Window Systems for Advanced Vehicles

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Report Number: FDL TDR 64-39
Author(s): Lis, S. J., Barile , R. G., Engholm, G.
Corporate Author(s): General American Transportation Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1964-12
Pages: 141
Contract: AF 33(657)-9138
DoD Project: 1368
DoD Task: 136802
Identifier: AD0459373

A basic investigation to describe the heat transfer and temperature distribution in semi-transparent window materials subjected to simultaneous convective and radiative heat input. The mechanism of heat transfer within the window is treated by separated conductive and radiative modes. Results derived from IBM 7090 Digital Computer Programs are presented for single glaze windows subjected to a hypersonic skip glide trajectory, a supersonic flight and a circular earth orbit. The conditions where radiative interchange is important are studied. Initial results considering the effects of a thin transparent film on a single glazing are presented.

Provenance: Lockheed Martin Missiles & Fire Control

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