The calculation of drag for airfoil sections and bodies of revolution at subcritical speeds
Description:
Report presenting a method for calculating the drag, in a real compressible fluid and at subcritical Mach numbers, of airfoil sections at arbitrary life coefficients and of bodies of revolution at zero angle of attack. The values of drag coefficient are compared with values obtained for the same configurations by other methods. The differences between the results are found to lie withint he limits of accuracy of current experimental techniques.
Date:
April 23, 1947
Creator:
Heaslet, Max A. & Nitzberg, Gerald E.
Item Type:
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Partner:
UNT Libraries Government Documents Department