论文部分内容阅读
提出了一种高超声速内收缩进气道设计方法.在壁面马赫数分布规律给定的前提下,通过有旋特征线法反设计出轴对称基准流场,采用流线追踪技术来生成进气道的无黏型面并通过黏性修正得到进气道最终构型.对相同约束条件下设计的几种典型马赫数分布规律的基准流场进行对比分析,选取了反正切马赫数分布规律设计基准流场进而生成一种圆形进口的高超内收缩进气道,数值仿真结果显示:这种进气道具有良好的流量捕获特性和较高的压缩效率,表明提出的设计方法可行,拓宽了基准流场的选择范围,值得进一步深入研究.
A method of design of hypersonic internal contraction inlet was proposed. Under the premise of the Mach number distribution law of the wall, the axisymmetric reference flow field was designed by the spin line method, and the flow tracing technique was used to generate the inlet gas And the viscous correction to obtain the final configuration of the inlet.The comparative analysis of several typical Mach number distribution laws under the same constraint conditions was made and the law of the arc tangent Mach number distribution The reference flow field then generates a super-highly-inward-contraction intake port with circular inlet. Numerical simulation results show that this intake port has good flow-trapping characteristics and high compression efficiency, indicating that the proposed design method is feasible and broadens The scope of the reference flow field, it is worth further study.