Shock wave incident on a wedge moving with supersonic velocity

1972 ◽  
Vol 3 (4) ◽  
pp. 111-111
Author(s):  
G. M. Arutyunyan
Keyword(s):  
Shock Wave ◽  
Supersonic Velocity ◽  
Wave Incident ◽  
Shock Wave Incident

Wave reflexion near a wall

1951 ◽  
Vol 47 (3) ◽  
pp. 528-544 ◽  
Author(s):  
A. Robinson
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Velocity Profile ◽  
Shear Layer ◽  
Continuous Wave ◽  
Rigid Wall ◽  
Main Flow ◽  
Supersonic Velocity ◽  
Main Stream ◽  
Numerical Examples

AbstractThe field of flow due to a shock wave or expansion wave undergoes a considerable modification in the neighbourhood of a rigid wall. It has been suggested that the resulting propagation of the disturbance upstream is largely due to the fact that the main flow in the boundary layer is subsonic. Simple models were produced by Howarth, and Tsien and Finston, to test this suggestion, assuming the co-existence of layers of uniform supersonic and subsonic main-stream velocities. The analysis developed in the present paper is designed to cope with any arbitrary continuous velocity profile which varies from zero at the wall to a constant supersonic velocity in the main stream. Numerical examples are calculated, and it is concluded that a simple inviscid theory is incapable of giving an adequate theoretical account of the phenomenon. The analysis includes a detailed discussion of the process of continuous wave reflexion in a supersonic shear layer.

Interaction of a shock wave with a mixing region

1960 ◽  
Vol 7 (3) ◽  
pp. 321-339 ◽  
Author(s):  
N. Riley
Keyword(s):  
Shock Wave ◽  
Numerical Solutions ◽  
Fourier Transforms ◽  
Equations Of Motion ◽  
Simple Wave ◽  
Incident Shock ◽  
Incident Shock Wave ◽  
Wave Number ◽  
Large Wave ◽  
Shock Wave Incident

The interaction of a simple wave, in steady supersonic flow, with a two-dimension mixing region is treated by applying Fourier analysis to the linearized equations of motion. From asymptotic forms for the Fourier transforms of physical quantities, for large wave-number, the dominant features of the resulting flow pattern are predicted; in particular it is found that a shock wave, incident on the mixing region, is reflected as a logarithmically infinite ridge of pressure. For two particular Mach-number distributions in the undisturbed flow, numerical solutions are obtained, showing greater detail than the results predicted by the asymptotic approach. A method is given whereby the linear theory may be improved to take into account some non-linear effects; and the reflected wave, for an incident shock wave, is then seen to consist of a shock wave, gradually diminishing in strength, followed by the main expansion wave.

Perturbation evolution at a metal-metal interface subjected to an oblique shock wave: Supersonic velocity of the point of contact

2003 ◽  
Vol 48 (8) ◽  
pp. 1001-1008 ◽  
Author(s):  
O. B. Drennov ◽  
A. L. Mikhailov ◽  
P. N. Nizovtsev ◽  
V. A. Raevskii
Keyword(s):  
Shock Wave ◽  
Oblique Shock ◽  
Supersonic Velocity ◽  
Oblique Shock Wave ◽  
Metal Interface ◽  
Metal Metal

The condition for the detachment of the shock wave from a wedge in a supersonic stream

1948 ◽  
Vol 44 (2) ◽  
pp. 298-300
Author(s):  
D. C. Pack
Keyword(s):  
Shock Wave ◽  
Present Note ◽  
Previous Treatment ◽  
Supersonic Velocity ◽  
Supersonic Stream ◽  
Flow Past

The flow past a wedge which is moving with supersonic velocity into a gas at rest has been treated by a number of investigators. In the analysis of the problem given in the present note, the condition for the detachment of the shock wave is examined, and an error in a previous treatment by Epstein is corrected.

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