NACA Technical Notes

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

NACA Technical Notes

Note presenting corrections for drag, lift, and moment that are derived for an axially symmetrical body placed in the test section of a supersonic tunnel on the assumption that the test section is characterized by a two-dimensional pressure field originating from construction flaws. Assuming irrotational conditions, the velocity potential of the flow around the body is expanded in a threefold manner: in powers of the thickness parameter of the body, in powers of a parameter characterized the inhomogeneity of the basic flow field, and as a Fourier series in the azimuth around the body axis