高超音速飞行器前体优化设计方法研究

基于响应面法对高超音速飞行器前体进行气动优化设计,流场求解采用欧拉方程,并结合非结构动网格技术,便于适应复杂外形而且在每次外形改变后不必重新生成网格,有利于保证计算效率,响应面模型采用二次多项式来构造,数值结果表明由本文设计的前体/进气道布局结构简单,能获得更高的压缩率和总压恢复系数,以及更高的升阻比,该方法在多约束多目标条件下进行气动优化设计,设计质量较高,有一定的工程应用价值.

Opgitimization Method Research about the Forebody and Afterbody of Hypersonic Aircraft

In this paper,the optimization design of forward part of hypersonic aerocraft is based on the Response Surface Methodology(RSM).The flow solver takes use of Euler equations,combining with the technique of the unstructured dynamic meshes.The unstructured meshes are more fitful for the complicated geometry,and the technique of dynamic meshes is beneficial to computing efficiency,avoiding regenerating meshes.The quadratic polynomials are employed to construct the response surface.Numerical results indicate that the forebody/inlet designed by us is of simple configuration but it can give higher compression ratio,higher total pressure recovery coefficient and higher lift-drag coefficient,thus the methodology could be successfully applied to improve aerodynamic performance under the condition of specified multiple constraints and targets,achieving high quality of the design,and have certain engineering significance for application.