高超声速飞行器自适应减阻盘动态减阻机理

doi:10.7527/S1000-6893.2022.26633

Abstract

Abstract:

To address the drag reduction problem of hypersonic aircraft during dynamic maneuver， the dynamic drag reduction effects of self-aligned aerodisks are studied based on the unsteady flow/kinematics coupled method and dynamic hybrid grid generation technique. Drag characteristics of aircraft are also analyzed with variation of different parameters to provide reference for hypersonic aircraft design and optimization. In addition， differences in dynamic drag reduction mechanisms between the fixed and self-aligned aerodisks are discussed. The numerical results show that self-aligned aerodisks， always aligning with the incoming flow， are helpful to maintain the structure of recirculation zone during maneuvering. Moreover， self-aligned aerodisks are able to reconstruct the flow field even at a high angle of attack. Compared to that of fixed aerodisks， the drag reduction effect of self-aligned aerodisks can be largely improved in more than 80% of the oscillation period. Furthermore， the superiority of the self-aligned method clearly increases with the growing pitch angle.

Key words: hypersonic aircraft, self-aligned aerodisk, drag reduction mechanism, dynamic hybrid grid technique, unsteady numerical simulation

CLC Number:

V211.3

Rong HAN, Wei LIU, Xiaoliang YANG. Dynamic drag reduction mechanism of self-aligned aerodisks on hypersonic aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(4): 126633.

Figures/Tables 21

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物理量	数值
来流密度ρ_∞/（kg·m^-3）	0.010 6
来流水平速度v_∞/（m·s^-1）	1 363.36
来流动力黏度μ_∞/（kg·m^-1·s^-1）	0.964×10^-5
来流总压P₀/Pa	425

特征	第1层网格高度/mm	网格雷诺数Re_grid
粗网格	0.03	46
中等密度网格	0.003	4.6
密网格	0.000 3	0.46

编号	第1层网格高度/mm	湍流模型	阻力系数
1	0.03	SST	1.526 6
2	0.03	SA	1.526 4
3	0.003	SST	1.516 3
4	0.003	SA	1.515 9
5	0.000 3	SST	1.503 0
6	0.000 3	SA	1.501 2
试验值方正汇总行^［20］			1.462

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Dynamic drag reduction mechanism of self-aligned aerodisks on hypersonic aircraft

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