Test results of a low-temperature space radiator model are presented. Radiator performance is evaluated with a low-thermal-conductivity fluid in laminar flow in D-shaped cross-section tubes. The test covered a Reynolds number range from 50 to 4500 and a fluid temperature range from 294 to 414 K (70 to 286 F). For low-temperature radiators, the fluid-to-surface temperature differential was predominately influenced by fluid temperature in laminar flow. Heat transfer and pressure drop for the radiator tube could be predicted within engineering accuracy from existing correlations
The research for determining the space shuttle aerothermal environment is reported. Brief summaries ...
Minimum weight space radiator subsystems which can operate over heat load ranges wider than the capa...
Analysis of wall temperatures in rocket engine cooling system using D-shaped copper and stainless st...
Test results of a low-temperature space radiator model are presented. Radiator performance is evalua...
A low-temperature radiator has been designed to reject 17.62 kW of thermal power from an isotope Bra...
A space-type laminar flow radiator was designed and integrated with a 2- to 15-kilowatt Brayton elec...
A two dimensional finite volume method is used to predict the film coefficients in the transitional ...
Tests were designed to investigate the validity of the "modular" approach to space radiator system d...
An analysis of the performance of a low-temperature Brayton space radiator is presented. The cylindr...
Low temperature droplet stream radiators, using nonmetallic fluids, can be used to radiate large amo...
Results are presented of an analysis which compares the performance predictions of a thermal model o...
Many payloads currently proposed to be flown by the space shuttle system require long-duration cooli...
Concept development work on space heat rejection subsystems tailored to the requirements of various ...
This report discusses development and proof-of-concept testing of a new lightweight carbon-carbon (C...
An optimized flight-weight prototype fluid-header panel (heatpipe radiator system) was tested in a v...
The research for determining the space shuttle aerothermal environment is reported. Brief summaries ...
Minimum weight space radiator subsystems which can operate over heat load ranges wider than the capa...
Analysis of wall temperatures in rocket engine cooling system using D-shaped copper and stainless st...
Test results of a low-temperature space radiator model are presented. Radiator performance is evalua...
A low-temperature radiator has been designed to reject 17.62 kW of thermal power from an isotope Bra...
A space-type laminar flow radiator was designed and integrated with a 2- to 15-kilowatt Brayton elec...
A two dimensional finite volume method is used to predict the film coefficients in the transitional ...
Tests were designed to investigate the validity of the "modular" approach to space radiator system d...
An analysis of the performance of a low-temperature Brayton space radiator is presented. The cylindr...
Low temperature droplet stream radiators, using nonmetallic fluids, can be used to radiate large amo...
Results are presented of an analysis which compares the performance predictions of a thermal model o...
Many payloads currently proposed to be flown by the space shuttle system require long-duration cooli...
Concept development work on space heat rejection subsystems tailored to the requirements of various ...
This report discusses development and proof-of-concept testing of a new lightweight carbon-carbon (C...
An optimized flight-weight prototype fluid-header panel (heatpipe radiator system) was tested in a v...
The research for determining the space shuttle aerothermal environment is reported. Brief summaries ...
Minimum weight space radiator subsystems which can operate over heat load ranges wider than the capa...
Analysis of wall temperatures in rocket engine cooling system using D-shaped copper and stainless st...