高超声速飞行器构型的数值模拟、试验研究与优化设计

 综合升力体和乘波构型的气动性能优势，发展了一种高超声速飞行器前体气动构型的设计方法。运用该方法参考某高超声速飞行器气动布局方案，设计了一种高超声速飞行器气动布局。对该类高超声速气动布局进行了数值模拟、优化设计和试验研究；并研究了该类气动布局在高空飞行时，稀薄气体效应对气动性能的影响。数值模拟结果表明：构型前体预压缩面能够将高压气体封闭在构型下表面，实现了乘波构型的设计概念；优化设计结果表明，对于该构型宽展比应在0.4~0.6之间，通过优化升阻比至少有3%~5%的提高余地。对DSMC算法的碰撞模型和有效碰撞次数进行了改进，发展了临近空间飞行器气动性能模拟软件。研究结果表明，在临近空间区域，该类气动布局的升阻比特性略有下降，但仍旧保持了高升阻比的气动优势。

Numerical Simulation,Experiment and Optimization of Hypersonic Vehicle Configuration

A new design method of the hypersonic forebody is present based on the waverider and liftbody concept.By means of this method and taking as reference the configuration of a certain hypersonic vehicle,the configuration of a new hypersonic vehicle is designed.Numerical simulation,optimization,and experiment are conducted on this vehicle,and the impact of thin gas on hypersonic vehicle configuration aerodynamics is also studied.Simulation investigation shows that the pre-compressed surface of the forebody can ...