This program calculates the exit properties of a compressible gas flowing adiabatically (no heat transfer) in a round, constant diameter pipe of length L with friction. Neither the initial velocity nor the exit velocity can exceed sonic velocity. The compressible pressure loss is compared to the incompressible pressure loss. The stagnation properties are calculated.
This application solves the Fanno equation for
sub-sonic flow. Note; the Fanno equation can have two solutions (one subsonice, the other supersonic). While both are valid solutions, for the purposes of this application, only the subsonic region is presented. Therefore, the initial and exit Mach Numbers must always be less than 1.0.
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