马赫数可控的乘波前体与内收缩进气道气动匹配机理及流动特性研究

The aerodynamic matching design of forebody-inlet is a critical issue for hypersonic vehicle integrated design. The waverider forebody and inward turning inlet are focused extensively due to their special performance and design advantages. For the hypersonic vehicle of ventral intake layout, their aerodynamic matching design method is still at concept exploratory stage and is not applied to achieve aerodynamic integrated design. The innovative aerodynamic matching design theory of forebody and inlet is proposed in this project which achieves the internal and external flows waverider respectively based on the inversed external and internal conical basic flowfield with controlled Mach number distribution. Based on theoretical analysis, numerical method as well as wind tunnel experiments, the flow mechanism, wave system configuration, coupling property and overall performance of dual-warerider integrated scheme are studied. It would be aimed at disclosing their aerodynamic matching mechanism and provide the best matching approach. Finally, the theoretical principle is obtained for designing the high overall performance forebody-inlet integrated configuration.

前体与进气道的气动匹配是高超声速飞行器一体化设计的关键问题。乘波前体和内收缩进气道以各自独特的性能和设计优势备受关注，然而对于腹部进气布局的高超声速飞行器，二者的气动匹配设计方法仍处于概念探索阶段，匹配机理尚不明确，没有实现真正的气动一体化。本项目基于反设计的马赫数可控内/外锥形一体化基准流场，提出一种内/外流分别乘波的前体与进气道气动匹配设计新方法。通过理论分析、数值仿真和风洞试验相结合的方法，研究二者的流场特点、波系配置和耦合特性，分析关键设计参数对流场和总体性能的影响规律，揭示二者的气动匹配机理，获得匹配设计的最佳途径，最终为设计出综合性能优良的前体与进气道一体化构型提供新理论和方法。

高效的前体/进气道一体化设计方法是实现高超声速飞行的关键。本项目在典型高超声速飞行器工作条件下，以新的设计理念研究了腹部进气布局的马赫数可控乘波前体与内收缩进气道一体化设计方法，实现了二者分别独立乘波，进气道在非均匀进口条件下可以捕获全部流量。 主要完成内容：（1）对基于弯曲激波的外锥形基准流场设计方法进行研究，并据此提出两种前后缘同时可控的乘波体设计方法，尽可能保持出口均匀性，极大降低了与内收缩进气道一体化设计难度；（2）根据乘波前体与内收缩进气道一体化设计约束，完成马赫数可控内/外锥形一体化基准流场设计方法研究并编写了设计程序及验证；（3）根据给定的乘波前体和进气道设计参数，编写了乘波前体与内收缩进气道一体化设计程序并完成一体化构型的无粘设计及粘性修正，分析了设计点和非设计点的流场特点和耦合特性，设计结果符合预期；（4）完成非均匀进口的内收缩进气道试验模型设计及风洞试验研究，初步验证了马赫数可控的乘波前体与内收缩进气道一体化设计方法可行，设计点和非设计点的总体性能较高。总体而言，本项目揭示了前体和进气道的耦合特性和匹配机理，确定了匹配设计的基本途径，为设计综合性能优良的前体与进气道一体化构型提供了一种新方法，可为高超声速飞行器的研制提供重要技术支撑。