DOI码：10.1016/j.actaastro.2024.02.017
发表刊物：Acta Astronautica
摘要：The curved surfaces widely exist in three-dimensional inward-turning inlets and variable sectional isolators, which determine the downstream evolution of the converged flow generated by the crossing shock wave/boundary layer interaction, thereby affecting the start performance and combustion efficiency of the hypersonic vehicles. In this work, the converged flow subjected to the curved surfaces is experimentally studied with the nanoparticle-based planar laser scattering method and particle image velocimetry. Results show that the velocity profiles of the converged flow on the transverse plane can be normalized at different angles. The upstream separation size is found to be decreased by the downstream convex surface due to the reduction of backpressure, especially in large-radius cases, whereas the converged flow gradually becomes smooth ought to the dependence of the acceleration effect on the velocity. The concave surface shows an opposite effect on the converged flow, which further indicates that a downstream convex surface is preferred for hypersonic inlets to weakens the flow non-uniformity to improve the inlet performance.
合写作者：Yu-xin Zhao, Yong-yi Zhou, Gang He
第一作者：Yi-long Zhao
论文类型：期刊论文
通讯作者：Li-can Wang
学科门类：工学
一级学科：航空宇航科学与技术
文献类型：J
卷号：218
页面范围：209-220
是否译文：否
发表时间：2024-05-01
收录刊物：SCI