高超声速流动中侧向喷射气动相互作用效应的CFD分析

P. Srinivas, Rishi Sharma, D. Yadav, G. Murty
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引用次数: 2

摘要

再入飞行器在再入过程中通常采用反作用力控制系统来提供必要的临界力。本文研究了由反作用控制系统引起的侧向射流对再入飞行器气动特性特别是稳定性方面的影响。研究了从飞行器表面向高超声速流中正常注入圆形音速空气射流的再入飞行器背风侧侧向射流相互作用的cfd分析。在自由流马赫数8.1下,对攻角为0、2、5、8和10度的横向射流相互作用进行了系统的数值分析。并将20度迎角时的压力分布与实验数据进行了比较,验证了该方法的正确性。通过比较有无侧向射流时气动特性沿长度的变化,研究了侧向射流对气动特性的影响。气动特性沿轴向的气动系数变化。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
CFD Analysis of the Aerodynamic Interaction Effects Due to Lateral Jet Injection in to Hypersonic Flow
Reentry vehicle often uses reaction control system for providing necessary critical forces during reentry. The effect of lateral jet due to reaction control system on aerodynamic characteristics especially stability aspect of a reentry vehicle has been investigated .CFD analysis of the interaction of a lateral jet on Leeward side has been investigated on a reentry body with a circular sonic air jet injected normally in to hypersonic flow from the body surface. A systematic numerical analysis for a lateral jet interaction was performed at angles of attack 0, 2, 5, 8, and 10 degrees at free stream Mach number 8.1. The methodology has also be verified by comparing the pressure distribution at an angle of attack of 20 degrees with experimental data. The effect of lateral jet on aerodynamic characteristic has been studied by comparing the variation of aerodynamic characteristic along the length with and without lateral jet. The aerodynamic coefficients variation of aerodynamic characteristics along the axial l...
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