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Path: ACPro/ACPerformance
% Compute flight equilibrium.
Ground effect is included and the scale factor is the square root of s.
This uses DragCoeff for the drag coefficients. If the altitude is zero
then the gravity force is assumed to be zero.
Type FlightEquilibrium for a demo
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Form:
d = FlightEquilibrium( gamma, h, v, d )
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Inputs
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gamma (1,:) Flight path angle (deg)
h (1,:) Altitude (m)
v (1,:) Velocity (m/s)
d (1,1) Data structure
.mass (1,1) Mass (kg)
.s (1,1) Reference area (m^2)
.cLAlpha (1,1) Lift coefficient
.length (1,1) Representative length (e.g. mean chord) (m)
.oswaldEff (1,1) Oswald efficiency factor (optional)
.aspectRatio (1,1) Aspect ratio for wing (length/mean chord)
.thickness (1,1) Ratio of length to thickness
.m1Peak (1,1) Peak at M = 1 an alternative to zetaTrans
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Outputs
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d (1,1) Data structure
.m (1,:) Mach number
.rho (1,:) Atmospheric density (kg/m^3)
.t (1,:) Stagnation temperature (deg-K)
.q (1,:) Dynamica pressure (N/m^2)
.drag (1,:) Drag force (N)
.lift (1,:) Lift force (N)
.thrust (1,:) Thrust force (N)
.cD0 (1,:) Drag coefficient
.kI (1,:) Induced drag coefficient
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ACPro: ACProAerodynamics/DragCoeff ACPro: ACProAerodynamics/GroundEffect AerospaceUtils: AtmosphericCalculations/TemperatureStagnation Common: Atmosphere/StdAtm Common: Database/Constant Common: Graphics/Plot2D Math: Trigonometry/CosD Math: Trigonometry/SinD
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