基于后掠唇罩的入射激波/边界层干扰流动控制方法

doi:10.7527/S1000-6893.2022.28091

Abstract

Abstract:

The strong cowl shock wave/boundary-layer interaction within the hypersonic inlet induces large scale separation and strong energy loss. To address this problem， we propose a flow control method for impinging shock wave/boundary-layer interaction based on the swept-back cowl configuration. The flow characteristics with swept/unswept cowl configurations were numerically revealed with the incoming Mach number of 3.0 and the cowl compression angle of 18°. The results show that the length-scale of the separation， induced by the swept-back cowl shock wave/boundary-layer interaction， increases along the spanwise direction. By utilizing the lateral pressure gradient resulted from three-dimensional swept shock waves， it forces the low momentum flow to migrate from the symmetry plane to the sidewall， leading to an over 50.6% diminution of the separation bubble compared to that of the unswept cowl configuration. In addition， the pressure distribution in the interaction region shows an elliptical similarity with the center of separation line curvature as the virtual center.

Key words: cowl shock/boundary layer interaction, swept-back cowl configuration, separation bubble, flow control, elliptical similarity

CLC Number:

V228.8

Canmin LI, Hexia HUANG, Gang LIANG, Jinghao LYU, Jia CAI, Huijun TAN. Flow control method for impinging shock/boundary-layer interaction based on swept-back cowl configuration[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(16): 128091-128091.

Figures/Tables 17

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Flow control method for impinging shock/boundary-layer interaction based on swept-back cowl configuration

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