BOUNDARY LAYER PROFILE MEASUREMENTS IN HYPERSONIC NOZZLES
AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OH
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An experimental investigation made to determine the flow parameter profiles across the boundary layer on contoured, axisymmetric hypersonic nozzles is described. The pitot pressure and total temperature profiles measured across the boundary layers on nozzles of Mach number seven and twelve are shown in graphical form. The static temperature and velocity profiles, calculated with the assumption of constant static pressure across the boundary layer, are given. A correlation is shown to exist between the exponent of the velocity profile power law and the product of the ratios of wall temperature to free stream total temperature and axial distance to momentum thickness. The static temperature profiles, calculated from the measured data is compared with Croccos relationship for the static temperature in terms of the velocity profile.
- Fluid Mechanics