EXPERIMENTAL INVESTIGATION OF THE SURFACE IMPACT PRESSURE PROBE METHOD OF MEASURING LOCAL SKIN FRICTION AT SUPERSONIC SPEEDS

摘要

The purpose of this report is to demonstrate from the results of proper wind tunnel tests the accuracy of the surface probe theory for compressible flow as derived by Fender at DRL (Ref. 1) and to demonstrate the feasibility of using a surface probe scheme in determining local skin friction coefficients on supersonic flight vehicles. This study was initiated because of the need for a simple and accurate experimental method of measuring the skin friction drag on such vehicles. The bulb of the experimental tests were conducted at the DRL wind tunnel test facility located at Balcones Research Center, The university of Texas.