A numerical study of oblique shock wave reflections over wedges in an ideal quantum gas

Shock Waves ◽  
2008 ◽  
Vol 18 (3) ◽  
pp. 193-204 ◽  
Author(s):  
J. C. Huang ◽  
T. Y. Hsieh ◽  
J. Y. Yang ◽  
K. Takayama
Keyword(s):  
Shock Wave ◽  
Numerical Study ◽  
Oblique Shock ◽  
Oblique Shock Wave ◽  
Quantum Gas ◽  
Wave Reflections ◽  
Ideal Quantum

scholarly journals A numerical study of oblique shock-wave reflections with experimental comparisons

1985 ◽  
Vol 398 (1814) ◽  
pp. 117-140 ◽  
Keyword(s):  
Shock Wave ◽  
Numerical Study ◽  
Wedge Angle ◽  
Quantitative Agreement ◽  
Oblique Shock ◽  
Computational Method ◽  
Oblique Shock Wave ◽  
Wave Reflections ◽  
Inviscid Flows ◽  
Reflection Transition

A direct comparison is made for several occurrences of oblique shock-wave reflections between interferometric results obtained at the University of Toronto Institute for Aerospace Studies (UTIAS) 10 cm x 18 cm hyper­-velocity shock tube and numerical results obtained by using a current computational method for solving the Euler equations. Very good qualitative agreement is obtained for equilibrium and frozen flow fields except in small regions where the experiments were dominated by viscous flow. The quantitative agreement is very close in some cases but can be out by 10–15% in cases with non-equilibrium flow or viscous structures or both. Additional parametrized sequences of calculations are presented to assess the utility of the present numerical method in constructing the various reflection–transition lines for perfect inviscid flows in the shock-wave Mach number, wedge-angle ( M s , θ w )-plane, and the validity of the ‘boundary-layer defect’ theory.

The interaction of an oblique shock wave with a laminar boundary layer revisited. An experimental and numerical study

1987 ◽  
Vol 177 ◽  
pp. 247-263 ◽  
Author(s):  
G. Degrez ◽  
C. H. Boccadoro ◽  
J. F. Wendt
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Laminar Boundary Layer ◽  
Stokes Equations ◽  
Numerical Study ◽  
Pressure Ratio ◽  
Oblique Shock ◽  
Oblique Shock Wave ◽  
Approximate Factorization ◽  
Pressure Distributions

An investigation of an oblique shock wave/laminar boundary layer interaction is presented. The Mach number was 2.15, the Reynolds number was 105 and the overall pressure ratio was 1.55. The interation has been demonstrated to be laminar and nominally two-dimensional. Experimental results include pressure distributions on the plate and single component laser-Doppler velocimetry velocity measurements both in the attached and separated regions.The numerical results have been obtained by solving the full compressible Navier-Stokes equations with the implicit approximate factorization algorithm by Beam & Warming (1980). Comparison with experimental data shows good agreement in terms of pressure distributions, positions of separation and reattachment and velocity profiles.

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