A Optimal Design of the Rocket Nozzle Wall by the Numerical Method

Details A Optimal Design of the Rocket Nozzle Wall by the Numerical Method A Optimal Design of the Rocket Nozzle Wall by the Numerical Method

Jun 1986

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1986jass....3...29k&link_type=abstract

Journal of Astronomy and Space Science, vol. 3, no. 1, p. 29-40.

Astronomy and Astrophysics

Astronomy

Scientific paper

It is the aims of this study to choose the materials and determine the material thickness of laminated Rocket Nozzle Wall operating at high pressure and high temperature. The heat conduction analysis of each layer was performed by Crank Nicolson method changing the thickness and the materials for the input data of Tungsten, Graphite, Alumina, Aluminum, Molybdenum, Plastic laminate. The results of the study of the study for pressure of 93.5 kg/cm2 and temperature of 3000 degC in the nozzle dia of 40 cm are as follows.

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