Prandtl-Meyer Expansion Angle Calculations


 
This form calculates properties of a supersonic flow through an expansion angle.The required input is the Mach number of the upstream flow and the expansion angle (θ). The gas is assumed to be ideal air. (γ=1.4)
Note: Flow separation at sharp corners due to viscous effects are ignored in these calculations.

Inputs
Upstream Mach Number (M1)

 
Expansion angle for flow (θ)(deg)

 
Results
Downstream Mach Number (M2) = 2.00000

 
Note: For results where M2=NAN -- indicates that expansion angle input is greater than the maximum permitted for upstream Mach number. Maximum turning angle shown in red.