NACA Technical Notes

Abstract

Note presenting an analysis of the corrections for lift, drag, and moment of a two-dimensional airfoil as 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. The pressure gradients of the tunnel as well as the effect of the airfoil to be tested are regarded as perturbations of the original rectilinear flow field of given Mach number