后缘射流对跨音速翼型激波振荡影响的数值模拟

周伟; 张正科; 屈科; 高超

doi:10.15892/j.cnki.djzdxb.2013.01.018

弹箭与制导学报 >

2013 , Vol. 33 >Issue 1: 135 - 137,144

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2013.01.018

弹道与气动力技术

后缘射流对跨音速翼型激波振荡影响的数值模拟

周伟 ,
张正科 ,
屈科 ,
高超

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西北工业大学翼型叶栅空气动力学国防科技重点实验室,西安 710072

周伟(1989-),男,四川人,硕士研究生,研究方向:计算流体力学应用。

收稿日期: 2012-05-21

网络出版日期: 2025-05-24

基金资助

重点实验室基金

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The Numerical Simulation of Trailing Edge Jet Effect on Shock Oscillation over Airfoil at Transonic Speed

ZHOU Wei ,
ZHANG Zhengke ,
QU Ke ,
GAO Chao

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Key Laboratory of National Defense Science an Technology of Airfoil, the Cascade Aerodynamic,Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2012-05-21

Online published: 2025-05-24

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摘要

跨音速翼型上激波与附面层相互干扰会导致激波在翼型上前后振荡,从而有可能引起机翼抖振。要对激波振荡进行控制主要应通过改变激波附面层相互作用区域的流动和后缘处尾流的流动来实现。通过数值方法模拟后缘射流对尾流流动的改变以及对跨音速翼型上激波振荡的影响。计算了不同射流速度下相对厚度为18%的双圆弧翼型绕流场,分析了后缘射流对激波振荡及翼型气动特性的影响。结果表明后缘射流对激波振荡有抑制作用,同时对翼型气动特性有一定改进作用。

关键词： 射流; 激波振荡; 跨音速; 附面层分离

本文引用格式

周伟 , 张正科 , 屈科 , 高超 . 后缘射流对跨音速翼型激波振荡影响的数值模拟[J]. 弹箭与制导学报, 2013 , 33(1) : 135 -137,144 . DOI: 10.15892/j.cnki.djzdxb.2013.01.018

Abstract

The shock/separated boundary layer interaction on transonic airfoil may result in shock oscillation which in turn may lead to wing buffet. Shock oscillation over transonic airfoil might be controlled by modifying the flow in the shock/boundary layer interaction region and by manipulating the wake flow near airfoil trailing edge. The effects of trailing edge jet on the airfoil wake flow and on shock oscillations were simulated by numerical methods. The flow around an 18% thick biconvex airfoil with various jet velocities were computed, and the effects on shock oscillation and aerodynamic characteristics were analyzed. It is found that the trailing edge jet will suppress the shock oscillation and improve the aerodynamic characteristics of airfoil.

Key words： jet flow; shock oscillation; transonic; boundary layer separation

参考文献

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[2]	Gibb J. The cause and cure of periodic flows at transonicspeeds[C] //Proceedings 16th Congress of the InternationalCouncil of the Aeronautical Sciences, Jerusalem, Israel,August-September, 1988: 1522 – 1530.
[3]	Raghunathan S, Gillan MA, Cooper RK, et al. Shock os-cillations on biconvex aerofoil J. Aerospace Science andTechnology, 1999, 3(1):1-9.
[4]	Xiong J, Nezhad ST, Liu F. Computation of self-excitedunsteady transonic flow of an airfoil in a channel usingURANS and DES, AIAA 2010-5109 R.2010.
[5]	Lee B HK. Self-sustained shock oscillations on airfoils attransonic speeds[C] //Progress in Aerospace Sciences,2001:147-196.
[6]	马侠, 蒋金贵, 张绵纯,等. 跨音速翼型上的激波/边界层干扰自适应控制计算. 应用力学学报, 1994, 11(1): 60-65.

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