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Radiative Viscous Shock Layer Analysis of Fire, Apollo, and PAET Flight DataEquilibrium, radiating viscous shock layer solutions are obtained for a number of trajectory points of the Fire II, Apollo 4, and PAET experimental flight vehicles. Convective heating rates calculated by a benchmark code agree well with two engineering correlations, except at high altitudes corresponding to low densities. Calculated radiation intensities are compared with the flight radiometer data and with inviscid flow results. Differences as great as 70% are observed between measured data and the viscous calculations. Because of boundary-layer absorption, viscous effects reduce the intensity to the wall by as much as 30% compared with inviscid intensities. Preliminary chemical and thermal nonequilibrium flow calculations along a stagnation streamline for a PAET trajectory predict an enhancement to the radiation owing to the chemical relaxation. Stagnation point solutions are also presented for future aeroassisted orbital transfer vehicle geometries with nose radii of 0.3-15 m.
Document ID
19990066625
Acquisition Source
Ames Research Center
Document Type
Reprint (Version printed in journal)
Authors
Balakrishnan, A.
(Eloret Corp. Sunnyvale, CA United States)
Park, Chul
(NASA Ames Research Center Moffett Field, CA United States)
Green, Michael J.
(NASA Ames Research Center Moffett Field, CA United States)
Date Acquired
August 19, 2013
Publication Date
January 1, 1986
Publication Information
Publication: Progress in Astronautics and Aeronautics: Thermophysical Aspects of Re-Entry Flows
Publisher: American Inst. of Aeronautics and Astronautics
Volume: 103
ISBN: 0-930403-10-X
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA Paper 85-1064
Meeting Information
Meeting: Thermophysics
Location: Williamsburg, VA
Country: United States
Start Date: June 19, 1985
End Date: June 21, 1985
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Other

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