高超声速飞行器通流模拟方法与风洞验证技术

doi:10.7527/S1000-6893.2014.0122

Abstract

Abstract:

The wind tunnel validation tests for the reduced model of hypersonic vehicle are presented in this paper, by comprehensively utilizing wind tunnel force measurement, pressure measurement and fluctuating pressure measurement and analysis technique. The through-flow status and aerodynamic characteristics of the model at different inlet throat heights, and Reynolds numbers' effects on aerodynamic characteristics of the model in the given inlet throat height are studied by wind tunnel validation tests for the axisymmetric configuration model and lifting-body configuration model. The results show that the validation tests can effectively carry out through-flow conditions of inlet in different working statuses by means of wind tunnel simulation, and the purposes of studying aerodynamic characteristics of the model and optimizing the design of inlet are achieved. Furthermore, Reynolds numbers' effects on through-flow characteristics of the lifting-body configuration model are very slight, which can provide some foundation for actual flight condition simulation. The interrelated data processing and analysis methods can be used in the similar condition of the model designs of wind tunnel test.

Key words: hypersonic vehicle, axisymmetric inlet, lifting-body, through-flow simulation, wind tunnel tests, fluctuating pressure measurement, aerodynamic characteristics

CLC Number:

V211.7

ZHAO Zhongliang, YANG Xiaojuan, JIANG Weimin, CHEN Jianzhong, WANG Junlan. Through-flow Simulation Method and Wind Tunnel Validation Technique for Hypersonic Vehicle[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(11): 2932-2938.

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Through-flow Simulation Method and Wind Tunnel Validation Technique for Hypersonic Vehicle

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