斜激波极值规律的边界层影响

doi:10.7527/S1000-6893.2019.23196

Abstract

Abstract: By using the boundary layer theory and the shock/expansion wave exact solutions, a new weighted method to balance Eckert's reference temperature and Illingworth-Stewartson transformation is put forward to model boundary layer effects on the oblique shock structure of a supersonic wedge flow. The CFD solvers of laminar and turbulent Navier-Stokes equations are separately applied to evaluate the new model. The errors of pressure ratio between CFD and theoretical values are less than 0.1% at a range of Mach number 1.2-2.4 and wedge angle 3°-20°. The theoretical model is used to study rules of minimum oblique shock strength. Optimal Mach numbers for minimum strength of oblique shocks will slightly increase when considering boundary layer effects. The amounts of increase of optimal Mach numbers are 0.001 5-0.003 3 for laminar flow and 0.002 8-0.006 1 for turbulent flow.

Key words: oblique shock waves, boundary layer thickness, shock strength, supersonic wedge flow, shock waves models

CLC Number:

V211.1

WEN Hao, SHI Aiming, YAN Rong. Boundary layer effects on rules of minimum oblique shock strength[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(12): 123196-123196.

References 30

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Boundary layer effects on rules of minimum oblique shock strength

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