一种隐身外形弹体下埋入式进气道的进气机理与低速实验研究

Air-admission mechanism and low speed tunnel test of a submerged inlet with low RCS missile body

对一种低雷达散射外形弹体下埋入式进气道的某设计方案进行了进气机理研究和低速气动实验研究。实验模型为低雷达散射的多边形弹体和埋入式进气道的组合。由于平面上的埋入式进气口进气困难,因此模型采用了由矩形进口逐渐过渡为圆形出口的进气道。通过对模型的CFD流场数值分析揭示了该平面上埋入式进气道的进气机理是进口侧棱产生涡,涡卷吸进气。通过对模型的低速气动实验研究获得了该埋入式进气道的流量特性以及气动特性随迎角和侧滑角的变化规律。结果表明,本研究所给出的进气道在低速气动实验时具有良好的流量特性和气动性能,较好地解决了埋入式进气道在平面弹身上难以进气的问题。因此可以推断,本文提出的埋入式进气道与低雷达散射弹身一体化设计具有光明的应用前景。

An investigation of a submerged inlet with low RCS missile body of which the cross section is pentagonal is presented in this paper.Since the underside surface of the body is a plane in which the entrance of the submerged inlet is,it may lead the flow characteristics in the inlet to be bad.In the study,a Sshaped duct is designed first and the cross section of the duct is changed from rectangle at the entrance to circularity at the outlet.Then the submerged inlet can be realized after cutting off the part of the Sshaped duct outside of the body.After a series of computational work,the airadmission mechanism of the inlet is revealed:it is the two side edges of the rectangular entrance that generate vortices,and it is these vortices that convolve air into the inlet.Following,lots of experiments in low speed wind tunnel were conducted to test the feasibility of the integrative configuration.The test results show that the submerged inlet with a low RCS missile body has the sound flow characteristics,which indicates that the integrative design is successful and has a bright future for the application.