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Afterbody Heat Flux Measurements in the NASA Ames HFFAF Ballistic RangeIn order to measure afterbody heat fluxes over a model in the ballistic range, the required modifications to a proven technique for measuring forebody heat fluxes are described. This involves the use of an extended helium gas plume to remove the glowing wake and the use of special high conductivity, high temperature capable graphite-filled plastic for the afterbody. The models and test conditions are described. Data in the form of plots of the surface temperature of the models are presented. Finally, experimental and computational fluid dynamic (CFD) heat flux data for forebody and afterbody heat fluxes are presented and compared. Data are presented for a 45 degree sphere-cone (with a projecting rear stud) at 2.70 km/s and for a sphere at 4.76 km/s. Both models were launched into 76 Torr of CO2 gas. The experimental forebody heat fluxes were within 1.5% of the CFD values. The experimental afterbody heat fluxes were within 1% of the CFD values for the sphere, but only 51% of the CFD values for the sphere-cone.
Document ID
20190001966
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Bogdanoff, David W. (Engineering Research and Consulting (ERC), Inc. Moffett Field, CA, United States)
Wilder, Michael C. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
March 29, 2019
Publication Date
October 19, 2014
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
ARC-E-DAA-TN17696
Meeting Information
Meeting: Meeting of Aeroballistic Range Association
Location: Arcachon
Country: France
Start Date: October 19, 2014
End Date: October 24, 2014
Sponsors: Aeroballistic Range Association
Funding Number(s)
CONTRACT_GRANT: NNA10DE12C
Distribution Limits
Public
Copyright
Public Use Permitted.

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