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采用特征线方法设计了具有直线初始激波、内收缩段消除激波反射、出口参数均匀可控的基准内锥流场。基于密切内锥(Osculating Inward turning Cone,OIC)乘波体设计方法,发展了密切内锥乘波前体进气道(Os-culating Inward turning Cone Waverider Inlet,OICWI)一体化设计技术。基于基准内锥流场和前体进气道一体化设计技术,设计了密切内锥乘波前体进气道。采用数值方法对设计的密切内锥乘波前体进气道进行了计算分析,结果表明无粘流场结构和基准内锥流场吻合,无粘模拟结果和理论设计结果吻合。粘性数值模拟结果显示一体化进气道具有较高的流量捕获率及总压恢复特性,进气道出口流场分布均匀。
Using the method of characteristic line, a cone-shaped taper flow field with a straight initial shock line and an internal shrinkage section for eliminating shock wave reflection and uniform outlet parameter control is designed. Based on the Osculating Inward Turning Cone (OIC) multiplying wave body design method, an integrated design technique of the Osculating Inward Turning Cone Waverider Inlet (OICWI) is developed. Based on the reference inner cone flow field and precursor inlet integrated design technology, the inlet of close inner cone multiplier wave precursors was designed. The numerical analysis is conducted on the inlet of the close-in cone-shaped wavefront precursors. The results show that the structure of the non-stick flow field is consistent with the cone flow field inside the reference. The results of the non-stick simulation are consistent with the theoretical design results. The viscous numerical simulation results show that the integrated inlet has high flow rate capture rate and total pressure recovery characteristics, and the inlet flow field distribution is uniform.