中文摘要：

介绍了新型曲外锥乘波前体进气道（CCWI）的一体化设计方法,设计了理论构型并验证了设计方法。在几何参数约束下,获得了隔离段矩形出口,考虑前缘钝度及展向切除的乘波前体进气道构型。基于验证的数值仿真工具及计算网格策略,分析了几何切除及钝度和黏性对一体化构型性能的影响。在来流马赫数为4.0和6.0,迎角（AoA）在-4°～8°范围内,对设计的乘波前体进气道的基本性能进行了雷诺平均Navier-Stokes数值仿真,结果表明,该乘波前体进气道具有较高的流量捕获和总压恢复特性,隔离段出口参数满足超燃冲压发动机入口需求。该新型乘波前体进气道一体化方案及研究结果为一体化曲外锥乘波飞行器及一体化乘波推进流道的研究奠定了技术基础。

英文摘要：

The integration design method for the novel curved cone waverider forebody inlet（CCWI）is introduced,and a prototype CCWI is designed.The practical CCWI with rectangle exit isolator and leading edge bluntness is obtained under geometrical constrains.The cutting off and bluntness effects are evaluated using the validated numerical simulation tools.Reynolds average Navier-Stokes simulations are conducted at free stream Mach number Ma∞ =4.0,6.0,angle of attack（AoA）from-4°to 8°.The results show that the practical CCWI has high mass flow capture ratios and total pressure recovery at the simulation conditions.Its basic compression characteristics can meet the needs of scramjet combustors.The present study provides the possibilities for the integration study of CCWI with hypersonic vehicles and scramjet combustors.