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Evaporative Film Cooling for Hypersonic Reentry VehiclesEvaporative film cooling on blunt nose models has been investigated in a 12″ × 12″ hypersonic blowdown wind tunnel at Mach number 7 with stagnation temperatures up to 2500 °R. Water as coolant was supplied continuously through orifices located near the stagnation point of a hemisphere-cylinder body (3 inch diameter) and a blunt cone with 10° half angle (base diameter 5.5 inches) forming an evaporating water film covering the body. This results in nearly uniform wall temperatures about 30 °R below the local boiling temperature of the water.
Document ID
19630006112
Acquisition Source
Legacy CDMS
Document Type
Other -
Authors
Rudolf Hermann (University of Minnesota Minneapolis, United States)
Date Acquired
August 1, 2013
Publication Date
March 23, 1962
Subject Category
Geophysics
Meeting Information
Meeting: Commemorating the Fiftieth Birthday of Wernher von Braun
Location: Huntsville, AL
Country: US
Start Date: March 23, 1962
Sponsors: National Aeronautics and Space Administration
Accession Number
63N15988
Funding Number(s)
CONTRACT_GRANT: AF 49/638/-190
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
HYPERSONIC HEAT TRANSFER
FILM COOLING
EVAPORATION COOLING
REENTRY VEHICLE
SPACE SCIENCE
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