Boundarylayer thickness and base pressure
Abstract
A theory for predicting base pressure in twodimensional supersonic flow (Tanner, 1980, 1984) relates changes in the basepressure coefficient to changes in the boundarylayer thickness. The theory predicts that the difference in the basepressure coefficient relative to the difference in the momentum thickness will become zero at any freestream Mach number at the limiting boundarylayer thickness value of 0.003. The theory correlates well with the results of Goecke (1978) obtained from flightmeasured base pressures taken at Mach numbers of 2.20, 2.50, and 2.85.
 Publication:

AIAA Journal
 Pub Date:
 December 1985
 DOI:
 10.2514/3.9208
 Bibcode:
 1985AIAAJ..23.1987T
 Keywords:

 Base Pressure;
 Flow Theory;
 Fluid Pressure;
 Supersonic Boundary Layers;
 Backward Facing Steps;
 Computational Fluid Dynamics;
 Mach Number;
 Pressure Measurement;
 Thickness;
 Fluid Mechanics and Heat Transfer