Path: ACPro/ACProAerodynamics
% Compute drag loss using LiftAndDragJonesSearsHaack.
This function is most useful for supersonic vehicles. It gives you the
loss in delta-v due to drag. This routine uses Euler integration.
mdV/dt = T - D
dV = (T-D)*dt/m
dm/dt = -T/uE
Type DragLoss for a demo of the Concorde.
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Form:
dV = DragLoss( m, d )
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Inputs
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m (1,:) Mach number
d (.) Data structure
.l (1,1) Aircraft length (m)
.h (1,:) Altitude (m)
.p (1,1) Standard Atmosphere
.b (1,1) Span (m)
.s (1,1) Surface area (m^2)
.v (1,1) Volume (m^3)
.sL (1,1) Lifting surface (m^2)
.uE (1,1) Exhaust velocity (m/s)
.t (1,1) Thrust (N)
.m (1,1) Initial mass (kg)
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Outputs
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dV (1,:) Drag loss (m/s)
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ACPro: ACProAerodynamics/CDSkinFriction ACPro: ACProAerodynamics/ConcordeLD ACPro: ACProAerodynamics/LiftAndDragJonesSearsHaack ACPro: ACUtils/SurfaceAreaEllipsoidRevolution 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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