THE LAMINAR BOUNDARY LAYER IN AXISYMMETRIC HYPERSONIC NOZZLES WITH WALL COOLING.
Interim technical rept. no. 2, 1 Apr-15 Nov 64,
OHIO STATE UNIV RESEARCH FOUNDATION COLUMBUS AERODYNAMIC LAB
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An experimental and analytic investigation of the influence of wall cooling on conical hypersonic nozzles operated at moderately low Reynolds numbers is reported. The experimental program consisted of nozzle static pressure distributions and impact pressure surveys of a nominal M 12, 3-inch exit diameter conical nozzle equipped with a coolant tank to allow for the adjustment of the wall temperature. Various coolants water, freon-dry ice mixture, and liquid nitrogen were used to provide selected wall temperatures down to 210R. The measurements showed a 25 reduction of the displacement and boundary layer thicknesses when referred to a nozzle equilibrium temperature of 670R. The momentum integral technique was used to formulate a digital computer program to examine the wall cooling effects on hypersonic axisymmetric nozzles. A Pr number of one is assumed. Fourth order velocity and total enthalpy profiles were used. These profiles were adjusted to account for wall temperature, transverse curvature, and pressure gradient. Results from this computer program were confirmed by the experiments. Author