This script determines whether a given nozzle pressure ratio (NPR) applied over a one-dimensional, C-D, Laval nozzle is strong enough to ensure the formation of a steady-state, shock-free, internal supersonic flow. It is based on the examples introduced in Anderson's "Modern Compressible Flows" (2003). The user may choose whether to introduce the expected exit Mach number or the exit-to-throat area ratio as inputs and the heat-capacity and nozzle pressure ratios. The mathematical model assumes one-dimensional, inviscid, steady-state, irrotational flow at moderate exit Mach numbers.
Ludovico Fossà (2021). 1D Convergent-Divergent Nozzle Shock Locator (https://www.mathworks.com/matlabcentral/fileexchange/85795-1d-convergent-divergent-nozzle-shock-locator), MATLAB Central File Exchange. Retrieved .
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