中文摘要：

介绍了密切曲面内锥乘波前体进气道（Osculating Inward turning Cone Waverider Inlet，OICWI）的一体化设计方法，对该型乘波前体进气道的性能进行了数值分析，针对该型一体化乘波前体进气道完成了风洞试验研究。理论设计结果和设计状态无粘模拟结果一致，设计状态下的计算结果表明，前体进气道具有较高的总压恢复、较好出口流场均匀度及较高的流量捕获率。试验研究结果表明，改型一体化前体进气道在马赫数5～7条件下顺利启动，流场波系及压力分布同数值分析结果吻合。

英文摘要：

An integration design method of osculating inward turning cone waverider inlet （OICWI）are put forward in the paper.The performance of a typical inlet designed by the method has been validated by numerical simulation and wind tunnel tests.The waverider inlet integration design method of OICWI is conceived based on osculation axisymmetric and stream line tracing theory.The basic flowfield was firstly conducted by Method of Characteristics （MOC）and basic inner compression cone,then the inlet configuration was induced by streamline tracing technique. At the same time,theoretic characteristic of the inlet was calculated by MOC.The accurate per-formance of the OICWI is analyzed using Computational Fluid Dynamics （CFD）software.De-tailed flowfield simulation results were directly compared to experimental data to evaluate the accuracy of the numerical model and provide insight into the experimental flowfield behavior.The experiment study was fulfilled in China Aerodynamics Research and Development Center （CRADC）’sΦ0.5m hypersonic wind tunnel.The numerical/experimental results analyses show that the design method of OICWI is reasonable.The inviscid numerical simulation results agree well with theoretical design results in the design condition.The numerical simulation results show that OICWI has high pressure recovery in design and off-design condition.The flowfield be-havior obtained by CFD indicates that the isolate exit flow field has benign uniformity and OICWI has high flow capture ratio.The experimental results show that the OICWI can start from Mach number 5 to 7 .The flow field structure and pressure distribution agree well with numerical anal-ysis results.