旋成体导弹小展弦比舵面大偏度对称状态下非对称流动机理

doi:10.7527/S1000-6893.2016.0007

Abstract

Abstract:

In transonic wind tunnel test, regarding the problem of the asymmetric flow over a slender body of the low aspect ratio and a cutoff-delta wing tail vane in the symmetric states of small angle of attack, zero sideslip angle and large rudder angle, a series of force test, oil-flow and particle image velocimetry (PIV) test has been launched and analyzed. Based on the test data and observation of flow field, the details of the asymmetric flow, topological structure and spatial form have been studied and discussed in detail by numerical simulation. The results show that when a slender body with a low aspect ratio of control surface has large symmetric deflection angle, the wingtip vortex generated by the leading edge of control surfaces will interfere mutually for the close range between them, which would make the wingtip vortex go asymmetrically along the flow and the pressure of control surfaces maldistribution. Finally, it would lead to asymmetric flow and large yawing force over the slender body, which would affect the aerodynamic performance of a missile.

Key words: small angle of attack, large rudder angle, leading edge vortex, vortex breakdown, asymmetric vortices, rotated missile

CLC Number:

V211.43
V224

SHI Xiaojun, LI Yonghong, LIU Dawei, CHANG Lixia, YANG Ke. Asymmetric flow mechanism for small aspect ratio rudders with large deflection angles on rotated missile[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(9): 2690-2698.

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Asymmetric flow mechanism for small aspect ratio rudders with large deflection angles on rotated missile

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