模拟飞行条件下的吸气式高超声速飞行器后体尾喷流干扰问题实验方案研究 *

Experiment Scheme Research on Afterbody Nozzle Plume Interferenece of Air-Breathing Hypersonic Vehicle Fly Condition

关键词:  高超声速  喷流干扰  相似参数  实验方案

Key words:  Hypersonic  Plume interfere  Similar parameter  Experiment scheme

摘要:

后体尾喷流干扰问题的准确模拟，对大尺度一体化飞行器气动力预测及后体尾喷流干扰机理认识至关重要。为了研究后体尾喷流干扰问题，本文基于相似理论，开展了模拟内外流相似参数的喷流干扰实验方案研究。提出了采用CF4+Air混合气体形式，模拟超然冲压发动机出口热态喷流的比热比等相似参数，建立了模拟真实条件下的喷流干扰问题的模拟方案。采用数值仿真软件对飞行条件和风洞条件下后体尾喷流干扰问题进行了数值模拟，从数值模拟结果来看，模拟内外流相似参数的喷流干扰实验方案是完全可行的。

Abstract:

The accurate simulation of afterbody nozzle plume interference is not only very important to predict the aerodynamic force of the large scale integrated vehicle，but also crucial to understand the mechanisms of the afterbody nozzle plume interference. Researches about the experiment scheme of plume interfere have been carried out based on similarity theory. The simulation of specific heat ratio of the hot plume of the scramjet outlet has been put forward by using the mixture gases of CF4 and air. The numerical simulation and validation have been accomplished for the afterbody flow disturbance problem of air-breathing hypersonic vehicle. By using numerical simulation software，numerical modeling for afterbody nozzle plume interference have been studied under flight condition and wind tunnel condition. According to the result of numerical simulation，this afterbody nozzle plume interference experiment scheme for the outflow of similar parameter in simulation is feasible.