Accession Number : AD0431202


Title :   PRESSURE AND HEAT TRANSFER MEASUREMENTS FOR HYPERSONIC FLOWS OVER EXPANSION CORNERS AND AHEAD OF RAMPS. PART 3: MACH 8 PRESSURE DATA FOR FLOWS AHEAD OF RAMPS 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/u2/431202.pdf


Report Date : Dec 1963


Pagination or Media Count : 139


Abstract : Pressure and heat transfer data were obtained for hypersonic flows over 40-degree expansion corners and ahead of ramps. Full and partial span ramps, having wedge angles up to 90 degrees, were tested at two locations on a sharp leading edge flat plate, with and without end plates. Pressure data were obtained for Mach 5 for model length Reynolds numbers between 1.1 and 6.6 million. Both pressure and heat transfer data were obtained for Mach 8 for Reynolds numbers between 1.1 and 3.3 million.


Descriptors :   *HYPERSONIC FLOW , *PRESSURE , *WEDGES , AERODYNAMIC CONFIGURATIONS , CONTROL , DELTA WINGS , FLAPS(CONTROL SURFACES) , FLAT PLATE MODELS , HEAT TRANSFER , INSTRUMENTATION , MEASUREMENT , MODEL TESTS , REYNOLDS NUMBER , SEPARATION , WIND TUNNEL MODELS


Subject Categories : Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE