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Journal of Projectiles, Rockets, Missiles and Guidance >

2022 , Vol. 42 >Issue 1: 28 - 31

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2022.01.006

Influence of Leading Edge Gap of Control Wing on Laminar Flow Separation

  • CHEN Zheng 1 ,
  • YANG Yu 1 ,
  • HE Xiaolong 1 ,
  • NI Zhaoyong 2 ,
  • WANG Junqi 2
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  • 1 China Academy of Launch Vehicle Technology,Beijing 100076,China
  • 2 China Academy of Aerospace Aerodynamics,Beijing 100074,China

Received date: 2020-08-08

  Online published: 2025-02-21

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Abstract

Characteristics of hypersonic laminar separation induced by the control wing with leading edge gap of HTV-2 like configuration were investigated numerically. The investigation was made to determine the quantitative effect of the gap width, rudder deflection angle and angle of attack on separation. The result showed that the suction effect of the leading edge gap has an obvious effect on the laminar separation induced by the control wing. When the gap width increased, the separation rangedecreased linearly. Given the gap width, the smaller the rudder deflection angle, the greater the reduction of the separation range, and as the angle of attack increased, the separation range first increased and then decreased slowly.

Key words： laminar separation; control wing; leading edge gap; numerical investigation

Cite this article

CHEN Zheng , YANG Yu , HE Xiaolong , NI Zhaoyong , WANG Junqi . Influence of Leading Edge Gap of Control Wing on Laminar Flow Separation[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2022 , 42(1) : 28 -31 . DOI: 10.15892/j.cnki.djzdxb.2022.01.006

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