Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 63-147 AIRFOIL (fx63147-il)

FX 63-147 AIRFOIL - Wortmann FX 63-147 airfoil


Airfoil fx63147-il
Details Dat file Parser  
(fx63147-il) FX 63-147 AIRFOIL
Wortmann FX 63-147 airfoil
Max thickness 14.7% at 33.9% chord.
Max camber 3.1% at 33.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
FX 63-147 AIRFOIL
       49.       49.

 0.0000000 0.0000000
 0.0010200 0.0054700
 0.0042200 0.0128000
 0.0096000 0.0187600
 0.0170200 0.0263300
 0.0265000 0.0333600
 0.0380200 0.0411300
 0.0515800 0.0483800
 0.0669400 0.0560000
 0.0842200 0.0630300
 0.1033000 0.0701700
 0.1240300 0.0766200
 0.1464300 0.0828600
 0.1703700 0.0883100
 0.1955800 0.0932700
 0.2222100 0.0972900
 0.2499800 0.1006200
 0.2789100 0.1029600
 0.3086100 0.1044800
 0.3393300 0.1050500
 0.3705600 0.1048400
 0.4024300 0.1037100
 0.4346900 0.1018400
 0.4673300 0.0991700
 0.4999700 0.0959600
 0.5327400 0.0922200
 0.5652500 0.0881500
 0.5975000 0.0837200
 0.6293800 0.0790700
 0.6607400 0.0742500
 0.6913300 0.0693000
 0.7211500 0.0642700
 0.7499501 0.0592100
 0.7777300 0.0541700
 0.8043600 0.0492100
 0.8297000 0.0443800
 0.8535000 0.0396400
 0.8759000 0.0350100
 0.8964400 0.0305200
 0.9157100 0.0261700
 0.9329900 0.0219800
 0.9484800 0.0179300
 0.9619200 0.0140400
 0.9734400 0.0102800
 0.9829100 0.0068300
 0.9903400 0.0038800
 0.9957100 0.0016500
 0.9989100 0.0003000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0010200 -.0025800
 0.0042200 -.0048500
 0.0096000 -.0083700
 0.0170200 -.0111900
 0.0265000 -.0146100
 0.0380200 -.0173600
 0.0515800 -.0204300
 0.0669400 -.0229400
 0.0842200 -.0257300
 0.1033000 -.0281300
 0.1240300 -.0307100
 0.1464300 -.0329000
 0.1703700 -.0351400
 0.1955800 -.0369400
 0.2222100 -.0387000
 0.2499800 -.0400200
 0.2789100 -.0411800
 0.3086100 -.0419000
 0.3393300 -.0424400
 0.3705600 -.0425100
 0.4024300 -.0423400
 0.4346900 -.0417400
 0.4673300 -.0409300
 0.4999700 -.0397300
 0.5327400 -.0382800
 0.5652500 -.0363500
 0.5975000 -.0341900
 0.6293800 -.0315600
 0.6607400 -.0285900
 0.6913300 -.0251300
 0.7211500 -.0213200
 0.7499501 -.0171400
 0.7777300 -.0127200
 0.8043600 -.0081700
 0.8297000 -.0035500
 0.8535000 0.0007300
 0.8759000 0.0043100
 0.8964400 0.0069000
 0.9157100 0.0086200
 0.9329900 0.0094600
 0.9484800 0.0095400
 0.9619200 0.0088800
 0.9734400 0.0076000
 0.9829100 0.0058500
 0.9903400 0.0039100
 0.9957100 0.0021200
 0.9989100 0.0006800
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

FX 61-147 AIRFOILPreviewDetails
FX 63-143 AIRFOILPreviewDetails
Eiffel 371 (Monge)PreviewDetails
MB253515 15.0% smoothedPreviewDetails
USA 48 AIRFOILPreviewDetails
AH 93-W-145PreviewDetails
S2027PreviewDetails
RAF-48 AIRFOILPreviewDetails
AVISTARPreviewDetails
FX 79-W-151 APreviewDetails

Polars for FX 63-147 AIRFOIL (fx63147-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx63147-il50,000918.6 at α=13°Mach=0 Ncrit=9Xfoil predictionDetails
   fx63147-il50,000527.5 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx63147-il100,000947.6 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   fx63147-il100,000548.6 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx63147-il200,000968.6 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx63147-il200,000563.8 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   fx63147-il500,000984.4 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx63147-il500,000584.5 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx63147-il1,000,000597.3 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx63147-il1,000,0000103.6 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit