Accession Number : AD0617620
Title : PRESSURE RECOVERY MEASUREMENTS ACROSS A TWO-DIMENSIONAL HYPERSONIC INLET WITH VARIABLE GEOMETRY.
Descriptive Note : Interim rept. for Dec 63-Jul 64,
Corporate Author : CINCINNATI UNIV OHIO
Personal Author(s) : Tabakoff,Widen ; McDonel,James D.
Report Date : MAY 1965
Pagination or Media Count : 43
Abstract : The report describes the experimental measurement of pressure recovery across a simulated combustion chamber duct of a two-dimensional hypersonic inlet with variable geometry. The model tested was a wedge type inlet which generated a single external shock wave. The program was conducted in the twenty-inch hypersonic wind tunnel. Testing was at a nominal free stream Mach number of 14 and free stream Reynolds number of 721,000 per foot. (Author)
Descriptors : (*RAMJET ENGINES, COMBUSTION CHAMBERS), (*RAMJET INLETS, PRESSURE), (*HYPERSONIC CHARACTERISTICS, RAMJET INLETS), HYPERSONIC DIFFUSERS, HYPERSONIC WIND TUNNELS, TWO DIMENSIONAL FLOW, GEOMETRY, MEASUREMENT, AERODYNAMIC CONFIGURATIONS, TRANSDUCERS, SIMULATION
Distribution Statement : APPROVED FOR PUBLIC RELEASE