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Prandtl-Meyer Expansion Calculator
Calculate supersonic expansion properties and final Mach number
Formula: ν(M) = √((γ+1)/(γ-1)) arctan(√((γ-1)/(γ+1)(M²-1))) - arctan(√(M²-1))
Computes final Mach number (M2) after flow turns by angle θ.
Computes final Mach number (M2) after flow turns by angle θ.
Aerodynamic Parameters
Calculation Results
⚠️ For compressible aerodynamics and aerospace engineering education reference only. Assumes steady, isentropic supersonic flow.