摘要:
介绍了10个压缩角模型在M数为2.011、2.504、3.015时产生的激波/边界层干扰的非定常特性的试验研究结果.压缩角模型的流向压缩角分别为15°、20°、24°,后掠角分别为0°、20°、40°、60°.实验结果表明:(a)所有无后掠压缩角和大多数20°后掠压缩角产生柱形干扰,而大后掠压缩角则产生锥形干扰;降低来流M数或增大模型后掠角有利于从柱形干扰转变为锥形干扰.(b)间隙区内的压力脉动出现低频峰值,此峰值随着模型后掠角增大或流向压缩角减小而减小;然而随着来流M数增大,此峰值在柱形干扰区减小,而在锥形干扰区略增大.对于锥形干扰,无粘激波的平均激波强度是控制其干扰特性的主要因素.
Abstract:
The paper presents the results of an experimental investigation on the unsteadiness of shock-wave/boundary layer interactions generated by ten ramps with streamwise angles of 15, 20 and 24 deg. and sweptback angles of 0, 20, 40 and 60 deg. respectively at Mach numbers of 2.011, 2.504 and 3.015. The results show that: (a) The interactions are cylindrical for all unswept and most of the 20 deg. sweptback interactions and quasi-conical for highly sweptback interactions. The decrease of Mach number or the increase of sweptback angle is favorable for the changeover from cylindrical to quasi-conical interaction. (b) The pressure fluctuations in the intermittent region show sharp low-frequency peak. The peak decreases with increasing sweptback or decreasing streamwise angle. However, with the increase of Mach number, the peaks decrease in cylindrical interactions but slightly increase in quasi-conical interactions. The average shock strength is a governing parameter in quasi-conical interaction.
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