Description: Report presenting the results of an estimation of the limit forces on airfoils at supersonic speeds. The limit pressure coefficient attainable on an airfoil is shown to be about 70 percent of the pressure coefficient for a vacuum over a wide range of Mach numbers.
Date: August 23, 1948
Creator: Mayer, John P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department