scholarly journals Corrections for non-ideal effects in reflected shock waves at low Mach numbers

1990 ◽  
Author(s):  
J. V. Michael ◽  
J. R. Fisher
Keyword(s):  
Shock Waves ◽  
Reflected Shock ◽  
Mach Numbers

A New Method for Current ``Crowbar,'' Utilizing Reflected Shock Waves

1972 ◽  
Vol 43 (10) ◽  
pp. 1481-1481 ◽  
Author(s):  
Koichi Kasuya ◽  
Toshimitsu Murasaki
Keyword(s):  
Shock Waves ◽  
New Method ◽  
Reflected Shock

Self-exchange of oxygen behind reflected shock waves

1979 ◽  
Vol 83 (23) ◽  
pp. 2933-2935 ◽  
Author(s):  
A. F. Bopp ◽  
R. D. Kern ◽  
T. Niki ◽  
G. M. Stack
Keyword(s):  
Shock Waves ◽  
Reflected Shock

Shock Wave - Film Cooling Interactions in Transonic Flows

2001 ◽  
Author(s):  
P. M. Ligrani ◽  
C. Saumweber ◽  
A. Schulz ◽  
S. Wittig
Keyword(s):  
Shock Wave ◽  
Mach Number ◽  
Shock Waves ◽  
Film Cooling ◽  
Cross Flow ◽  
Injection Velocity ◽  
Film Cooling Effectiveness ◽  
Mach Numbers ◽  
Density Ratios ◽  
Film Cooling Holes

Interactions between shock waves and film cooling are described as they affect magnitudes of local and spanwise-averaged adiabatic film cooling effectiveness distributions. A row of three cylindrical holes is employed. Spanwise spacing of holes is 4 diameters, and inclination angle is 30 degrees. Freestream Mach numbers of 0.8 and 1.10–1.12 are used, with coolant to freestream density ratios of 1.5–1.6. Shadowgraph images show different shock structures as the blowing ratio is changed, and as the condition employed for injection of film into the cooling holes is altered. Investigated are film plenum conditions, as well as perpendicular film injection cross-flow Mach numbers of 0.15, 0.3, and 0.6. Dramatic changes to local and spanwise-averaged adiabatic film effectiveness distributions are then observed as different shock wave structures develop in the immediate vicinity of the film-cooling holes. Variations are especially evident as the data obtained with a supersonic Mach number are compared to the data obtained with a freestream Mach number of 0.8. Local and spanwise-averaged effectiveness magnitudes are generally higher when shock waves are present when a film plenum condition (with zero cross-flow Mach number) is utilized. Effectiveness values measured with a supersonic approaching freestream and shock waves then decrease as the injection cross-flow Mach number increases. Such changes are due to altered flow separation regions in film holes, different injection velocity distributions at hole exits, and alterations of static pressures at film hole exits produced by different types of shock wave events.

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