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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。
The integrated design method of the new Quasar Convective Wavelet Precursor Inlet (CCWI) was introduced, the theoretical configuration was designed and the design method was validated. Under geometrical constraints, the rectangular exit of the isolation section was obtained, considering the leading edge ductility and the fringe-cut MWW precursor inlet configuration. Based on the numerical simulation tools and computational grid strategy, the effects of geometrical ablation and ductility and viscosity on the performance of the integrated configuration are analyzed. The Navier-Stokes numerical simulation of Reynolds-averaged Navier-Stokes equations was carried out on the basis of the inlet gas flow path with mach numbers 4.0 and 6.0 and AoA ranging from -4 ° to 8 °. The results show that The inlet of the wavefront precursor has high flow trapping and total pressure recovery characteristics, and the outlet parameters of the isolation section meet the requirements of scramjet engine inlet. The integrated scheme and research results of inlet of new wavefront precursors laid the technical foundation for the research on the integrated curved outer cone propellant aircraft and the integrated wave propagation advancing flow channel.