Journal Publications

DOI number:10.1016/j.actaastro.2024.02.017

Journal:Acta Astronautica

Abstract: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.

Co-author:Yu-xin Zhao, Yong-yi Zhou, Gang He

First Author:Yi-long Zhao

Indexed by:Journal paper

Correspondence Author:Li-can Wang

Discipline:Engineering

First-Level Discipline:Aerospace Science and Technology

Document Type:J

Volume:218

Page Number:209-220

Translation or Not:no

Date of Publication:2024-05-01

Included Journals:SCI