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采用反设计方法研究双锥Bump压缩面设计技术,该方法实质是融合运动间断边界在运动网格条件下对轴对称欧拉方程组求解.为避免激波捕获法对激波型面位置求解误差,应用计算域分块的方法预估第2道激波,在此基础上采用流线追踪法生成Bump压缩面;结合平面机身设计一双锥Bump实例,运用计算流体力学仿真手段对其进行黏性数值模拟.研究结果表明:①该模型流场结构仍保持较强的附面层扫掠能力;②在来流马赫数为2.0条件下,相比传统的正圆锥乘波体Bump压缩面设计,新型设计方法可使Bump外压缩系统总压恢复系数提高0.04左右,为Bump进气道性能提高奠定基础.
In this paper, the reverse design method is used to study the design of Bump compression plane with double cone. The method is essentially to solve the axisymmetric Euler equations by moving the boundary of motion discontinuity in the condition of moving grid.In order to avoid the shock wave capture method, , The second shock wave is predicted by the block method of calculation domain. Based on this, the Bump compression surface is generated by the streamline tracing method. A double cone Bump example is designed based on the plane fuselage design, and the computational fluid dynamics simulation The numerical results show that: (1) the flow field structure of the model still maintains a strong sweep of the attachment layer; (2) compared to the traditional Bump compression surface design The new design method can increase the total pressure recovery coefficient of Bump external compression system by about 0.04, laying a foundation for the improvement of Bump inlet performance.