An integral solution to the flat-plate laminar boundary-layer flow existing inside and after expansion waves and after shock waves moving into quiescent fluid with particular application to the complete shock-tube flow
Description: Report presenting a solution to the unsteady two-dimensional laminar boundary-layer flow inside centered expansion waves and behind both centered expansion waves and shock waves using an extension of the Karman-Pohlhausen method. The Prandtl unsteady-boundary-layer equations are also integrated normal to the surface bounding the flow and are transformed into a conical coordinate system. The solution to the two-dimensional unsteady laminar boundary layer existing at all points in an air-air shock tube is obtained using the method.
Date: June 1957
Creator: Trimpi, Robert L. & Cohen, Nathaniel B.
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Partner: UNT Libraries Government Documents Department