一种宽速域乘波三角翼气动布局设计

doi:10.7527/S1000-6893.2023.28441

Abstract

Abstract:

To overcome the difficulty in inclusive consideration of the subsonic/transonic/supersonic/hypersonic aerodynamic performance of hypersonic vehicles in wide-speed range， we propose a wide-speed-range hypersonic aerodynamic configuration with a waverider forebody and a large swept delta wing. The design of the waverider forebody is based on the conical flow theory. The design Mach number is 5. The wide-speed range airfoil based on the surrogate model optimization design is arranged on a large swept wing with a small aspect ratio. The result shows that in subsonic flight， the configuration can improve aerodynamic performance using vortex lift at high angles of attack， with the lift-drag ratio maintained above 8. In supersonic flight， the double “S” shaped lower surface of the delta wing enables additional loading near the trailing edge of the aerodynamic configuration. In hypersonic flight， the shock wave characteristics at the leading edge of the waverider improve the lift-drag performance. The lift-drag ratio in the supersonic/hypersonic speed range is no smaller than 4.5 with good cruise performance. In addition， the longitudinal static stability in the wide-speed range is analyzed， showing that the aerodynamic center of the aerodynamic configuration is near the tailing edge.

Key words: wide-speed range, hypersonic, waverider, delta wing, vortex lift

CLC Number:

V211.3

Shusheng CHEN, Zhaokang ZHANG, Jinping LI, Cong FENG, Zhenghong GAO. Wide-speed aerodynamic layout adopting waverider-delta wing[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(23): 128441.

Figures/Tables 25

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马赫数	翼型	C_L	C_D	K
0.8	NASA_SC（2）_0404	0.641 003 0	0.015 086 1	42.489 643
0.8	宽速域优化翼型	0.868 432 3	0.015 825 4	54.878 107

4.0	NASA_SC（2）_0404	0.071 808 0	0.022 099 0	3.249 319
4.0	宽速域优化翼型	0.068 432 3	0.016 473 8	4.154 008

参数	取值
长、宽、高/m	8.65、7.74、0.75
宽速域机翼根梢比	4.3
前缘后掠角/（°）	45.0~76.8
垂尾高度/m	1.6
设计马赫数Ma	5
锥形流场半锥角/（°）	15
前缘钝化半径/mm	3

参数	稠密网格（参考）	中等网格		稀疏网格
参数	稠密网格（参考）	取值	误差/%	取值	误差/%
C_L	0.173 426	0.174 861	0.821	0.179 236	3.242
C_D	0.044 088	0.044 309	0.499	0.045 353	2.789
C_m	-0.230 822	-0.232 816	0.856	-0.238 322	3.147

高度/km	温度/K	压强/Pa	马赫数Ma
0	288.150	101 325.00	0.5
4	262.166	61 660.40	0.8
5	255.676	54 048.30	1.0
6	249.187	47 217.60	2.0
9	229.733	30 800.70	3.0
13	216.650	16 579.60	4.0
17	216.650	8 849.73	5.0
21	217.581	4 728.94	6.0
25	221.552	2 549.22	7.0

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Wide-speed aerodynamic layout adopting waverider-delta wing

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