StagnationPAndT:

Path: ACPro/ACThermal

% Stagnation conditions for a gas.
 Computes the ratio between stagnation M = 0 and the
 input Mach number.

 Type Stagnation for a demo.

 Demos gives the results for air, gamma = 1.4 from Mach 0 to 6.
--------------------------------------------------------------------------
   Form:
   [pR, tR] = Stagnation( m, gamma )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   m           (1,:) Mach number
   gamma       (1,1) Ratio of specific heats

   -------
   Outputs
   -------
   pR          (1,:) Pressure ratio
   tR          (1,:) Temperature ratio

--------------------------------------------------------------------------
   Reference: P. G. Hill, C. R. Peterson, "The Mechanics and Thermodynamics
              of Propulsion," Addison-Wesley, 1965, pp. 151-154.
--------------------------------------------------------------------------

Children:

Common: Graphics/Plot2D

Back to the ACPro Module page