Corrections for lift, drag, and moment of an airfoil in a supersonic tunnel having a given static pressure gradient

H. F. Ludloff, M. B. Friedman
naca-tn-2849
Dec 1952


The corrections for lift, drag, and moment of a two-dimensional airfoil have been analyzed, on the assumption that the airfoil is tested in the working section of a supersonic tunnel in which the pressure field, instead of being uniform, is characterized by gradients in the axial and transverse directions.

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