高超声速内转式进气道型面流场重构

doi:10.7527/S1000-6893.2019.23493

Abstract

Abstract: The distribution of flow field parameters of inward turning inlet is uneven. In order to improve the aerodynamic performances of inward turning inlet, a numerical simulation method is employed to study the flow field reconstruction of inward inlet based on the configuration. The results show that the centerline of the flow field reconstruction surface largely influences the flow field structure and flow characteristics of inlet. Under the given offset distance/length and slope at the end of centerline, the aerodynamic performances and the distribution of flow field parameters of the inlet at appropriate initial angle of centerline are improved. Compared with the basic inward turning inlet, at centerline initial angle 10°, the total pressure recovery at outlet and the back pressure capability of the inlet improved by 33.7% and 26.4%, and the self-starting Mach number decreased by 1.1. As the initial angle of the centerline increases, the streamwise vortex induced by the shock/sidewall boundary layer interaction weakens and the trajectory of streamwise vortex shifts to the cowl side from ramp, and the migration of flow with low total pressure to cowl on both sides enhances. Within the research scope, as the initial angle of centerline increases, the total pressure recovery of the outlet increases firstly and then decreases, and the self-starting Mach number decreases firstly and then remains constant.

Key words: inward turning inlet, flow characteristics, shock/boundary layer interaction, stream wise vortex, aerodynamic performance

CLC Number:

V211.3

WANG Weixing, ZHU Ting, ZHANG Rentao, LI Youchen. Flow field reconstruction of hypersonic inward turning inlet based on configuration[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(3): 123493-123493.

References 28

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Flow field reconstruction of hypersonic inward turning inlet based on configuration

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