The selection of an appropriate turbulence/transition model is critical when simulating the hypersonic flows based on the Reynolds-averaged Navier–Stokes (RANS) equation. In particular, a deep understanding of the validity, reliability, and limitations of existing models is an essential prerequisite to facilitate their further development. This paper reports on the assessment of two models dedicated to hypersonic boundary layer transition analysis. Both models are compared with two other models that are widely used in this field. The double ramp and shock wave laboratory scramjet intake cases are used for the validation and evaluation of the predictive performance of both models via comparison against experimental data. The results reveal that the appropriate selection of the transition model is critical to the attainment of accurate results. Moreover, the forebody of the scramjet combustion propulsion-01 (SCP-01) flight vehicle, which is a research model, is analyzed as a case study. The air intake performance of the SCP-01, as predicted by four models, is compared and analyzed at different flight altitude and Mach number conditions. The results reveal that the accuracy of the prediction of boundary layer and separated flow transitions significantly affects the flow field and corresponding air intake performance. Furthermore, the uncertainty of results obtained using the two models increases significantly with an increase in altitude. Finally, the reliability and limitations of the transition models considered in this study are examined.

中文翻译：

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改进型超燃冲压发动机进气流分析模型的比较评估

在基于雷诺平均纳维 - 斯托克斯 (RANS) 方程模拟高超声速流动时，选择合适的湍流/过渡模型至关重要。特别是，深入了解现有模型的有效性、可靠性和局限性是促进其进一步发展的必要先决条件。本文报告了对两个专用于高超声速边界层过渡分析的模型的评估。这两种模型都与该领域广泛使用的另外两种模型进行了比较。双斜坡和冲击波实验室超燃冲压发动机进气案例用于通过与实验数据的比较来验证和评估两种模型的预测性能。The results reveal that the appropriate selection of the transition model is critical to the attainment of accurate results. 此外，作为研究模型的超燃冲压发动机燃烧推进-01（SCP-01）飞行器的前体作为案例进行了分析。SCP-01 的进气性能，如四个模型所预测的，在不同的飞行高度和马赫数条件下进行了比较和分析。结果表明，边界层和分离流转变的预测精度显着影响流场和相应的进气性能。此外，使用两种模型获得的结果的不确定性随着高度的增加而显着增加。最后，检查了本研究中考虑的转换模型的可靠性和局限性。SCP-01 的进气性能，如四个模型所预测的，在不同的飞行高度和马赫数条件下进行了比较和分析。结果表明，边界层和分离流转变的预测精度显着影响流场和相应的进气性能。此外，使用两种模型获得的结果的不确定性随着高度的增加而显着增加。最后，检查了本研究中考虑的转换模型的可靠性和局限性。SCP-01 的进气性能，如四个模型所预测的，在不同的飞行高度和马赫数条件下进行了比较和分析。结果表明，边界层和分离流转变的预测精度显着影响流场和相应的进气性能。此外，使用两种模型获得的结果的不确定性随着高度的增加而显着增加。最后，检查了本研究中考虑的转换模型的可靠性和局限性。结果表明，边界层和分离流转变的预测精度显着影响流场和相应的进气性能。此外，使用两种模型获得的结果的不确定性随着高度的增加而显着增加。最后，检查了本研究中考虑的转换模型的可靠性和局限性。结果表明，边界层和分离流转变的预测精度显着影响流场和相应的进气性能。此外，使用两种模型获得的结果的不确定性随着高度的增加而显着增加。最后，检查了本研究中考虑的转换模型的可靠性和局限性。