内外流一体化“全乘波”气动设计理论和方法研究

With the aim of integrating a ramjet or scramjet with an airframe, a novel full waverider aerodynamic design theory and methodology for air-breathing hypersonic vehicles is proposed, using the method of characteristics (MOC), the streamline tracing technique, osculating axisymmetric, and osculating flowfield theories. Firstly, the methodology for the design of the novel osculating flowfield waverider is studied, and then the basic flowfield for the design of the waverider is optimized to improve the aerodynamic performances. Secondly, a novel inlet-airframe integrated axisymmetric basic flow model that accounts for both external and internal flows is designed using the method of characteristics and the streamline tracing technique. Finally, the design of the novel full waverider air-breathing hypersonic vehicles is generated from the integrated axisymmetric basic flow model using the streamline tracing technique. For this newly proposed design concept and for the specified flight conditions, not only the forebody of the vehicle but also its engine cowl and wings can ride on the bow shock wave, causing the bow shock wave to remain attached to the leading edge for the entire length of the vehicle. Thus, this integrated vehicle can take full advantage of the waveriders high lift-to-drag ratio characteristics and the ideal pre-compression surface for the engine, and it can become one the key techniques for ensuring the success of air-breathing hypersonic vehicles.

针对吸气式高超声速飞行器，本项目拟采用特征线理论、流线追踪技术、吻切轴对称理论以及吻切流场理论，开展新型内外流一体化“全乘波”气动设计理论和方法研究。首先，开展基于任意轴对称激波基准流场的吻切流场乘波体设计理论研究，通过优化基准流场提高乘波体性能。其次，开展适用于机体/进气道一体化设计的内外流一体化轴对称基准流场模型及其设计方法研究，通过该新型基准流场模型,在外流场乘波机体设计和内流场流线追踪进气道设计之间建立联系。最后，基于新型内外流一体化轴对称基准流场模型和吻切流场设计理论，发展一套新型内外流一体化全乘波设计理论。该设计理论在获得流线追踪进气道的同时，可以实现飞行器整个机体（包含前体、进气道唇口外罩及机翼）的完全"乘波"，使得一体化飞行器气动构型既具备流线追踪进气道的优良性能，又具备乘波体的高升阻比和高效预压缩气流特性，可为研制吸气式高超声速飞行器提供重要的气动设计理论和技术支持。

针对吸气式高超声速飞行器，本项目采用了特征线理论、流线追踪方法和吻切理论，开展了新型内外流一体化“全乘波”气动设计理论和方法研究。首先，开展了基于任意外压缩激波基准流场的吻切流场乘波体设计理论研究，通过优化基准流场模型，提高了乘波体性能。其次，开展了适用于机体/进气道一体化设计的内外流一体化基准流场模型研究，通过该新型基准流场模型，建立外流场乘波机体设计和内流场流线追踪进气道设计方法之间的联系。最后，基于新型内外流一体化基准流场模型和吻切理论，发展了新型内外流一体化“全乘波”气动设计理论。研究结果表明，该设计理论在获得流线追踪进气道的同时，可以实现飞行器整个机体（包含前体、进气道唇口外罩及机翼）的“乘波”，使得一体化飞行器气动构型既具备流线追踪进气道的优良性能，又具备乘波体的高升阻比和高效预压缩气流特性，可为研制新一代吸气式高超声速飞行器提供重要的气动设计理论和技术支持。