Experimental study for combustion within a supersonic boundary layer and its effect on laminar-turbulent transition
V.I. Lysenko, A.V. Starov
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia
Keywords: compressible boundary layer, permeable surface, injection, burning, hydrodynamic stability, transition
Abstract
For the first time, experimental studies were carried out on the effect of hydrogen combustion inside a supersonic (Ме= 2) flat-plate boundary layer on the laminar-turbulent transition in this flow. It was found in experiments that hydrogen injection (originating from the streamlined model) and its combustion in a certain sublayer partly stabilizes the layer flow. This result corresponds to the calculated data from S.A. Gaponov: it was shown that the heat supply into the supersonic boundary layer can deter the disturbance growth (i.e., facilitates the stabilization of the boundary layer stabilization). However, in general (compared to the non-combustion flow), the supersonic boundary layer is destabilized by combined hydrogen injection and fuel combustion. This means that the destabilizing effect of hydrogen injection prevails over the stabilizing effect of heat supply to the boundary layer.
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