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Cooling Panel Optimization for the Active Cooling System of a Hypersonic AircraftOptimization of cooling panels for an active cooling system of a hypersonic aircraft is explored. The flow passages are of rectangular cross section with one wall heated. An analytical fin-type model for incompressible flow in smooth-wall rectangular ducts with coupled wall conduction is proposed. Based on this model, the a flow rate of coolant to each design minimum mass flow rate or coolant for a single cooling panel is obtained by satisfying hydrodynamic, thermal, and Mach number constraints. Also, the sensitivity of the optimal mass flow rate of coolant to each design variable is investigated. In addition, numerical solutions for constant property flow in rectangular ducts, with one side rib-roughened and coupled wall conduction, are obtained using a k-epsilon and wall function turbulence model, these results are compared with predictions of the analytical model.
Document ID
19990109045
Acquisition Source
Ames Research Center
Document Type
Reprint (Version printed in journal)
Authors
Youn, B.
(California Univ. Los Angeles, CA United States)
Mills, A. F.
(California Univ. Los Angeles, CA United States)
Date Acquired
August 19, 2013
Publication Date
January 1, 1995
Publication Information
Publication: Journal of Thermophysics and Heat Transfer
Publisher: American Institute of Aeronautics and Astronautics
Volume: 9
Issue: 1
Subject Category
Aircraft Design, Testing And Performance
Distribution Limits
Public
Copyright
Other

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