PRESSURE RECOVERY MEASUREMENTS ACROSS A TWO-DIMENSIONAL HYPERSONIC INLET WITH VARIABLE GEOMETRY

PRESSURE RECOVERY MEASUREMENTS ACROSS A TWO-DIMENSIONAL HYPERSONIC INLET WITH VARIABLE GEOMETRY

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 twent...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: Tabakoff,Widen, McDonel,James D
Format: Report
Sprache:eng
Schlagworte:
AERODYNAMIC CONFIGURATIONS
COMBUSTION CHAMBERS
GEOMETRY
HYPERSONIC CHARACTERISTICS
HYPERSONIC DIFFUSERS
HYPERSONIC WIND TUNNELS
MEASUREMENT
PRESSURE
RAMJET ENGINES
RAMJET INLETS
SIMULATION
TRANSDUCERS
TWO DIMENSIONAL FLOW
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Beschreibung
Zusammenfassung: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)