn of lift coefficient wifh Much number. . Provided by IHSNot for ResaleNo reproduction or networkin

21、g permitted without license from IHS-,-,-. NACA RM No. A7J22 Fig. 5 b - .- - .4 l-4 I 6f Idegl _- I I - tw E 5 25 0 72.5 -5 I I i I I I I -1 I l-4 i15 I I I I i 5 2.5 0 I . I I I-551 I .T .3 4 .5 .6 .7 .8 .S Mffcb number, M (3 a,-27 -I*. figure 5- Confhued. .4 -.4 Provided by IHSNot for ResaleNo rep

22、roduction or networking permitted without license from IHS-,-,-Fig. 5 c NACA RM No.:A7J22 .6 a, 00 .4 .5 .6 .7 .8 .9 Mach number, M .6 t . c . c Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No. A?JZZ .8 0 Fig. 5 d 3-T-l-I i15 5 2.5 .3 A .5

23、 .6 .7 .8 .9 Much number, M Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 5 e NACA RM No. A7J22 L-l 2.5 z5 5 2.5 0 ,dr; 3 .4 .5 -6 -7 .8 .9 Mach number, M (el a, So; 89 Figure 5.- Conchoed. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-