Aerodynamic Cooling of the Wall in the Trace of a Supersonic Flow behind a Backward-Facing Ledge

The results of an experimental study of the effect of reducing the adiabatic wall temperature (aerodynamic cooling) for a case of separated supersonic flow behind a backward-facing ledge are presented. The study was conducted on an unsteady-state regime during the launching of a wind tunnel before r...

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Veröffentlicht in:	Fluid dynamics 2022-12, Vol.57 (Suppl 1), p.S57-S64
1. Verfasser:	Popovich, S. S.
Format:	Artikel
Sprache:	eng
Schlagworte:	Adiabatic flow Boundary layers Classical and Continuum Physics Classical Mechanics Continuous flow Cooling Engineering Fluid Dynamics Fluid flow Fluid- and Aerodynamics Gas dynamics Heat flux Mach number Physics Physics and Astronomy Reynolds number Stagnation flow Stanton number Static pressure Supersonic flow Wall temperature Wind tunnels
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