Boundary-Layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6
Description:
"Measurements are presented for pressure gradients induced by a laminar boundary layer on a flat plate in air at a Mach number of 9.6 and for the drag of thin wings at a Mach number of about 6.8 and zero angle of attack. The pressure measurements at a Mach number of 9.6 were made in the presence of substantial heat transfer from the boundary layer to the plate surface. The measured pressure distribution o the surface of the plate was predicted with good accuracy by a modification to insulated-p…
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Date:
1959
Creator:
Bertram, Mitchel H.
Partner:
UNT Libraries Government Documents Department