基于全局/梯度优化方法的宽速域乘波-机翼布局气动设计

doi:10.7527/S1000-6893.2023.29596

Abstract

Abstract:

Wide-speed-range hypersonic vehicle， as a new strategic high ground in the aerospace field， face the challenge of balancing subsonic aerodynamic performance with transonic and supersonic as well as hypersonic characteristics due to the maximization of their flight speed and altitude range. To alleviate the high and low speed aerodynamic design conflict， this paper combines a global optimization approach based on surrogate models with a local optimization approach based on adjoint gradients to perform a multi-objective stepwise optimization of the layout parameters and airfoil shapes of the wide-speed-range configuration， spanning from the global to the local scale. The results indicate that under the constraints on subsonic lift coefficient and hypersonic drag coefficient， the layout parameter optimization method based on surrogate models can enhance the subsonic lift-to-drag ratio by 9.5%， while maintaining hypersonic aerodynamic performance. Furthermore， by selecting the configuration on the Pareto front of layout parameter optimization results with the optimal subsonic aerodynamic characteristics， a gradient optimization of the wing profile is performed using an adjoint gradient-based method. The optimization results demonstrate that the gradient optimization effectively enhances the drag characteristics during subsonic and hypersonic cruising states， leading to the geometric optimization of the airfoil as a dual-S shape that balances subsonic and hypersonic aerodynamic characteristics. Through the aforementioned optimization from layout parameters to profile parameters， the subsonic lift-to-drag ratio of the waverider-wing configuration increased by 12.4% compared to the original configuration， while the hypersonic lift-to-drag ratio improved by 6.2% compared to the original configuration.

Key words: waverider-wing configuration, wide-speed-range, surrogate model, adjoint method, stepwise optimization

CLC Number:

V211.3

Shusheng CHEN, Cong FENG, Zhaokang ZHANG, Ke ZHAO, Xinyang ZHANG, Zhenghong GAO. Aerodynamic design of wide-speed-range waverider-wing configuration based on global & gradient optimization method[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(6): 629596-629596.

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参数		取值
机身长度/m		13.4
翼展/m		18.0
翼根长/m		7.1
翼中拐折段长/m		2.6
翼梢长/m		1.7
后掠角/（°）	一段	63
后掠角/（°）	二段	35
设计马赫数Ma		5
设计几何参数	δ/（°）	13
	ψ/（°）	45
	θ/（°）	15
	k	5
前缘钝化半径/mm		20

翼型	状态	升力系数C_L	阻力系数C_D	升阻比K	力矩系数C_m
NACA64A204	Sub	0.677 4	0.009 9	65.17	0.077 6
NACA64A204	Hyp	0.048 5	0.014 0	3.36	0.015 4
OptFoil	Sub	0.731 4	0.008 2	89.19	0.102 2
OptFoil	Hyp	0.049 5	0.011 0	4.49	0.016 1

参数范围	H₁/mm	H₂/mm	γ/（°）	ψ/（°）	L₁/mm	L₂/mm
取值下界	1 200	1 200	20	20	2 400	1 200
取值上界	3 900	3 900	60	60	6 000	4 800

构型	Ma=0.8，α=2°				Ma=6.0，α=5°
构型	C_L	C_D	C_m	K	C_L	C_D	C_m	K
Base	0.303 0	0.023 8	-0.173	12.73	0.066 7	0.014 4	-0.030 3	4.62
Sample1	0.267 6	0.020 6	-0.167	12.95	0.065 7	0.014 0	-0.030 7	4.69
Sample2	0.275 5	0.020 4	-0.147	13.49	0.649 1	0.013 9	-0.031 3	4.67
Sample3	0.308 4	0.022 1	-0.179	13 .95	0.064 4	0.014 1	-0.028 1	4.56

构型	Ma=0.8，α=2°			Ma=6.0，α=5°
构型	C_L	C_D	K	C_L	C_D	K
Base	0.303 0	0.023 8	12.73	0.066 7	0.014 4	4.62
Sample3	0.308 4	0.022 1	13.95	0.064 4	0.014 1	4.56
Opt	0.291 9	0.020 4	14.31	0.066 7	0.013 5	4.91

Aerodynamic design of wide-speed-range waverider-wing configuration based on global & gradient optimization method

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