This function provides the ability to import Airfoil performance data from an ascii file.

To import;

1. Select click on the Winfoil Airfoil Performance Data radio button.

2. Click on the Ok button.


The import data file must follow the format shown below.


1. Performance Airfoil Data File 

This file contains the airfoil name, reynolds number, lift coefficient, drag coefficient, angle of attack and pitching moment coefficient. An example of the file layout is shown below. Please note the comma after each value.


AQUILA,59400,0.2610,0.0238,-1.8600,0.0000

AQUILA,59400,0.3520,0.0224,-0.8300,0.0000

AQUILA,59400,0.4450,0.0213,0.1800,0.0000

AQUILA,59400,0.5250,0.0224,1.2000,0.0000

AQUILA,59400,0.6070,0.0298,2.2300,0.0000

AQUILA,59400,0.6860,0.0291,3.2300,0.0000

AQUILA,59400,0.7640,0.0354,4.2600,0.0000

AQUILA,59400,0.8390,0.0358,5.2700,0.0000

AQUILA,59400,0.9110,0.0404,6.2800,0.0000

AQUILA,59400,0.9890,0.0373,7.3000,0.0000

AQUILA,59400,1.0610,0.0383,8.3300,0.0000

AQUILA,59400,1.1200,0.0422,9.3400,0.0000

AQUILA,59400,1.1480,0.0507,10.3400,0.0000


The data must appear in the same sequence when viewed using a text editor such as the windows Notepad (ie. carriage returns at the end of each line).


After this data is loaded the maximum lift coefficient, minimum drag coefficient and maximum picthing moment can be quickly found and set for the airfoil by clicking on the airfoil coordinates tab and clicking on the LookupLookup_Airfoil_Performance_Data  button at the bottom of the tab.