Three-Dimensional Approximate Viscous Shock Layer Method for Hypersonic Flow over Blunt-Nosed Bodies

2003 ◽  
Author(s):  
M Dirin ◽  
M Maerefat ◽  
S.M.H. Karimian
Keyword(s):  
Hypersonic Flow ◽  
Shock Layer ◽  
Three Dimensional ◽  
Viscous Shock Layer ◽  
Layer Method

Approximate viscous shock-layer method for hypersonic flow over blunt-nosed bodies

1990 ◽  
Vol 27 (6) ◽  
pp. 597-605 ◽  
Author(s):  
A. C. Grantz ◽  
F. R. DeJarnette ◽  
R. A. Thompson
Keyword(s):  
Hypersonic Flow ◽  
Shock Layer ◽  
Viscous Shock Layer ◽  
Layer Method

High-altitude effects on three-dimensional nonequilibrium viscous shock-layer flows

1985 ◽  
Vol 22 (6) ◽  
pp. 614-619 ◽  
Author(s):  
D. J. Song ◽  
S. Swaminathan ◽  
Clark H. Lewis
Keyword(s):  
High Altitude ◽  
Shock Layer ◽  
Three Dimensional ◽  
Viscous Shock Layer

Hypersonic Viscous Shock Layer Calculation of Leeward Vortex-Induced Heat Transfer on a Sharp Cone at a High Angle of Attack

1977 ◽  
Vol 99 (2) ◽  
pp. 307-313 ◽  
Author(s):  
J. C. Adams
Keyword(s):  
Heat Transfer ◽  
Flow Field ◽  
Shock Layer ◽  
Vortex Flow ◽  
Local Heating ◽  
Three Dimensional ◽  
Leeward Side ◽  
Heating Rates ◽  
Viscous Shock Layer ◽  
Sharp Cone

An analysis technique applicable to the problem of leeward vortex-induced heat transfer on a sharp cone at high angles of incidence under hypersonic laminar flow conditions is presented. The analysis, a three-dimensional hypersonic viscous shock layer approach in conjunction with a numerical solution procedure, is shown to be both applicable and accurate based on comparisons of heat-transfer distributions, surface pressure distributions, and leeward meridian flow-field profile measurements taken in a hypersonic wind tunnel. Detailed calculations of the embedded vortex flow field on the leeward side of the cone are presented in such a manner as to clearly portray exactly how embedded vortex flow influences local heating rates.

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