JavaFoil has replaced CalcFoil. The PEF file format has changed and Winfoil 3.0 has been modified to support the new format.

Martin Hepperle’s JavaFoil http://www.mh-aerotools.de/ !JumpHtml(`http://www.mh-aerotools.de/') program can analyse an airfoil given the airfoil coordinates and selected Reynolds Number(s) for the analysis. Winfoil can now call JavaFoil directly to perform the analysis and once completed can load the generated data back into Winfoil. For details on how to do this please see;

JavaFoil Polar Analysispolar_analysis 


Alternatively JavaFoil can be run manually to generate a PEF file. You can then import the file using this facility.


To import;

1. Select click on the JavaFoil airfoil PEF File radio button.

2. Click on the Ok button.

3. Select the appropriate file from a directory on your computer and click on the OK button.


Winfoil will validate the contents of the file and if the data is found to be invalid you will be notified as to the cause of the error. Winfoil will also automatically format the data to match your Regional settings for numbers. Therefore if your number format uses commas for the decimal point Winfoil will automatically convert all numeric values in the file to use commas for the decimal point.


If Winfoil cannot find an airfoil with the same name then you will be prompted to select an airfoil from the Winfoil database so that the data can be linked and loaded for that airfoil. 


A sample of a PEF file is shown below;


[Airfoil] 

Description1=SD5060

NumberSets=1


[Set1]

Origin=CalcFoil Analysis

Description1=Copyright 1996 Martin Hepperle

NumberPolars=1


[Set1-Polar1]

ReynoldsNumber=100000

NumberPoints=21

Values=Alpha  Cl  Cd  Cm  xtu  xtl

Value01=-10.000000 -0.623419 0.078998 -0.026668 0.851780 0.057911

Value02=-9.000000 -0.572535 0.068058 -0.026804 0.832877 0.058310

Value03=-8.000000 -0.503818 0.060154 -0.025343 0.821254 0.042124

Value04=-7.000000 -0.427679 0.052219 -0.025529 0.805105 0.042640

Value05=-6.000000 -0.345242 0.045709 -0.025751 0.776997 0.043298

Value06=-5.000000 -0.257124 0.041230 -0.024598 0.756258 0.031911

Value07=-4.000000 -0.166486 0.037077 -0.025061 0.735154 0.033615

Value08=-3.000000 -0.090704 0.014372 -0.047755 0.715523 0.036887

Value09=-2.000000 0.026349 0.013531 -0.048152 0.688946 0.186104

Value10=-1.000000 0.144228 0.013109 -0.048216 0.656919 0.276494

Value11=0.000000 0.262014 0.011852 -0.048402 0.611257 0.741718

Value12=1.000000 0.379504 0.012065 -0.048603 0.576781 0.840401

Value13=2.000000 0.496609 0.012662 -0.048800 0.484321 0.978305

Value14=3.000000 0.612911 0.013901 -0.049012 0.375018 0.997373

Value15=4.000000 0.727511 0.015399 -0.049223 0.285638 0.997796

Value16=5.000000 0.836784 0.018537 -0.049260 0.055103 0.998148

Value17=6.000000 0.936203 0.020175 -0.049181 0.049242 0.998459

Value18=7.000000 1.021604 0.022141 -0.049055 0.039942 0.998713

Value19=8.000000 0.903033 0.051736 -0.026528 0.037774 0.998965

Value20=9.000000 0.950730 0.059744 -0.026419 0.036580 0.999188

Value21=10.000000 0.985629 0.067253 -0.028651 0.055417 0.999374


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.