Abstract: The basic inward turning cone was designed by Methods of Characteristics which has straight initial shock wave and inner compression section shock wave canceled, flow parameters controllable and uniformity exit inner compression section. The intergrated Osculating Inward turning Cone Waverider Inlet(OICWI) design methods were developed based on the Osculating Inward turning Cone(OIC) waverider design methods. Based on the designed basic inward turning cone flow field and OICWI design methods, an OICWI was designed. The OICWI’s performances were analyzed by numerical ways. The inviscid results show that numerical simulation results agree well with design results and flow field structures are consistent with basic inward turning cone flow field. The viscous results show that OICWI has high pressure recovery and flow capture characteristics. The flow field parameters are uniform in the inlet exit plane. 

Key words: Supersonic inlet; Wave rider forebody; Intergrated design; Osculating inward turning cone; Streamline tracing

摘要： 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(Osculating 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。 

关键词: 超声速进气道;乘波前体;一体化设计;密切内锥;流线追踪