Path: ACPro/ACPerformance
% Compute climb angle
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 ClimbAngle for a demo
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Form:
gamma = ClimbAngle( h, v, d )
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Inputs
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h (1,:) Altitude (m)
v (1,:) Velocity (m/s)
d (.) Data structure
.mass (1,1) Mass (kg)
.s (1,1) Reference area (m^2)
.cLAlpha (1,1) Lift coefficient
.thrust (1,:) Thrust force (N)
.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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gamma (1,:) Climb angle
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See also DragCoeff
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AC: ACData/ACTConstants ACPro: ACProAerodynamics/CDSkinFriction ACPro: ACProAerodynamics/DragCoeff ACPro: ACProAerodynamics/FormDragCoeff ACPro: ACProAerodynamics/InducedDragCoeff ACPro: ACProAerodynamics/PrandtlGlauertCorrection AerospaceUtils: AeroData/AtmData SC: SCData/sCTConstants Common: Atmosphere/StdAtm Common: CommonData/Constants Common: CommonData/SwooshWatermark Common: CommonData/xSplashSmall Common: Database/Constant Common: General/CellToMat Common: General/DeleteCell Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Analysis/Logistic
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