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《Journal of Astronautics》 1987-01
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IMPLICIT FORMULATION FOR CALCULATING THE UNSTEADY TEMPERATURE FIELD OF THE THRUST CHAMBER BY RADIATION COOLING

Cheng Huier(Shanghai Jiaotong University)  
Implicit difference formulation for calculating unsteady temperature field of the thrust chamber with radiation cooling for liquid rocket engine has been producted, and linearize treatment is accomplished. According to this can be compiled general program and has been calculated unsteady temperature history for any thrust chamber with radiation cooling.
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