Abstract A numerical study to evaluate the critical height of microvortex generators in controlling swept shock wave boundary layer interactions is carried out. The planar shock wave is generated by placing a 20° sharp fin in a supersonic flow at Mach 4. The ramp and thick vane microvortex generator geometries were considered. The device heights were varied from 30 to 90 % of the incoming boundary layer thickness. The efficacy of the devices was observed to increase with increasing device height up to a height of 70 % of the incoming boundary layer thickness beyond which no further improvement was achieved.
Effect of height of microvortex generators on swept shock wave boundary layer interactions
CEAS Aeronautical Journal ; 4 , 3
2013
Aufsatz (Zeitschrift)
Englisch
BKL: | 55.50 Luftfahrzeugtechnik / 50.03 Methoden und Techniken der Ingenieurwissenschaften / 50.03$jMethoden und Techniken der Ingenieurwissenschaften / 55.50$jLuftfahrzeugtechnik | |
DDC: | 629.105 |
Effect of height of microvortex generators on swept shock wave boundary layer interactions
Springer Verlag | 2013
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