Numerical investigation of supersonic flow past blunt bodies with protruding spikes

1986 ◽  
Vol 21 (3) ◽  
pp. 437-445 ◽  
Author(s):  
V. N. Karlovskii ◽  
V. I. Sakharov
Keyword(s):  
Supersonic Flow ◽  
Numerical Investigation ◽  
Flow Past ◽  
Blunt Bodies

Supersonic flow past blunt bodies involving fast nonequilibrium processes

1967 ◽  
Vol 2 (5) ◽  
pp. 57-60 ◽  
Author(s):  
V. P. Stulov ◽  
L. I. Turchak
Keyword(s):  
Supersonic Flow ◽  
Nonequilibrium Processes ◽  
Flow Past ◽  
Blunt Bodies

Experimental investigation of supersonic flow past blunt bodies with strong distributed injection

1978 ◽  
Vol 13 (3) ◽  
pp. 406-415 ◽  
Author(s):  
M. A. Koval' ◽  
V. P. Stulov ◽  
A. I. Shvets
Keyword(s):  
Experimental Investigation ◽  
Supersonic Flow ◽  
Flow Past ◽  
Blunt Bodies

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

A numerical investigation of supersonic flow past an aft body

2000 ◽  
Author(s):  
George Catalano ◽  
Walter Sturek
Keyword(s):  
Supersonic Flow ◽  
Numerical Investigation ◽  
Flow Past

Numerical Investigation of Viscous Laminar Supersonic Flow Past an Asymmetric Biconvex Circular-Arc Aerofoil

2013 ◽  
Vol 390 ◽  
pp. 147-151
Author(s):  
Saif Akram ◽  
Nadeem Hasan ◽  
Aqib Khan
Keyword(s):  
Reynolds Number ◽  
Mach Number ◽  
Supersonic Flow ◽  
Numerical Investigation ◽  
Lower Surface ◽  
Two Dimensional ◽  
Circular Arc ◽  
Flow Past ◽  
Supersonic Regime ◽  
Force Characteristics

A numerical investigation of two-dimensional unsteady, viscous and laminar compressible flow past an asymmetric biconvex circular-arc aerofoil in supersonic regime is carried out. The focus of the present work is to investigate the effects of variation of Mach number, at two different angles of attack, on the flow and force characteristics on NACA 2S-(50)(04)-(50)(20) aerofoil. The value of Reynolds number is taken as 5x105. The computations are carried out at Mach numbers of 1.25, 1.5 and 2.0 at an angle of attack of α=0° and α=10°. It is found that the aerofoil works well in the supersonic flow and, unlike the conventional symmetric biconvex aerofoil, generates finite lift at α=0° due to stronger shock waves at the lower surface. Moreover, the L/D ratio at α=10° is always found to be more than 2.5.

Supersonic flow past blunt bodies screened by a permeable surface

1986 ◽  
Vol 21 (2) ◽  
pp. 287-291 ◽  
Author(s):  
S. V. Guvernyuk ◽  
K. G. Savinov
Keyword(s):  
Supersonic Flow ◽  
Permeable Surface ◽  
Flow Past ◽  
Blunt Bodies
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