Accession Number : AD0431280


Title :   PRESSURE MEASUREMENTS FOR MACH 8 FLOWS OVER EXPANSION CORNERS AND RAMPS ON AN INTERNALLY COOLED MODEL. PART I. EXPANSION CORNER FLOWS. PART OF AN INVESTIGATION OF HYPERSONIC FLOW SEPARATION AND CONTROL CHARACTERISTICS


Corporate Author : GRUMMAN AIRCRAFT ENGINEERING CORP BETHPAGE NY


Personal Author(s) : Kaufman, II, Louis G


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/431280.pdf


Report Date : Oct 1963


Pagination or Media Count : 75


Abstract : Pressure distributions were obtained for Mach 8 flows over a sharp 40 degree expansion corner and ahead of ramps on an internally cooled model. Full and partial span ramps, having wedge angles up to 30 degrees, were tested at model angles of attack from -45 to +10 degrees for Reynolds numbers ranging from 1.1 to 3.3 million. The model wall temperature was maintained at fairly constant levels ranging from 450 to 1150 degrees Rankine.


Descriptors :   *HYPERSONIC TEST VEHICLES , *AERODYNAMIC CONTROL SURFACES , HEAT TRANSFER , PRESSURE , HYPERSONIC WIND TUNNELS , EXHAUST FAIRINGS , HYPERSONIC FLOW , HYPERSONIC CHARACTERISTICS , WEDGES


Subject Categories : Research and Experimental Aircraft
      Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE