On shock layer method for the hypersonic flow problems

1987 ◽  
Vol 8 (5) ◽  
pp. 467-476
Author(s):  
Yuan Yi-wu
Keyword(s):  
Hypersonic Flow ◽  
Shock Layer ◽  
Flow Problems ◽  
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

MHD Control of the Hypersonic Flow in the Shock Layer Around a Body

2008 ◽  
Author(s):  
Andrea Cristofolini ◽  
Carlo Borghi ◽  
Gabriele Neretti ◽  
Andrea Passaro ◽  
Leonardo Biagioni
Keyword(s):  
Hypersonic Flow ◽  
Shock Layer

Magnetohydrodynamic Interaction in the Shock Layer of a Wedge in a Hypersonic Flow

2006 ◽  
Vol 34 (5) ◽  
pp. 2450-2463 ◽  
Author(s):  
C.A. Borghi ◽  
M.R. Carraro ◽  
A. Cristofolini ◽  
A. Veefkind ◽  
L. Biagioni ◽  
...  
Keyword(s):  
Hypersonic Flow ◽  
Shock Layer ◽  
Magnetohydrodynamic Interaction

The separation of Newtonian shock layers

1966 ◽  
Vol 26 (3) ◽  
pp. 563-572 ◽  
Author(s):  
J. R. Ockendon
Keyword(s):  
Hypersonic Flow ◽  
Shock Layer ◽  
Present Approach ◽  
Free Layer ◽  
Newtonian Theory ◽  
Direct Verification ◽  
Continuous Curvature ◽  
Shock Layers ◽  
Layer Solution

The separation points which occur in the Newtonian theory of hypersonic flow are treated by locally modifying the shock-layer equations. This approach leads to direct verification of the free-layer theory for separation on certain bodies with discontinuous curvature. Separation points on bodies with continuous curvature have already been treated by matching the upstream shock-layer solution to the downstream free-layer solution. The agreement that is found between these results and those of the present approach provides further confirmation of the free-layer theory.

Three-dimensional wings in hypersonic flow

1972 ◽  
Vol 54 (2) ◽  
pp. 305-337 ◽  
Author(s):  
R. Hillier
Keyword(s):  
Exact Solution ◽  
Hypersonic Flow ◽  
Shock Layer ◽  
Three Dimensional ◽  
Leading Edge ◽  
The Other ◽  
Calculation Methods ◽  
Conical Flow ◽  
Thin Shock Layer ◽  
Good For

Messiter's thin shock layer approximation for hypersonic wings is applied to several non-conical shapes. Two calculation methods are considered. One gives the exact solution for a particular three-dimensional geometry which possesses a conical planform and also a conical distribution of thickness superimposed upon a surface cambered in the chordwise direction. Agreement with experiment is good for all cases, including that where the wing is yawed. The other method is a more general approach whereby the solution is expressed as a correction to an already known conical flow. Such a technique is applicable to conical planforms with either attached or detached shocks but only to the non-conical planform for the region in the vicinity of the leading edge when the shock is attached.

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