INFORMATION ABOUT SOARTECHSOARTECH_INFORMATION


Soartech Airfoil performance data can be imported using this facility. There are three volumes of performance data. Each file is named dragnn.txt, where nn = volume number. Eg; drag01.txt is volume one of the Airfoil Data Files. Please note that this format is different to the previous format (prior to 1998). Winfoil was modified to cater for this change in version 2.2.7. Registered users can download the latest version of Winfoil from the Winfoil website at; 

http://www.winfoil.com. The file coordnn.txt (nn = volume number) is also provided with this data. To import the coordinates you will need to manually extract each airfoil and save each to a separate file. See Soartech Airfoil ImportSOARTECH topic on the format of the data. A sample of the Lift/Drag data format of this data  is shown below;


::::::::::::::

A18.DRG

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Airfoil: A18

Builder: R. Cooney

Comment: clean


Number of Reynolds #'s:

 7 


Average Reynolds #:

 40000 

Number of angles of attack:

 7 

 alpha /   Cl   /  Cd   /  Spanwise Cd's >>>

 -1.16   0.117   0.0244   0.0247   0.0203   0.0290   0.0236

  0.93   0.324   0.0202   0.0155   0.0237   0.0253   0.0164

  2.82   0.540   0.0349   0.0363   0.0353   0.0396   0.0286

  5.05   0.842   0.0405   0.0350   0.0401   0.0471   0.0397

  7.04   1.007   0.0314   0.0316   0.0402   0.0284   0.0256

  9.08   1.108   0.0283   0.0254   0.0371   0.0270   0.0237

 11.10   1.155   0.0572   0.0516   0.0734   0.0510   0.0525

Tabulated from data in file MS00278.DAT & reduced using program Q01.00L


This data format repeats for each set.


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).

Winfoil will attempt to match the data with existing airfoils. If the airfoil is found it will then load the data otherwise you will be prompted to select an airfoil that matches. You are provided with an option to skip the import for a selected airfoil.


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.