An Experimental Investigation of a Shock Location Prediction Method on Supercritical Airfoils.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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The purpose of this investigation was to attempt to verify or refute empirical correlations developed by Studwell used to correct airfoil shock locations which are computer-predicted by inviscid theory. Data were analyzed and correlated from tests conducted in the Air Force Flight Dynamics Laboratory Trisonic Gasdynamic Facility and at Ohio State University on supercritical airfoils. The Studwell correlations relate a separation pressure coefficient, as defined by a computer-predicted, inviscid, theoretical flow solution, to an onset pressure coefficient which, when located on the theoretical distribution, gives a corrected location for the shock. The separation and onset pressure coefficients are related through their Mach numbers and the ratio of the separation pressure to the onset pressure which are determined using isentropic relations referenced to free stream conditions.