Computer code, RTE, developed to perform three-dimensional thermal analyses of rocket thrust chambers. Calculates rate of heat transfer from combustion gases to coolant, coolant-temperature rise and pressure drop, and temperature profiles within cooling-jacket wall. Also calculates combustion-gas wall static pressure, temperature and enthalpy, as well as coolant pressure, temperature, and mach number for all stations. Program used for any propellant combination and most coolants commonly used in rockets. Code used for both regeneratively and radiatively cooled engines. However, in case of regeneratively cooled engines, applicability limited to engines featuring single-pass cooling and rectangular cooling channels.
Analyzing Thermal Conditions In Rocket Engines
NASA Tech Briefs ; 18 , 3
1994-03-01
Miscellaneous
No indication
English
Analyzing Thermal Conditions in Rocket-Engines
Online Contents | 1994
Thermal nuclear rocket engines
Online Contents | 2000
Engineering Index Backfile | 1957
|Engineering Index Backfile | 1957
|Engineering Index Backfile | 1957
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