高超声速二维钝楔激波快速计算方法

Rapid Calculate Method for Shock of Hypersonic 2 - D Blunt Wedge

在飞行器气动外形优化设计问题的研究中,由于激波脱体距离和形状影响类乘波体飞行器表面压力分布和升阻比特性,考虑熵层效应的气动加热分析的必须条件之一。为了建立在高超声速范围内一致适用的工程激波计算方法,针对高超声速二维钝楔外形,采用Maslen发展的求解高超声速无粘激波层的反方法——薄激波层理论对激波以及壁面压力进行了研究。与数值仿真和其它工程方法的比较分析表明,薄激波层理论在激波脱体距离、形状以及壁面压力的预测上均具有较高的精度,且能适用于更大的马赫数范围。同时,薄激波层理论具有很好的计算效率,为优化高超声速乘波体飞行器气动外形设计、参数研究和大熵梯度下的气动加热分析等复杂问题的研究提供了依据。

The stand - off distance and shape of shock, which influences the pressure distribution and the lift - drag ration of the quasi - wavrider, is one of the pre - requisite conditions used to involve the entropy layer effection in aeroheating analysis. For providing an engineering shock calculation method which can be applicable for all hyper- sonic flight, the thin shock layer theory which is the inverse method of that developed by Maslen for hypersonic invis- cid shock layer, was introduced to investigate the hypersonic shock and wall pressure for the hypersonic 2 - D blunt wedge. Compared with the numerical simulation and other engineering method, the results show that the thin shock layer theory has preferable precision on the prediction of shock stand - off distance, shape and wall pressure. And, it can be applied in a wide range of mach number with appreciable efficiency, which can be used for many complex problems of hypersonic quasi - wavrider vehicle, such as the aerodynamic configuration design, the parameter study and the aeroheating analysis in great grads of entropy.