Path: ACPro/ModelCreation
% Propeller thrust
d.N and rho can be vectors. The thrust coefficient is a function of
advance ratio.
cT = CTFun( j ) where j = v/(n*d) where d is the diameter of the blade
and n is rad/s.
Type PropellerThrust for a demo
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Form:
thrust = PropellerThrust( x, rho, d )
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Inputs
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x (13,1) State [r;v;q;omega]
rho (1,:) Density (kg/m^3)
d (.) Data structure
.N (1,:) RPM
.cT (1,1) Thrust coefficent function
.d (1,1) Diameter of blade (m)
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Outputs
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t (1,:) Thrust (N)
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Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Linear/Mag
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