Highlights from
Wing Designer
- 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
- InitializeGUI(airfoildata) Initializes the GUI and establishes callback functions
- 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
- View all files
Wing Designer
27 Jun 2007 (Updated 02 Jul 2007) Wing Designer computes aircraft performance measures from wing and engine parameters. |
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