Supersonic Flow Analysis
Solving 2D Flowfield for Velocity, Temperature, Pressure and Density
Supersonic Flow Analysis
NozzlePy is capable of computing the complete supersonic flow field inside the nozzle. For the Ideal Nozzle and the Truncated Ideal Contour (TIC), the Method of Characteristics (MoC) directly provides the Mach number at each characteristic point within the flow field.
Based on the local Mach number, the flow velocity, temperature, pressure, and density are obtained using the isentropic flow relations in combination with ideal gas equations.
For the Thrust Optimized Parabola (TOP) method, an additional characteristic mesh is generated for the flow analysis. In this case, the previously computed TOP contour is used as a boundary condition for the construction of the characteristic network. From here on, the caculation is similar to the ideal expansion case.