Record Details

Simulation of Hypersonic Shock/Turbulent Boundary-Layer Interactions Using Shock-Unsteadiness Model

DSpace at IIT Bombay

View Archive Info
 
 
Field Value
 
Title Simulation of Hypersonic Shock/Turbulent Boundary-Layer Interactions Using Shock-Unsteadiness Model
 
Creator PASHA, AA
SINHA, K
 
Subject NAVIER-STOKES EQUATIONS
TURBULENCE MODELS
LINE RELAXATION
WAVE
 
Description In hypersonic flows, the interaction of a shock wave with a turbulent boundary layer can result in flow separation and high aerothermal loads. In this paper, cone flare configurations with different flare angles and freestream Mach numbers are simulated using Reynolds-averaged Navier Stokes method, and results are compared with experimental data. The standard Spalart-Allmaras and k-omega turbulence models do not predict flow separation at the cone flare junction, and therefore yield a large deviation from the surface pressure measurements. Sinha et al. ("Modeling Shock-Unsteadiness in Shock/Turbulence Interaction," Physics of Fluids, Vol. 15, No. 8, 2003, pp. 2290-2297) proposed a shock-unsteadiness model to account for the effect of unsteady shock motion in a steady mean flow. The shock-unsteadiness correction damps turbulence amplification at the shock and results in significant improvement in predicting flow separation and reattachment. The flow topology in the interaction region, in terms of the pattern of shocks and expansion waves, is predicted correctly by the modified turbulence models. The resulting surface pressure distribution matches experimental data well.
 
Publisher AMER INST AERONAUTICS ASTRONAUTICS
 
Date 2014-10-15T13:25:42Z
2014-10-15T13:25:42Z
2012
 
Type Article
 
Identifier JOURNAL OF PROPULSION AND POWER, 28(1)46-60
http://dx.doi.org/10.2514/1.B34191
http://dspace.library.iitb.ac.in/jspui/handle/100/14999
 
Language en