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Development of a Thermal Radiator Optimization Tool with Alternate CoolantsThe development of a modeling tool to optimize the design of a thermal radiator based on capacity, rejection temperature, geometry, type and coolant is presented. The radiator size is determined from the desired capacity, environmental conditions and rejection temperature. Flow through the radiator is derived from the overall heat load and prescribed inlet to outlet delta temperature for a given coolant. The tool considers radiator geometry (i.e., tube spacing and diameter, face-sheet thickness, overall size, etc.) and general type (i.e., parallel/manifold versus serpentine) in the optimization. Selection from a handful of potential coolants is also available in the tool which primarily affects necessary tube diameter to maintain turbulent flow and minimize pressure drop. An Equivalent System Mass (ESM) approach is utilized to include pump power in the optimization. Results from the tool and potential future enhancements are also discussed.
Document ID
20260007746
Acquisition Source
Marshall Space Flight Center
Document Type
Presentation
Authors
Greg Schunk
(Amentum Chantilly, Virginia, United States)
Date Acquired
August 12, 2026
Subject Category
Engineering (General)
Meeting Information
Meeting: Thermal and Fluids Analysis Workshop (TFAWS)
Location: Huntsville, AL
Country: US
Start Date: August 31, 2026
End Date: September 4, 2026
Sponsors: National Aeronautics and Space Administration
Funding Number(s)
CONTRACT_GRANT: 954879.06.03.14.62
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Coolant
Radiator
Thermal
Spacecraft
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