The concentration of this numerical investigation is focused to generate data for developing optimum profile of Supersonic nozzle irrespective of the altitude of operation. The investigation has been carried out for different altitudes when the combustion conditions including combustion temperature, combustion pressure, specific heat ratio and molecular weight remain unchanged. Considering the aerodynamic issues, method of characteristics is chosen for profile generation. During the application of method of characteristics, exit pressure to atmospheric pressure ratio is maintained unity. The coding has been done in the MATLAB interface with an aim to generate maximum thrust at the outlet of the optimized supersonic nozzle. Both Mach and pressure distribution for maximum thrust generation are within the domain of interest of this investigation.
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[v1] 2012-08-19 10:37:55
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