Airfoil List
Airfoil List
This screen is accessed by selecting the Airfoil List menu item from the File Menu or by clicking on the Airfoil List toolbar button.
The Airfoil List screen which was available in version 2.1 has been converted to an explorer style screen with a number of tabs. On the left is a pane containing a list of all airfoils, lift coefficients, drag coefficients, thickness to chord ratios , maximum camber and maximum camber location. This screen is resizeable and the left pane may be resized individually by clicking and dragging on the black vertical border just like Explorer in Windows 95. The size of the pane is stored by Winfoil so that the next time the screen is opened the pane will be restored to its originally selected size and position.
Creating a New Airfoil
1. Open the Airfoil List screen by selecting the Airfoil List menu item from the File Menu or
click on the Airfoil List toolbar button.
2. Click on the Airfoil tab.
3. Click on the New button.
4. You will then be prompted to either add an airfoil manually or to select the NACA airfoil wizard. If you are creating a new airfoil manually you must enter the name of the airfoil. If you enter the name of an airfoil which already exists an error message will be displayed and Winfoil will prevent you creating an airfoil with the same name. If you select the NACA Wizard option you will be shown the NACA Wizard screen. If you selected the manual option you have two ways of creating the new airfoil. You can either enter the coordinates by typing in values in the Coordinates Tab or enter coordinates in the CAD Tab.
Available Tabs;