Prandtl-Meyer Supersonic Expansion Fan Calculator
Calculate downstream Mach number (M2), isentropic static pressure and temperature drops, and expansion fan Mach wave angles around convex corners.
Initial Supersonic State & Turn Angle
Convex deflection away from flow
Expanded Flow State & Fan Boundary Angles
Downstream Mach Number (M2):
—
ΔM = + —
Downstream Static Pressure (P2):
—
P2 / P1 = —
Prandtl-Meyer Function ν(M1):
— °
Downstream PM Function ν(M2):
— °
Leading Mach Wave Angle (μ1):
—
Trailing Mach Wave Angle (μ2):
—