A study on prediction of the base pressures for an axi-symmetric body

A flow modeling method has been developed to analyze the flow in the annula r base (rear-facing surface) of a circular engine nacelle flying at subsoni c speed but with a supersonic exhaust jet. Real values of exhaust gas prope rties and temperature at an altitude of 30, 000 feet are employed. Potentia l flows of the air and gas streams are computed for the flow past a separat ed wake. Then a viscous jet mixing is superimposed on this inviscid solutio n. Conservation of mass. momentum and energy for the wake flow field is ach ieved by multiple iterations with modest computer requirements.