DETERMINATION OF THE HEAT TRANSFER COEFFICIENT FOR SUBLIMATION OF SOLID CARBON DIOXIDE,
LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA
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Tests were conducted to determine the heat transfer coefficient for air flowing over solid carbon dioxide in order to provide design data for a missile cooling system utilizing this refrigerant. Heat transfer coefficients were obtained for a Reynolds Number range of 39,200 to 53,500 and inlet temperature of 70 to 130 F. It is believed that the turbulent flow data obtained is good to plus or minus 20 and that the representative curve may be within plus or minus 10 of the true heat transfer values for the range of Reynolds Numbers covered.
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