Supersonic flow around a hemi-axisymmetric body resting on a flat plate.

AIAA Journal ◽  
1965 ◽  
Vol 3 (11) ◽  
pp. 2152-2154
Author(s):  
STEVEN S. CHERRY
Keyword(s):  
Supersonic Flow ◽  
Flat Plate ◽  
Axisymmetric Body

The Effect of Sting Diameter and Length on Base Pressure at M = 3·88

1968 ◽  
Vol 19 (4) ◽  
pp. 368-374 ◽  
Author(s):  
Walter R. Sieling
Keyword(s):  
Supersonic Flow ◽  
Axisymmetric Body ◽  
Base Pressure ◽  
Base Diameter ◽  
Apparent Change

SummaryThe effects of sting diameter and cylindrical protuberance length on the base pressure of an axisymmetric body in a turbulent supersonic flow are experimentally determined. It is found that the change in base pressure due to the presence of the sting is greater than 4 per cent when the ratio of sting diameter to base diameter is 0·150 or greater. When the ratio of cylindrical protuberance length to base diameter is greater than 1·3 there is no apparent change in base pressure with a change in length. However, when this ratio is less than 1·3, the base pressure varies greatly with length.

Stability of a wake behind a flat plate in a supersonic flow

1995 ◽  
Vol 36 (6) ◽  
pp. 844-847
Author(s):  
V. I. Lysenko ◽  
N. V. Semenov
Keyword(s):  
Supersonic Flow ◽  
Flat Plate

Flowfield in the vicinity of cylindrical protuberances on a flat plate in supersonic flow.

1968 ◽  
Vol 5 (1) ◽  
pp. 127-128 ◽  
Author(s):  
PAUL J. WALTRUP ◽  
DOUGLAS G. HALL ◽  
JOSEPH A. SCHETZ
Keyword(s):  
Supersonic Flow ◽  
Flat Plate

scholarly journals Experimental and numerical studies of supersonic flow over circular protuberances on a flat plate

2015 ◽  
Vol 64 (5) ◽  
pp. 054705
Author(s):  
Gang Dun-Dian ◽  
Yi Shi-He ◽  
Zhao Yun-Fei
Keyword(s):  
Supersonic Flow ◽  
Flat Plate ◽  
Numerical Studies

scholarly journals Supersonic Cascade Interaction

1974 ◽  
Author(s):  
H. J. Lichtfuss ◽  
H. Starken
Keyword(s):  
Exact Solution ◽  
Supersonic Flow ◽  
Flat Plate ◽  
Constant Velocity ◽  
Flow Conditions ◽  
Inlet Flow ◽  
Flow Adjustment ◽  
Outlet Flow ◽  
Quantitative Results ◽  
Cascade Interaction

The supersonic flow adjustment between two interacting blade rows is predicted theoretically. One of both cascades may have a constant velocity in the circumferential direction. The calculation is carried out in a quasi-stationary manner. This represents an exact solution if the constant inlet and outlet flow conditions are solely under the scope of view. Admitting the above assumptions it is possible to calculate the uniform outlet flow of the first and the associated inlet flow of the second cascade as a function of the circumferential velocity. Quantitative results are presented for flat plate cascades. However, the method is not at all restricted to these simple cases.

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