Path: ACPro/ACProAerodynamics
% Lift and drag using the R.T. Jones, Sears, and Haack model.
This is for the minimum drag of a supersonic body with fixed
lift, span, length, and volume. Either d.h or d.p is needed.
if cL is not entered it will compute the optimal cL.
Volume and surface area includes fuselage and wings.
Type LiftAndDragJonesHaackSears for a demo.
--------------------------------------------------------------------------
Forms:
d = LiftAndDragJonesSearsHaack; % default data structure
[lift, dragTotal, qCL, cD] = LiftAndDragJonesSearsHaack( m, d )
--------------------------------------------------------------------------
------
Inputs
------
m (1,1) Mach number
d (.) Data structure
.l (1,1) Aircraft length (m)
.h (1,:) Altitude (m)
.p (.) Standard Atmosphere struct
.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)
.cL (1,1) Lift coefficient
.alpha (1,1) Angle of attack
------
Outputs
-------
lift (1,1) Lift (N)
dragTotal (1,1) Drag (N)
qCL (1,1) Dynamic pressure times lift coefficient (N/m^2)
cD (1,1) Drag coefficient
--------------------------------------------------------------------------
Reference: "Applied Aerodynamics: A Digital Textbook", Version 5.0,
January 2007, Desktop Aeronautics, Inc.
--------------------------------------------------------------------------
See also: ConcordeLD, SurfaceAreaEllipsoidRevolution, StdAtm,
CDSkinFriction
--------------------------------------------------------------------------
ACPro: ACProAerodynamics/CDSkinFriction ACPro: ACProAerodynamics/ConcordeLD 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
Back to the ACPro Module page