北京航空航天大学学报

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燃气喷流干扰气动热数值模拟方法研究

林博希1,阎超2,李亚超2   

  1. 1. 北京航空航天大学
    2. 北京航空航天大学航空科学与工程学院
  • 收稿日期:2015-06-09 修回日期:2015-09-27 发布日期:2016-01-20
  • 通讯作者: 阎超

Numerical Simulation Method Research of Aerodynamic Heat Transfer of Hypersonic Jet

  • Received:2015-06-09 Revised:2015-09-27 Published:2016-01-20

摘要: 通过数值试验对比分析,主要探讨了两个问题,其一是使用空气喷流近似燃气喷流进 行数值模拟的方法,分析不同的喷流热力学参数匹配方法对喷流形态及热流分布的影响,其二是探讨喷 管几何形状导致的喷流出口速度型对热流分布的影响。研究表明,当采用空气喷流模拟燃气喷流时, 静 压比、动量系数参数决定流动结构,而考虑传热影响则需要额外选取相似参数进行热力学匹配。所研究 的四种相似参数变换方法中,静焓守恒方法热流计算结果最大,静温守恒方法热流计算结果最低。对第 二个问题研究表明,真实喷管几何形状的模拟程度对喷流膨胀形态发生影响,外流场发生相应的改变, 数值试验表明从截断喷管开始模拟较为合理。

关键词: 计算流体力学, 喷流, 相似准则, 数值模拟, 气动加热

Abstract: Navier-Stokes equations were solved to simulate the aerodynamic heating interactions of thruster’s hot gas jet and surface wall. This study tried to model real gas thruster exhaust gas by a methodology of ideal gas equivalence. The authors designed the procedure not only to match the original thruster performance in terms of average pressure, velocity, density values at the exit plane of thruster nozzle, but also to match thermodynamic values at the plane. The modeling of thruster internal geometries and transform of the ideal gas inflow boundary condition are studied. Several results are included in this paper to show how these approaches impact heat transfer. Simulation results show that different ideal gas thermodynamic equivalence impacts and thruster internal geometry modeling impacts are very big to heat transfer.

Key words: computational fluid dynamic , high temperature gas jet , similitude parameter , numericalsimulation, aerodynamic heat transfer

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