隐身外形飞行器用埋入式进气道的设计与风洞实验研究

本文为隐身外形飞行器用埋入式进气道发展了一套设计方法。该方法的理论基础是埋入式进气道进气机理和气动S弯概念,其关键技术包含通道中心线设计、横截面面积变化规律设计以及横截面形状设计等,各技术可以方便地用数学方法加以描述,整个方法易于编程实现。并结合一种隐身外形无人机提出了埋入式进气道方案,通过实验得到了此类隐身外形飞行器用埋入式进气道的气动特性。结果表明,所提出的埋入式进气道方案可行,所设计的模型进气道性能良好,所发展的设计方法合理。同时验证了埋入式进气道进气机理的正确性,也表明隐身外形飞行器与埋入式进气道的组合方案具有十分光明的应用前景。

A study of the design method and an investigation of high speed experiments for a submerged inlet under a stealthy shaped fuselage

A design method of submerged inlets under stealthy shaped fuselages is presented based theoretically on an air-admission mechanism of submerged inlets and a conception of aerodynamic S-shaped ducts in this paper.The key techniques of the method consist of the design of a centerline,the design of cross section areas,and the design of cross section figures.All these techniques can be depicted conveniently by mathematic methods,and the whole method can be realized conveniently by computer codes.In order to validate the feasibility of the design method,a project of a submerged inlet is put forward for a pre-research UAV with a stealthy shaped fuselage,and a sub-scale model is designed and produced using the method.Subsequently a lot of tests of the model in high subsonic wind tunnel are conducted and the effect of such aerodynamic characteristics as total pressure recovery and flow field distortion on the following four aerodynamic parameters,the mass flow rate,the free stream Mach number,the attack of angle,and yaw angle,are obtained for such submerged inlets from the experiments.The results show that the submerged inlet project for the UAV is feasible,and that the characteristics of the designed model can satisfy the overall requests.The results also indicate that the air-admission mechanism at high subsonic speed is correct,and that the design method in present paper is reasonable.Thus a conclusion can be drawn that a submerged inlet integrated with a stealthy shaped fuselage has a bright future for application.