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基于某飞机科研试飞,进行了飞机进气道出口边界层测量试验系统设计与搭建,完成了发动机工作在多种状态下的边界层测量。通过建立三维数值计算模型,进行了与试验对应工况下的边界层特性计算。计算结果和试验数据吻合性良好,误差较小。分析结果表明,随着发动机状态逐渐增大,进气道出口处的物理边界层厚度相应增大,位移边界层厚度减小,边界层对空气流量的影响逐渐降低。
Based on the test flight of an aircraft, the design and construction of the boundary layer measurement test system for the air intake of the aircraft was completed, and the boundary layer measurement of the engine working under various conditions was completed. By establishing a three-dimensional numerical model, the calculation of the boundary layer properties under the corresponding test conditions is carried out. The calculated results are in good agreement with the experimental data and the errors are small. The results show that as the engine state increases, the thickness of the boundary layer increases, the thickness of the boundary layer decreases, and the influence of the boundary layer on the air flow rate decreases.