ThrustPropeller:

Path: AC/ACEngine

% Compute propeller thrust. 

   There are two options, 'power' or 'thrust'. With power the thrust is
   t = propeller efficiency*power/velocity

   If it is thrust the it is

     thrust = cT*rho*N^2*d^4

   where the constants are defined below.

   Type ThrustPropeller for a demo.
--------------------------------------------------------------------------
   Form:
   thrust = ThrustPropeller( 'thrust', rho, cT, N, d )
   thrust = ThrustPropeller( 'power', etaP, v, p )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   type            (1,:) 'power' or 'thrust'
   rho             (1,:) Density (kg/m^2)
   cT              (1,1) Thrust coefficient
   N               (1,1) RPS
   d               (1,1) Propeller diameter (m)
   etaP            (1,1) Propulsive efficiency
   v               (1,:) Velocity (m/s
   p               (1,1) Power (W)

   -------
   Outputs
   -------
   thrust          (1,:) Thrust (N)

--------------------------------------------------------------------------
   Reference: Mair, W. and D. L. Birdsall, "Aircraft Performance,"
              Cambridge, p.97.
--------------------------------------------------------------------------

Children:

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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