Wing Designer: All Files - File Exchange

No BSD License

Highlights from
Wing Designer

InitializeGUI(airfoildata) Initializes the GUI and establishes callback functions
DeterminePanelGeometry(inputg... find coordinates for horseshoe vortices and control points and plot
DetermineProfileDrag(airfoild... Determine the wing profile drag from the airfoils' drag polars
FinalOutput(CL, CDi, CD0, y_c... calculate score and other outputs, post to the GUI
GetGeometryfromGUI(root, tip,... Get parameters from the GUI and create geometry structure "geo"
InducedDrag(gamma, geo, panel... Calculate far field induced drag
LiftCoeff(gamma, panel, geo, ... Determine the lift coefficient given the vortex strengths
PerformRegression(data) Relate the coefficients of the drag polar to Re as parabolic functions.
SpanLoading(l_s, l_t, CL, geo... Determine center of pressure and spanwise loading
StandardAtmosphere(alt) Read in altitude and output viscosity, density, and speed of sound
ZeroOutput(output) Null output to GUI when error checking is not satisfied
[C,T,A]=naca4_3d(airfoil,y,nc... determine airfoil skin and camber coordinates from NACA designation
[gamma, Fu_bar, Fv_bar, Fw_ba... Implement Vortex Lattice Method
parseNACAairfoildata parse the text file NACAdata.txt into a structure
Contents.m
Main.m
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from Wing Designer by John Rogers
Wing Designer computes aircraft performance measures from wing and engine parameters.

All files for Wing Designer

/Contents.m
/DeterminePanelGeometry.m
/DetermineProfileDrag.m
/FinalOutput.m
/GetGeometryfromGUI.m
/InducedDrag.m
/InitializeGUI.m
/LiftCoeff.m
/Main.m
/NACAdata.txt
/NacaCoord.m
/PerformRegression.m
/SpanLoading.m
/StandardAtmosphere.m
/VortexStrength.m
/ZeroOutput.m
/parseNACAairfoildata.m

Highlights from Wing Designer

Highlights from
Wing Designer