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.
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Form:
thrust = ThrustPropeller( 'thrust', rho, cT, N, d )
thrust = ThrustPropeller( 'power', etaP, v, p )
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Inputs
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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)
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Outputs
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thrust (1,:) Thrust (N)
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Reference: Mair, W. and D. L. Birdsall, "Aircraft Performance,"
Cambridge, p.97.
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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
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