Two-dimensional finite difference program for thermal analysis of rocket thrust chambers
Technical Report
·
OSTI ID:5481617
A two-dimensional finite difference computer model for thermal analysis of rocket thrust chambers has been developed. The model uses an iterative scheme for calculating the temperature distribution within the chamber wall and implements a successive overrelaxation formula for a quick convergence. The inputs of the models are the dimensions of the thrust chamber wall, types of materials used, heat transfer coefficients and temperatures of the hot gas and the coolant. The resulting output of the program consists of the nodal temperature distribution, heat transfer to the coolant and heat transfer from the hot gas.
- Research Organization:
- National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center
- OSTI ID:
- 5481617
- Report Number(s):
- N-88-12539; NASA-TM-100191; E-3773; NAS-1.15:100191
- Country of Publication:
- United States
- Language:
- English
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