Path: ACPro/ACPerformance
% Compute glide angle, range and velocity..
Type Glide for a demo of a Cessna 172. In this example we add a
parasitic drag cofficient of 0.21 to account for the fuselage.
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Form:
[angle, v, r] = Glide( h, v, d, cL )
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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)
.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
cL (1,:) Lift coefficient (otpional)
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Outputs
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angle (1,:) Glide angle
v (1,:) Glide velocity
r (1,:) Glide range
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Reference: Anderson, J. D., "Introduction to Flight 3rd Edition,",
McGraw-Hill 1989, pp 294-297.
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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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