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