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 Type of Solution2-D Ideal NozzleAxi-Symmetric Ideal NozzlePressure Altitude (ft)Exhaust Ratio of Specific Heats (γ)Throat Stagnation Pressure (P0 psi)Throat Stagnation Temp. (T0 oR)Required Exit Mach Number (Me)Plot VariablesMach Pressure [Current Geometry]Back to Method of Characteristics Section