鸭式布局飞行器的翼体摇滚特性风洞试验

doi:10.7527/S1000-6893.2016.0042

Abstract

Abstract:

In order to study wing-body rock of the canard-configuration aircraft, different methods including free rolling motion, applying disturbance to free rolling motion, static force balance test, dynamic derivative test and smoke wire technique are used for the model which has canard wing, chine forebody, strake wings, main wings and a vertical fin in the wind tunnel. The roll angle time history is obtained by free rolling motion and disturbed motion, and then non-limit cycle motion is verified by static force balance test and dynamic derivative test. The results show that rolling motions of the canard-configuration aircraft model have several different central angles in the same side, and one center can jump to the other at the critical pitch angles. Finally, the basic flow field distribution of the canard-configuration aircraft model is described by flow visualization technique. The vortex system interaction mechanism and cause of wing-body rock of model are briefly analyzed at 0°rock angle.

Key words: canard wing, wing-body rock, non-limit cycle, dynamic derivative, flow visualization

CLC Number:

V211.7

WEI Dechen, SHI Zhiwei, GENG Xi, LIU Chao, ANG Haisong. Wind tunnel test for wing-body rock of canard-configuration aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(10): 3003-3010.

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大攻角动态实验装置: 中国, CN101929915B[P]. 2011-11-30.
SHI Z W, LI L Y, CHENG K M, et al. Wind-tunnel high attack angle dynamic testing device based on hy-brid mechanism: China, CN101929915B[P]. 2011-11-30(in Chinese).
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LIU W, YANG X L, ZHANG H X, et al. A review on investigations of wing rock problems under high angles of attack[J]. Advances in Mechanics, 2008, 38(2):214-218(in Chinese).
[22] BRANDON J M, NGUYEN L T. Experimental study of effects of forebody geometry on high angle of attack stability[J]. Journal of Aircraft, 1988, 25(7): 591-597.

Wind tunnel test for wing-body rock of canard-configuration aircraft

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