Busemann pressure rise distribution based design of inward turning basic flowfield with controlled and cancelled shock waves

An inward turning basic flowfield with controlled and cancelled shock waves was proposed based on Busemann pressure rise distribution by combining the method of Busemann design and method of characteristics. By this method, the aerodynamic truncation of the basic Busemann flowfield was realized. Then the inward turning basic flowfield with controlled and cancelled shock waves and a streamline traced sugar-scoop inlet were numerically simulated by inviscid CFD. The results show that the flowfield results solved by method of characteristics agree well with CFD, indicating that the inward turning basic flowfield with controlled and cancelled shock waves is reasonable and feasible. It inherits the high compression efficiency of Busemann design and keeps the reflected shock waves under control, and the shock cancellation is almost achieved, so it performs better than the classical truncated Busemann inlet. At the design point of Mach number 7, the flow parameters of throat section are uniform, with a pressure ratio of 18.32, a total pressure recovery coefficient of 0.878 and a compression efficiency of 0.936. There is almost no reduction of total pressure in isolator. The outflow is straight and uniform and the flow angle deviation is all within ±0.4 degree. The traced sugar-scoop inlet has a more circle-like outlet and inherits the characterisitics of inward turning basic flowfield with controlled and cancelled shock waves.