The structure of MHD shock waves in a thermally-radiating gas at high mach numbers

1991 ◽  
Vol 179 (2) ◽  
pp. 171-176
Author(s):  
A. R. Bestman
Keyword(s):  
Shock Waves ◽  
Mach Numbers ◽  
High Mach ◽  
Mhd Shock Waves

The aerodynamic resistance to a sphere rotating at high Mach numbers in the rarefied transition régime

1966 ◽  
Vol 293 (1433) ◽  
pp. 156-168 ◽  
Keyword(s):  
Experimental Study ◽  
Aerodynamic Resistance ◽  
Pressure Gauge ◽  
Transition Regime ◽  
Drag Torque ◽  
Free Molecule ◽  
Rotating Sphere ◽  
Mach Numbers ◽  
High Mach ◽  
Molecule Flow

An experimental study has been made of the gaseous drag torque on an isolated sphere rotating at high Mach numbers. The sphere was suspended electromagnetically and spun by induction. The drag torque has been measured through the transition régime from continuum to free molecule flow at Mach numbers (based on equatorial speed) of up to about five. These high Mach numbers were achieved in heavy vapours (diiodomethane, germanium tetrabromide and stannic bromide) with sonic speed as little as a quarter of that in air. To measure the pressure in the vapour a second (smaller) rotating sphere was used as a pressure gauge. The results agree well with those previously obtained and show an unexpected Mach number dependence in the transition régime.

The generation of MHD shock waves during the impulsive phase of the February 27, 1992 flare

Solar Physics ◽  
1994 ◽  
Vol 155 (1) ◽  
pp. 171-184 ◽  
Author(s):  
Marian Karlický ◽  
Dušan Odstrčil
Keyword(s):  
Shock Waves ◽  
Impulsive Phase ◽  
Mhd Shock Waves

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.

Ion Heating in High—Mach-Number, Oblique, Collisionless Shock Waves

1972 ◽  
Vol 28 (7) ◽  
pp. 410-413 ◽  
Author(s):  
D. Biskamp ◽  
H. Welter
Keyword(s):  
Mach Number ◽  
Shock Waves ◽  
Collisionless Shock ◽  
Ion Heating ◽  
High Mach Number ◽  
High Mach

A comparative study of scramjet injection strategies for high Mach numbers flows

1992 ◽  
Author(s):  
D. RIGGINS ◽  
C. MCCLINTON ◽  
R. ROGERS ◽  
R. BITTNER
Keyword(s):  
Comparative Study ◽  
Mach Numbers ◽  
High Mach ◽  
Injection Strategies

Transition from regular to Mach reflection of shock waves Part 2. The steady-flow criterion

1982 ◽  
Vol 123 ◽  
pp. 155-164 ◽  
Author(s):  
H. G. Hornung ◽  
M. L. Robinson
Keyword(s):  
Shock Waves ◽  
Steady Flow ◽  
Mach Reflection ◽  
Strong Shock ◽  
Hysteresis Effect ◽  
Neumann Condition ◽  
Flow Transition ◽  
Von Neumann ◽  
Mach Numbers ◽  
Flow Criterion

It is shown experimentally that, in steady flow, transition to Mach reflection occurs at the von Neumann condition in the strong shock range (Mach numbers from 2.8 to 5). This criterion applies with both increasing and decreasing shock angle, so that the hysteresis effect predicted by Hornung, Oertel & Sandeman (1979) could not be observed. However, evidence of the effect is shown to be displayed in an unsteady experiment of Henderson & Lozzi (1979).

Numerical Simulation of R-M instability at High Mach Numbers

2009 ◽  
pp. 738-744
Author(s):  
Fu Dexun ◽  
Ma Yanwen ◽  
Liang Xian
Keyword(s):  
Numerical Simulation ◽  
Mach Numbers ◽  
High Mach
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