NASA NACA-RM-A7K03-1948 Low-speed investigation of a small triangular wing of aspect ratio 2 0 I the effect of combination with a body revolution and height above a ground plane《展.pdf

1、Copy No. C L- RM No. A7K03 . 7 LOW-SPEED INVESTIGATfON OF A SMALL TRIANGULIIR WING OF ASPECT RATIO 2.0. I - THE EFFECT OF COMBINATION WITH A BODY REVOLUTION AND HEIGHT ABOVE A GROUND PLANE By Leonard M. Roae Ames Aeronautical Laboratory Moffett Field, Calif. I NATIONAL ADVISORY COMMITTEE FOR AERONAU

2、TICS Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.- . By Leonard M. Rose Lm-speed .wind-tunnel tests were conducted of a triangular wlng of aspect ratio 2,O 5th a sgnrmetrical double-wedge section having a maxim= thickness of 5 percent of the cho

3、rd at 20 percent of the chord. The wing was also tested in the presence of a ground plane. Additional data were obtained with conatankhord Bplit flaps and in combination with a body having a fineness ratio of 12.5. At low lift coefficients, relatively linear characteristics were obtained; whereas, a

4、t high lift coefficients the lateral+tability chazacteristics became fncreasingly nanlfnear. This tramition range of lift coefficients was marked by an abrupt chasge in longitudinal stability. The effect of the body was to reduce the severity of $he longitudinal“etabi1ity change with relatively litt

5、le effect on the lateral characteristice, Decreasing the heimt above the murid resulted in a considerable increase in the lift-curve slope and the maxim= lift, a reduction in induced drag, as well as a slisnamic pressure (he nlng to represent a volume approximately that required for efther a rocket

6、or turbo-jet installa- tion in a fighter airplane. The two wing looations relative to the body mre chosen to cover a range of poseible Etpplicatlona. The wlng was constructed of wood over a laminated steel spar; whereas the body was of whereas the effect of angle of attack was negligible for upward

7、flap deflections. Similar-, the fncremant of angle of attack at a constant IAPt coefficient, produced by the flaps, was small at high -lea of attack. Some insight into the usefulness of these flaps a8 balancing. devices my be obtaTned from figure 13 which fndicates litle effect of lift coefficient o

8、n the increment in pitchin; moment sttainable with upmrd.flap deflection. EoCTever, the results also indicate that this flap produced relatively small pitching moments, which would necessitate static nnrgins of less than 10 percent for operation at lift coefficients in excess of 0.8. Provided by IHS

9、Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-6 Ground Effect The effects of proximity to the ground on static longitudinal stability, lift-curve slope, and maximum lift coefffcient of the wing are eummariaed in figure 14 from the data presented in tables IV thro

10、ugh VI1 for the wing alone and the wing Kithout flap in the aft loastion CM the body.= Ihe effect of the ground plane on the atatic longitudinaL stability of the wing w and even with a height-to-epan ratio of 1.0, C- - . .“ . t B Provided by IHSNot for ResaleNo reproduction or networking permitted w

11、ithout license from IHS-,-,-CL - -0.592 -0488 - . 385 -a 302 - 208 - .120 - .021 . 061 m1S6 rn 259 . 353 . 435 . 534 0652 728 . e48 CL - 4 668 - . 473 381 - 276 - .204 - 117 -0031 m061 169 256 m350 461 t 548 662 768 856 -956 1.060 1 075 1.119 1 166 1.184 1.165 1 . 190 1.195 1.210 1.225 - 578 cn 0 16

12、06 0 1460 .1896 a 1200 ,1091 ,0876 ,0686 ,0778 -0551 .0416 . 0218 ,0178 0169 -.004& -. 0142 “0287 -8 0474 -00664 -a0643 “0820 -.0710 -. 1015 “0942 -0 0990 -. 1071 -m 1167 -,1127 -01380 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-HACA RM NO. A7m3

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14、saleNo reproduction or networking permitted without license from IHS-,-,-B Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-18 IWA RM NO. A703 I I f 4 c Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-

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16、1654 -. 1752 -. 1920 -. 1812 -.2022 f - a 0 1 2 3 4 6 8 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 - s, = -5O . re 6, * -15O 0 1 2 3 4 6 8 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 Provided by IHSNot for ResaleNo reproduction or networking permitted withou

17、t license from IHS-,-,-WCA RM Woo A7803 “. .-_ . .“ . .1. “.“ “- -“. L“.“. . “, B Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I i Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-22 NACA Rbi No0 A7

18、K03 I D f Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM No. Am3 . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-24 RACA RM no. am03 I I v 2 I I I“- 7 Provided by IHSNot for ResaleNo reprod

19、uction or networking permitted without license from IHS-,-,-XACA RM NO Am3 25 a m I ti 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-,-,-RACA RM No. AVO3

20、27 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-,-,-I?ACA. RM NO AZO3 29 ._ “ . . . . - _ - A- 1 I306 (a) Front view. (b) Side view. Figure 5.- Model inatallation for ground-lane tests. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-