Mach reflection in steady supersonic flow considering wedge boundary-layer correction
Chinese Journal of Aeronautics
Chinese Journal of Aeronautics ; 33 , 2
2020-02-01
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Shock Wave Laminar Boundary Layer Interaction Over a Double Wedge in a High Mach Number Flow
British Library Conference Proceedings | 2014
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