机体尾缘形状对高压捕获翼构型亚声速特性影响

doi:10.7527/S1000-6893.2022.27215

Abstract

Abstract:

Based on the conceptual configuration combining the conical-cone airframe and flat plate capturing wing configuration， a series of different shapes were obtained by changing the side expansion angle of the trailing edge. The configuration was solved by computational fluid dynamics under the condition of typical subsonic flow （Ma=0.5）. The results show that， at the angle of attack of 0°， the spanwise section of the body tail widened， the expansion effect of the channel between the body and the capturing wing on the incoming flow was weakened， and the reverse pressure gradient on the upper surface of the body platform was reduced， which could effectively inhibit the flow separation phenomenon in the channel. In addition， the whole vehicle lift coefficient rose， and the drag coefficient first fell and then grew. With the increase of the angle of attack， the pressure on the upper surface of the round platform of the body climbed， while the range of the separation zone gradually declined until it disappeared. Furthermore， the spanwise widening of the tail section of the body could accelerate the disappearance of the separation zone. When the angle of attack increased further， the transverse flow appeared on the leeward side of the body， while the spanwise widening of the body tail section could delay the development of the transverse flow. As the angle of attack increased， the calculation results also show that the lift and drag of the whole machine were mainly attributed to the capturing wing. The aerodynamic force contributed by the body was not sensitive to the change of the angle of attack. The spanwise widening of the body tail section had little effect on the aerodynamic center of the whole vehicle. The geometry change of the lower surface of the body had no significant effect on the flow characteristics in the channel between the body and the capturing wing and the aerodynamic characteristics of the capturing wing.

Key words: high-pressure capturing wing, subsonic, flow characteristics, flow separation, trailing edge

CLC Number:

V211

Haoxiang WANG, Yao XIAO, Kaikai ZHANG, Guangli LI, Siyuan CHANG, Zhongwei TIAN, Kai CUI. Effect of body trailing edge shape on subsonic flow characteristics of high-pressure capturing wing configuration[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(6): 127215-127215.

Figures/Tables 33

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壁面法向第1层网格厚度	C_L	C_D	C_my
L×10^-5	-0.068 2	0.035 7	0.048 9
L×10^-6	-0.068 4	0.034 5	0.048 9

θ/（°）	F_x/N
θ/（°）	尾截面	圆台面
0	-831	-6 791
3	-1 278	-6 358
6	-1 696	-5 940
9	-2 017	-5 530
12	-2 513	-5 114

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Effect of body trailing edge shape on subsonic flow characteristics of high-pressure capturing wing configuration

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