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弹箭与制导学报 >

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

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

控制翼前缘缝隙对层流分离的影响

  • 陈政 1 ,
  • 杨瑜 1 ,
  • 何小龙 1 ,
  • 倪招勇 2 ,
  • 王军旗 2
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  • 1 中国运载火箭技术研究院,北京 100076
  • 2 中国航天空气动力技术研究院,北京 100074

陈政(1989—),男,湖北咸宁人,工程师,硕士,研究方向:飞行器气动设计。

收稿日期: 2020-08-08

  网络出版日期: 2025-02-21

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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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摘要

针对类HTV-2高超声速飞行器控制翼诱导层流分离问题,数值研究了不同前缘缝隙宽度下控制翼诱导的层流分离流动特性,并在给定缝隙宽度下分析了舵偏角、攻角对分离的影响规律。结果表明:前缘缝隙抽吸效应对控制翼诱导层流分离影响明显,当缝隙增至一定值后,分离范围缩进幅度变大并呈线性减小趋势;给定缝隙宽度下,舵偏角减小,分离范围减小幅度越大,攻角增大,分离范围先增大而后缓慢减小。

关键词： 控制翼; 层流分离; 前缘缝隙; 数值模拟

本文引用格式

陈政 , 杨瑜 , 何小龙 , 倪招勇 , 王军旗 . 控制翼前缘缝隙对层流分离的影响[J]. 弹箭与制导学报, 2022 , 42(1) : 28 -31 . DOI: 10.15892/j.cnki.djzdxb.2022.01.006

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

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参考文献

原文顺序 | 文献年度倒序 | 文中引用次数倒序
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