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随着航空宇航技术的研究及应用不断发展,进气道作为高速飞行器的重要组成部分,其性能对高速飞行影响显著。首先建立进气道三维数值计算模型,运用计算流体动力学理论(CFD)计算方法,研究了总压恢复系数随攻角、侧滑角和马赫数等不同工况的变化情况,进而研究各工况下进气道性能,为进气道性能优化、评价和再设计提供了方法和依据。
As the research and application of aerospace technology continues to evolve, the inlet duct, as an important part of a high-speed aircraft, has a significant impact on high-speed flight performance. Firstly, the three-dimensional numerical model of inlet was established. The CFD calculation method was used to study the variation of total pressure recovery coefficient with different working conditions, such as angle of attack, side slip angle and Mach number, Under the condition of the intake port performance, it provides the method and basis for the optimization, evaluation and redesign of the intake port performance.