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针对吸气式高超声速前体/进气道外形,利用在Φ600mm脉冲燃烧风洞和Φ0.5m高超声速风洞上获得的边界层转捩试验数据以及CFD流场计算结果,研究了前体边界层强制转捩区域的起始位置及其影响参数。采用回归分析方法,提出了一种适用于常规风洞和脉冲燃烧风洞、能够预测自然转捩和钻石型强制转捩起始位置的转捩准则。这个转捩准则考虑了边界层外沿的马赫数、雷诺数,以及总温/壁温比、来流气体平均分子量、粗糙元高度等影响转捩位置的主要因素;当粗糙元高度为0时,强制转捩准则退化为自然转捩准则。转捩准则成功推广到X-43A进气道风洞试验,预测最大偏差约为进气道全长的13%,可以应用到工程项目的转捩预测中。
Aiming at the shape of the aspirated hypersonic precursor / inlet, the experimental data of the boundary layer transition obtained on the Φ600mm pulsed combustion wind tunnel and the Φ0.5m supersonic wind tunnel were used to calculate the CFD flow field. The precursor boundary The initial position of the layer coercion zone and its influence parameters. Using the regression analysis method, a criterion that can be applied to conventional wind tunnel and pulsed combustion wind tunnel to predict the starting position of natural turning and diamond type forced turning is proposed. This transition criterion considers the Mach number, Reynolds number, and the total temperature / wall temperature ratio, the average molecular weight of the incoming gas, the height of the roughness element, and other factors that affect the position of the transition zone. When the height of the roughness element is 0 , The mandatory transfer criteria degenerated into a principle of natural transfer. The transition criterion was successfully applied to the X-43A inlet wind tunnel test. The maximum deviation predicted was about 13% of the total inlet length and could be applied to the project forecasting.