MassFlow:

Path: ACPro/ACEngine

% Computes the mass flow divided by the inlet area. The code
   is based on a constant Mach number at station 2 which is the exit
   of the diffuser and inlet to the fan or compressor.
--------------------------------------------------------------------------
   Form:
   mDot = MassFlow( m0, p0, t0, piDMax, eD, gamma, r, m2, units )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   m0         (1,:)   Inlet mach number
   p0         (1,1)   Inlet pressure
   t0         (1,1)   Inlet temperature
   piDMax     (1,1)   Maximum diffuser pressure ratio
   eD         (1,1)   Diffuser efficiency
   gamma      (1,1)   Rate of specific heats, cP/cV
   r          (1,1)   Gas constant
   m2         (1,1)   Mach number at exit of diffuser
   units      (1,:)   'eng' or 'mks'

   -------
   Outputs
   -------
   mDot       (1,:)   Mass flow

--------------------------------------------------------------------------

Children:

ACPro: ACEngine/AOverAStar
ACPro: ACEngine/MassFlowParameterR
ACPro: ACEngine/RamRecovery
AerospaceUtils: AeroData/AtmData
AerospaceUtils: AtmosphericCalculations/AtmGamma
Common: Atmosphere/StdAtm
Common: CommonData/SwooshWatermark
Common: General/CellToMat
Common: General/MatToCell
Common: General/Watermark
Common: Graphics/NewFig
Common: Graphics/Plot2D
Common: Graphics/PltStyle

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