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通过将经典Busemann设计方法和特征线反设计方法相结合,实现了对基准Busemann流场的气动截短,构建了一种具有基准Busemann流场截短压升规律的可控消波内转基准流场.通过数值模拟对可控消波内转基准流场及其追踪得到的“糖勺”型进气道进行了无黏验证分析.结果表明:特征线和CFD计算结果相吻合,可控消波内转基准流场设计合理可行.该基准流场继承了Busemann设计方法的高效压缩特性,且反射激波得到有效控制,基本实现消波,性能优于传统的截短Busemann流场.在设计点马赫数为7条件下,喉部截面参数均匀,增压比为18.32,总压恢复系数为0.878,压缩效率为0.936,隔离段内几乎无损失,出口气流匀直,气流角均在±0.4°以内.流线追踪得到的“糖勺”型进气道出口形状更加饱满,流动特征与可控消波内转基准流场基本一致.
By combining the classical Busemann design method with the anti-design method of the characteristic line, the aerodynamic truncation of the reference Busemann flow field is achieved, and a controllable wave cancellation reference with Busemann flow field is constructed Field. By numerical simulation, the non-viscous verification of the reference flow field and the “Sugar Spoon” air intake of the controllable wave-elimination internal reference was carried out. The results show that the characteristic curve coincides with the CFD calculation result, The design of controllable wave interpolation reference flow field is reasonable and feasible.The reference flow field inherits the efficient compression characteristic of Busemann design method, and the reflected shock wave is effectively controlled, and the basic realization of the wave cancellation is better than the traditional truncated Busemann flow field. Under the conditions of design Mach number of 7, the parameters of throat section are uniform, the pressurization ratio is 18.32, the total pressure recovery coefficient is 0.878, the compression efficiency is 0.936, there is almost no loss in the isolation section, the exit airflow is uniform and the airflow angle is ± 0.4 °, the shape of outlet port of “Sugar Spoon” inlet obtained by streamline tracking is more full, and the flow characteristics are basically the same as that of controllable wave elimination reference flow field.