Wind tunnel wall interference effects on a supercritical airfoil at transonic speedsWind tunnel tests of a 10% supercritical airfoil have been conducted in the Lockheed Compressible Flow Facility at transonic speeds to determine the effects of varying wind tunnel wall porosity on airfoil performance. Wall configurations ranging in porosity from 1.3% to 10% were investigated at Reynolds numbers of 7 to 30 million. Experimental data presented to show the effect of varying wall porosity include airfoil surface pressures, airfoil forces, and wind tunnel wall pressures. Utilizing the experimental results, an assessment of the applicability of current subcritical theoretical methods to predict wall interference corrections in subsonic and transonic flows is made.
Document ID
19760055661
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Blackwell, J. A., Jr. (Lockheed-Georgia Co. Marietta, GA, United States)
Pounds, G. A. (Lockheed-Georgia Co. Marietta, Ga., United States)