Path: ACPro/ACDesign
% Computes the thrust required for an aircraft trajectory
Type AircraftThrustFromFlight for a demo
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Form:
d = AircraftThrustFromFlight;
thrust = AircraftThrustFromFlight( h, v, vC, mass, d );
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Inputs
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h (1,:) Altitude (m)
v (1,:) Velocity (m/s)
vC (1,:) Rate of climb (m/s)
mass (1,:) Mass (kg)
d (.) Aircraft data structure
.e (1,1) Oswald efficiency
.aR (1,1) Aspect ratio
.s (1,1) Wing area (m^2)
.cD0 (1,1) Zero-lift drag coefficient, clean
.cLAlpha (1,1) Coefficient of lift over angle of attack
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Outputs
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thrust (1,:) Thrust (N)
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ACPro: ACProAerodynamics/InducedDragCoeff AerospaceUtils: AeroData/AtmData 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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