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FX 63-158 AIRFOIL (fx63158-il)

FX 63-158 AIRFOIL - Wortmann FX 63-158 airfoil


Airfoil fx63158-il
Details Dat file Parser  
(fx63158-il) FX 63-158 AIRFOIL
Wortmann FX 63-158 airfoil
Max thickness 15.8% at 33.9% chord.
Max camber 3.8% at 37.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
FX 63-158 AIRFOIL
       49.       49.

 0.0000000 0.0000000
 0.0010200 0.0082000
 0.0042200 0.0166100
 0.0096000 0.0240000
 0.0170200 0.0315500
 0.0265000 0.0390000
 0.0380200 0.0470600
 0.0515800 0.0538700
 0.0669400 0.0628500
 0.0842200 0.0695900
 0.1033000 0.0778700
 0.1240300 0.0840700
 0.1464300 0.0913200
 0.1703700 0.0966400
 0.1955800 0.1025600
 0.2222100 0.1066500
 0.2499800 0.1109200
 0.2789100 0.1134400
 0.3086100 0.1158100
 0.3393300 0.1164500
 0.3705600 0.1166200
 0.4024300 0.1151100
 0.4346900 0.1130600
 0.4673300 0.1094900
 0.4999700 0.1055700
 0.5327400 0.1007000
 0.5652500 0.0957800
 0.5975000 0.0902500
 0.6293800 0.0848300
 0.6607400 0.0790700
 0.6913300 0.0735400
 0.7211500 0.0677700
 0.7499501 0.0622400
 0.7777300 0.0566200
 0.8043500 0.0512400
 0.8297000 0.0458900
 0.8535000 0.0407900
 0.8753000 0.0358000
 0.8964400 0.0310900
 0.9157100 0.0265400
 0.9329900 0.0222900
 0.9484800 0.0182500
 0.9619200 0.0144600
 0.9734400 0.0108400
 0.9829100 0.0075000
 0.9903400 0.0046600
 0.9957100 0.0024100
 0.9989100 0.0008900
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0010200 -.0020000
 0.0042200 -.0043000
 0.0096000 -.0071900
 0.0170200 -.0095000
 0.0265000 -.0128400
 0.0380200 -.0149800
 0.0515800 -.0190100
 0.0669400 -.0220000
 0.0842200 -.0248000
 0.1033000 -.0268000
 0.1240300 -.0300900
 0.1464300 -.0318900
 0.1703700 -.0347000
 0.1955800 -.0361600
 0.2222100 -.0383600
 0.2499800 -.0392700
 0.2789100 -.0407400
 0.3086100 -.0410300
 0.3393300 -.0416900
 0.3705600 -.0412200
 0.4024300 -.0409600
 0.4346900 -.0396700
 0.4673300 -.0384700
 0.4999700 -.0363100
 0.5327400 -.0340200
 0.5652500 -.0304900
 0.5975000 -.0262900
 0.6293800 -.0208000
 0.6607400 -.0150900
 0.6913300 -.0092000
 0.7211500 -.0039700
 0.7499501 0.0009100
 0.7777300 0.0048200
 0.8043500 0.0081400
 0.8297000 0.0105200
 0.8535000 0.0122700
 0.8753000 0.0131600
 0.8964400 0.0135000
 0.9157100 0.0131600
 0.9329900 0.0123400
 0.9484800 0.0109800
 0.9619200 0.0091900
 0.9734400 0.0070900
 0.9829100 0.0048700
 0.9903400 0.0028600
 0.9957100 0.0012600
 0.9989100 0.0002500
 1.0000000 0.0000000
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Polars for FX 63-158 AIRFOIL (fx63158-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx63158-il50,00096.7 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx63158-il50,000518.8 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx63158-il100,000947.5 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx63158-il100,000551.4 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx63158-il200,000972.4 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx63158-il200,000567.9 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   fx63158-il500,000976.9 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx63158-il500,000570.4 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx63158-il1,000,000985 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx63158-il1,000,000581.9 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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