Exact solution for wind tunnel interference using the panel method (Q1069798)

Wind tunnel wall interference effects on lifting and non-lifting bodies are computed here for incompressible two-dimensional flows. The flows around bodies under consideration are computed by a panel method using linearly varying vortex distributions. The method is regarded as an exact numerical method. Also to exactly compensate for the wind tunnel wall, we use the method of images of the complete body in the wind tunnel. The image system consists of two cascades which extend infinitely on both sides of the wind tunnel. Thus, the exact wind tunnel wall interference effects are obtained for circular and elliptic cylinders. NACA 23012, NACA 64A010 and NACA 0010 airfoils. The velocity distributions and lift coefficient variations are presented for different blockages. The effects of airfoil incidences and the relative proximity of the two walls are also investigated. The present analysis has given rise to some results which otherwise would not have been possible by earlier existing very approximate methods. Wind tunnel walls are found to change the circulation around the body in the wind tunnel. This effect is further accentuated if we either change the incidence or change the relative proximity of the wind tunnel walls.