Isentropic Expansion 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 (theta). The gas is assumed to be ideal air.   Tabulated Data
Inputs Upstream Mach Number (M1)   Expansion angle for flow (theta)(deg)	Results Downstream Mach Number (M2)   Note: NAN -- indicates that expansion angle input is greater than the maximum permitted for upstream Mach number.

(c) 2006 AMME, University of Sydney.