圆形出口内转式进气道流动特征

doi:10.7527/S1000-6893.2015.0108

Abstract

Abstract:

The flow characteristics of an inward turning inlet are numerically studied. The results show that at design condition, the secondary flow near the wall is induced by the cowl shock and the streamwise vortex is generated in isolator, which will cause the flow with low velocity and low total pressure to accumulate. The distribution of the aerodynamic parameters at the isolator outlet is even, which will weaken the back-pressure capacity of inlet. With angle of attack, the compression shock departs the leading edge of cowl lip and the shock wave structure changes. The middle part of the shock wave presents quasi-two-dimensional feature in the span-wise. The shock wave is weak on the two sides of compression surface and the expansion waves occur in local zone. The streamwise vortex presents in the compression section without viscosity with angle of attack, and this streamwise vortex will enhance the transfer of the flow with high total pressure from the core flow region to the wall, so the evenness of flow at the outlet of isolator is improved under viscosity.

Key words: streamwise vortex, shock wave structure, flow characteristics, inward turning inlet, numerical simulation

CLC Number:

V211.3

WANG Weixing, GUO Rongwei. Flow characteristics of an inward turning inlet with circular outlet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(2): 533-544.

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Flow characteristics of an inward turning inlet with circular outlet

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