基于数值模拟的超声速进气道附加阻力计算方法研究

Study on Calculation Method for Additive Drag of Supersonic Inlet Based on Numerical Simulation

基于CFD数值模拟,提出了一种超声速进气道附加阻力的快速计算方法。以某三波系二元超声速进气道为对象,开展了实例分析。计算结果表明,本文提出的附加阻力计算方法简单易行,便于推广应用于真实三维进气道设计中,可综合评估进气道捕获来流的气动特性,包括攻角特性和导弹前弹体的干扰特性等,具有明显的实用性和应用前景。

Based on CFD numerical model, a convenient algorithm of additive drag for supersonic inlet was presented. As an example, a certain three-shock two-dimensional supersonic inlet was simulated and analyzed. The results show that the algorithm presented in this paper is simple and feasible, and can be generalized to actual three-dimensional inlet design conveniently. Also, the aerodynamic performances of inlet can be synthetically evaluated, including angle of attack characteristics and body-inlet interference. This method has obvious practicability and applied future.