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Influence of radiant energy exchange on the determination of convective heat transfer rates to Orbiter leeside surfaces during entryTemperatures measured at the aerodynamic surface of the Orbiter's thermal protection system (TPS), and calorimeter measurements, are used to determine heating rates to the TPS surface during atmospheric entry. On the Orbiter leeside, where convective heating rates are low, it is possible that a significant portion of the total energy input may result from solar radiation, and for the wing, cross radiation from the hot (relatively) Orbiter fuselage. In order to account for the potential impact of these sources, values of solar- and cross-radiation heat transfer are computed, based upon vehicle trajectory and attitude information and measured surface temperatures. Leeside heat-transfer data from the STS-2 mission are presented, and the significance of solar radiation and fuselage-to-wing cross-radiation contributions to total energy input to Orbiter leeside surfaces is assessed.
Document ID
19820048319
Document Type
Conference Paper
Authors
Throckmorton, D. A. (NASA Langley Research Center Space Systems Div., Hampton, VA, United States)
Date Acquired
August 10, 2013
Publication Date
June 1, 1982
Subject Category
AERODYNAMICS
Report/Patent Number
AIAA PAPER 82-0824
Meeting Information
Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference(St. Louis, MO)
Distribution Limits
Public
Copyright
Other