Download All

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
View all files

5.0

5.0 | 2 ratings Rate this file 27 Downloads (last 30 days) File Size: 23.05 KB File ID: #15442

Wing Designer

by John

27 Jun 2007 (Updated 02 Jul 2007)

Wing Designer computes aircraft performance measures from wing and engine parameters.

| Watch this File

File Information

Description

Wing Designer was written by Phillip J. Root and John R. Rogers

main.m will run the program.

Wing Designer was written as an educational tool to teach the concepts of engineering design trade-off and parametric analysis. The user selects airfoil cross sections from a menu, enters wing span, dihedral angle, sweep, angle of attack, and engine parameters. The program calculates a score based on the aircraft performance. Lift, drag, range and other performance measures are calculated. Range in miles is the basis for the score, and several modifications are made for other measures such as wing span and bending moment. It is not intended for use in designing real aircraft.

MATLAB release

MATLAB 7.1.0 (R14SP3)

Tags for This File
Everyone's Tags	aerodef, aeronautics, aerospace, aircraft, airfoil(2), design(2), performance, wing
Tags I've Applied
Add New Tags	Please login to tag files.

Comments and Ratings (3)
21 Jun 2008	MAHABOOB BASHA
26 Sep 2008	DRAGO MATJASEC	ok
22 Feb 2009	ZerO	I like ur own comment,specially the last line ,really true ,good luck.

Please login to add a comment or rating.

Updates
02 Jul 2007	Fixed typo in description

Tag Activity for this File
Tag	Applied By	Date/Time
aerospace	John	22 Oct 2008 09:17:36
aeronautics	John	22 Oct 2008 09:17:36
aerodef	John	22 Oct 2008 09:17:36
airfoil	John	22 Oct 2008 09:17:36
aircraft	John	22 Oct 2008 09:17:36
design	John	22 Oct 2008 09:17:36
wing	John	22 Oct 2008 09:17:36
performance	John	22 Oct 2008 09:17:36
design	ali mehmani	04 Nov 2009 05:19:09
airfoil	ali mehmani	04 Nov 2009 05:19:11

Highlights from Wing Designer

Wing Designer

Highlights from
Wing Designer