Supersonic flow past a star-shaped body without symmetry planes at angle of attack

1993 ◽  
Vol 28 (4) ◽  
pp. 560-567
Author(s):  
M. I. Follet
Keyword(s):  
Supersonic Flow ◽  
Angle Of Attack ◽  
Shaped Body ◽  
Flow Past

Supersonic flow past a sharp cone oscillating about a zero angle of attack

1998 ◽  
Vol 33 (6) ◽  
pp. 913-923
Author(s):  
Yu. M. Lipnitskii ◽  
E. V. Matsyura ◽  
A. N. Pokrovskii
Keyword(s):  
Supersonic Flow ◽  
Angle Of Attack ◽  
Flow Past ◽  
Sharp Cone

Effect of angle of attack on supersonic flow past axisymmetric blunt bodies with surface injection

1988 ◽  
Vol 22 (5) ◽  
pp. 737-742 ◽  
Author(s):  
V. A. Antonov ◽  
A. M. Grishin ◽  
F. M. Pakhomov
Keyword(s):  
Supersonic Flow ◽  
Angle Of Attack ◽  
Flow Past ◽  
Blunt Bodies

The Supersonic Flow Past a Slender Ducted Body of Revolution with an Annular Intake

1950 ◽  
Vol 1 (4) ◽  
pp. 305-318
Author(s):  
G. N. Ward
Keyword(s):  
Supersonic Flow ◽  
Velocity Potential ◽  
Operational Calculus ◽  
The Body ◽  
Body Of Revolution ◽  
Internal Flows ◽  
Flow Past ◽  
External Forces ◽  
Internal Pressures ◽  
Slender Body Of Revolution

SummaryThe approximate supersonic flow past a slender ducted body of revolution having an annular intake is determined by using the Heaviside operational calculus applied to the linearised equation for the velocity potential. It is assumed that the external and internal flows are independent. The pressures on the body are integrated to find the drag, lift and moment coefficients of the external forces. The lift and moment coefficients have the same values as for a slender body of revolution without an intake, but the formula for the drag has extra terms given in equations (32) and (56). Under extra assumptions, the lift force due to the internal pressures is estimated. The results are applicable to propulsive ducts working under the specified condition of no “ spill-over “ at the intake.

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