Nozzle design using Method of Characteristics

This form allows the calcualtion or design of supersonic nozzle parameters for two dimensional and axi-symmetric flows.

Input Parameters Pressure Altitude (ft) Exhaust Ratio of Specific Heats (γ) Throat Stagnation Pressure (P0 psi) Throat Stagnation Temp. (T0 oR) Required Exit Mach Number (Me) Type of Solution

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