Pressure Recovery at Supersonic Speeds Through Annular Duct Inlets Situated in a Region of Appreciable Boundary Layer PDF Download

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Pressure Recovery at Supersonic Speeds Through Annular Duct Inlets Situated in a Region of Appreciable Boundary Layer

Pressure Recovery at Supersonic Speeds Through Annular Duct Inlets Situated in a Region of Appreciable Boundary Layer PDF Author: Wallace F. Davis
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 22

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Book Description
A model having a nozzle upstream of an annular duct inlet for the purpose of ejecting high-velocity air into the boundary layer of the flow along the forebody was tested at Mach numbers between 1.36 and 2.01. The size and location of the nozzle and the total pressure of the air in the jet were varied to determine their effects upon the pressure recovery attainable after diffusion through the duct inlet. The results of the tests showed that the maximum total-pressure recovery was greater than that of a model having no air ejected. The causes of the greater recovery were the delay in the separation of the boundary layer that resulted from mixing between the boundary layer and the jet and also the reduction in the intake Mach number caused by an oblique shock wave that originated from the nozzle outlet when the free boundary of the jet was divergent.