The Mach number does not reach 1 in the duct. The flow is sonic at the throat and the exit. The Mach number does not reach 1 in the duct.
Flow is sonic at the throat.
Iteration loop to calculate normal shock location. If so, then print results and end. Iteration loop to calculate normal shock location. This project is in development. While we have not fully validated the code, many test cases have been run correctly.