TESTS OF ONE-THIRD-SCALE NASA HYPERSONIC RESEARCH ENGINE INLET AT MACH NUMBERS 6 AND 8

An axisymmetric, variable geometry, hypersonic inlet was tested at Mach numbers 6 and 8 as a preliminary step in the development of the NASA hypersonic Research Engine (HRE). Surface pressure measurements on the inlet centerbody and inside the cowl and pitot pressure measurements at two stations alo...

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Bibliographic Details
Main Author: Hube, Frederick K
Format: Report
Language:English
Subjects:
AERODYNAMIC LOADING
ANGLE OF ATTACK
CENTERBODIES
FAIRINGS
Fluid Mechanics
HYPERSONIC CHARACTERISTICS
HYPERSONIC INLETS
INLETS
Jet and Gas Turbine Engines
MODEL TESTS
PRESSURE
RAMJET INLETS
SUPERSONIC COMBUSTION RAMJET ENGINES
WIND TUNNEL MODELS
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Summary:An axisymmetric, variable geometry, hypersonic inlet was tested at Mach numbers 6 and 8 as a preliminary step in the development of the NASA hypersonic Research Engine (HRE). Surface pressure measurements on the inlet centerbody and inside the cowl and pitot pressure measurements at two stations along the internal passage were made. The measurements were obtained at various centerbody positions, free-stream Reynolds numbers from 970,000 to 2,500,000, based on the 6-in. cowl diameter, and over an angle-of-attack range from -6 to +6 deg. Selected results are presented to illustrate the effects of centerbody position, angle of attack, Mach number, and Reynolds number on the surface and pitot pressure distributions. Prepared in cooperation with ARO, Inc., Tullahoma, TN.