1958•NASA STI Repository (National Aeronautics and Space Administration)Requires access
Wind-Tunnel Investigation of the Effects of Lip Geometry on Drag and Pressure Recovery of a Normal-Shock Nose Inlet on a Body of Revolution at Mach Numbers of 1.41 and 1.81
A. W. Robins
Open publisher page 0 citations
Abstract
Report presenting an investigation to determine some of the effects of lip geometry on drag and pressure recovery of a normal-shock nose inlet. Lip bluntness, lip camber, and forebody angle were all explored as possible variables. Total-pressure recoveries, external drags, duct total-pressure distributions, lip and forebody pressure distributions, and Schileren photographs are provided.