Airfoil ListAirfoil_List 

Other Available Tabs;

Airfoil Coordinates TabAirfoil_Coordinates_Tab 

Airfoil Polar GraphAirfoil_Polar_Graph 

Lift Graph TabLift_Graph_Tab 

Lift Drag Data Maintenance TabLift_Drag_Data_Maintenance_Tab 

Airfoil CAD TabAirfoil_CAD_Tab 


This tab lists all available Airfoils stored in the Winfoil Database. Selection of an airfoil from the list will make Winfoil Plot the airfoil section in the box provided. Any comments about the airfoil will be listed in the box directly under the airfoil plot.

If Lift and Drag data is available for the selected airfoil then the following picture will be displayed to the right of the airfoil name on this tab;


The List on the left side of the screen contains the following information;

Airfoil Name

CL MAX is the maximum lift coefficient of the airfoil. The higher this value the greater the amount of lift that the airfoil generates. A short take off and landing aircraft requires a high lift airfoil therefore one would select an airfoil with a very high CL ( Coefficient of lift).

CD MIN is the minimum drag coefficient. An airfoil with a low drag coefficient and good lift coefficient will provide excellent gliding performance. A high drag airfoil will provide poor glide performance ,acceleration and climb performance.

CM MAX is the maximum pitching moment coefficient. A positive value means that the airfoil will pitch up , a negative value means that the airfoil will pitch down.  Tailless aircraft require a positive pitching moment for pitch stability. Therefore one would choose an airfoil with a  positive pitching moment . This can also be achieved with an airfoil with zero pitching moment (eg; symmetrical) and a control deflection upwards eg; up elevator. The larger the pitching coefficient the greater the force required to balance the aircraft. To minimise tail areas for minimal drag on conventional wing and tail designs one would select an airfoil with a low pitching moment.

Thickness is the maximum thickness of the airfoil. ie; a Thickness = 10.00 means that the airfoils maximum thickness is ten percent.

Thickness Position is the chordwise location of the airfoils maximum thickness (expressed as a percentage of the chord).

Camber  is the maximum camber of the airfoil expressed as a percentage of the chord.

Camber Position is the chordwise position of the airfoils maximum camber (expressed as a percentage)


The airfoil performance data has been obtained with permission from SOARTECH SOARTECH .Data in the airfoil list screen is for the lowest Reynolds number. Typically airfoil performance improves with higher Reynolds numbers therefore it is more important to have details on performance at low Reynolds numbers.


This screen can also be accessed quickly from the toolbar by clicking on the

button or pressing the Ctrl key and the A key at the same time.



Adding a new Airfoil

See Airfoil ListAirfoil_List 


To Edit an Airfoil

Select the airfoil as above and click on the Airfoil Coordinates TabAirfoil_Coordinates_Tab   or the Airfoil CAD TabAirfoil_CAD_Tab .


To Print an Airfoil

Select  an airfoil by clicking on an airfoil in the list then select PRINT COMMANDPRINT_COMMAND 


from the FILE MENU .or click on the PRINT button in the toolbar.



Delete an Airfoil

Click on the DELETE button.


To search for a particular Airfoil

Click on the SEARCH button. This action will display the AIRFOIL SEARCHAIRFOIL_SEARCH screen.


To add or amend Airfoil Comments

Click on the Comments button to display the Airfoil CommentsAirfoil_Comments screen.


To rename an Airfoil

Click on the RENAME button.


To analyze an Airfoil

Click on the ANALYZEpolar_analysis button.


To select another screen

Select from the FILE menu or click on a button in the toolbar. The function of the button will be shown on the status bar at the left side of the bottom of the screen.