NDLI: Heating augmentation in laminar flow due to heat-shield cavities on the project orion cev

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Heating augmentation in laminar flow due to heat-shield cavities on the project orion cev

Content Provider	NASA Technical Reports Server (NTRS)
Author	Hollis, Brian R.
Copyright Year	2008
Description	An experimental study has been conducted to assess the effects of compression pad cavities on the aeroheating environment of the Project Orion CEV heat-shield at laminar conditions. Testing was conducted in Mach 6 and Mach 10 perfect-gas wind tunnels to obtain heating measurements on and around the compression pads using global phosphor thermography. Consistent trends in heating augmentation levels were observed in the data and correlations of average and maximum heating at the cavities were formulated in terms of the local boundary-layer parameters and cavity dimensions. Additional heating data from prior testing of Genesis and Mars Science Laboratory models were also examined to extend the parametric range of cavity heating correlations.
File Size	10699708
Page Count	13
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20080034444
Archival Resource Key	ark:/13960/t08w8d23k
Language	English
Publisher Date	2008-08-18
Access Restriction	Open
Subject Keyword	Spacecraft Design, Testing And Performance Cavities Compressibility Effects Wind Tunnels Phosphors Aerodynamic Heating Ideal Gas Heat Shielding Crew Exploration Vehicle Thermography Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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