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

作　　者：蔡飞超[1] 陈玉春[1] 陈凤明[2] 闫斌斌[2] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]西北工业大学航天学院,西安710072

出　　处：《科学技术与工程》2013年第15期4270-4274,共5页Science Technology and Engineering

基　　金：国家自然科学基金(61104195)资助

摘　　要：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.

关 键 词：超声速 进气道 附加阻力 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]