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FX 61-168 AIRFOIL (fx61168-il)

FX 61-168 AIRFOIL - Wortmann FX 61-168 airfoil


Airfoil fx61168-il
Details Dat file Parser  
(fx61168-il) FX 61-168 AIRFOIL
Wortmann FX 61-168 airfoil
Max thickness 16.8% at 37.1% chord.
Max camber 3% at 37.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
FX 61-168 AIRFOIL
       49.       49.

 0.0000000 0.0000000
 0.0010200 0.0066800
 0.0042200 0.0137700
 0.0096000 0.0210700
 0.0170200 0.0286100
 0.0265000 0.0364300
 0.0380200 0.0445300
 0.0515800 0.0525600
 0.0669400 0.0604900
 0.0842200 0.0680800
 0.1033000 0.0753800
 0.1240300 0.0821900
 0.1464300 0.0886100
 0.1703700 0.0944200
 0.1955800 0.0996600
 0.2222100 0.1041300
 0.2499800 0.1078600
 0.2789100 0.1106900
 0.3086100 0.1126900
 0.3393300 0.1137300
 0.3705600 0.1139300
 0.4024300 0.1131600
 0.4346900 0.1114600
 0.4673300 0.1086400
 0.4999700 0.1048200
 0.5327400 0.1000700
 0.5652500 0.0947400
 0.5975000 0.0890400
 0.6293800 0.0832500
 0.6607400 0.0773800
 0.6913300 0.0715400
 0.7211500 0.0657100
 0.7499501 0.0599900
 0.7777300 0.0543700
 0.8043500 0.0489600
 0.8297000 0.0437500
 0.8535000 0.0387800
 0.8759000 0.0340300
 0.8964400 0.0295300
 0.9157100 0.0252500
 0.9329900 0.0212100
 0.9484800 0.0174100
 0.9619200 0.0138200
 0.9734400 0.0104700
 0.9829100 0.0074100
 0.9903400 0.0048400
 0.9957100 0.0026600
 0.9989100 0.0009900
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0010200 -.0021900
 0.0042200 -.0055200
 0.0096000 -.0090100
 0.0170200 -.0125800
 0.0265000 -.0163000
 0.0380200 -.0199600
 0.0515800 -.0236600
 0.0669400 -.0272800
 0.0842200 -.0308700
 0.1033000 -.0343300
 0.1240300 -.0377100
 0.1464300 -.0409000
 0.1703700 -.0438900
 0.1955800 -.0467300
 0.2222100 -.0491900
 0.2499800 -.0512000
 0.2789100 -.0526700
 0.3086100 -.0536300
 0.3393300 -.0540700
 0.3705600 -.0541300
 0.4024300 -.0535800
 0.4346900 -.0523800
 0.4673300 -.0504500
 0.4999700 -.0478400
 0.5327400 -.0445700
 0.5652500 -.0405800
 0.5975000 -.0357600
 0.6293800 -.0301900
 0.6607400 -.0241800
 0.6913300 -.0181700
 0.7211500 -.0126200
 0.7499501 -.0077000
 0.7777300 -.0034500
 0.8043500 0.0001400
 0.8297000 0.0030800
 0.8535000 0.0053700
 0.8759000 0.0070100
 0.8964400 0.0080500
 0.9157100 0.0085100
 0.9329900 0.0084400
 0.9484800 0.0078800
 0.9619200 0.0069100
 0.9734400 0.0056100
 0.9829100 0.0041200
 0.9903400 0.0028100
 0.9957100 0.0015000
 0.9989100 0.0004000
 1.0000000 0.0000000
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Lednicer format dat file
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Polars for FX 61-168 AIRFOIL (fx61168-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx61168-il50,00095.1 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx61168-il50,000515.4 at α=12°Mach=0 Ncrit=5Xfoil predictionDetails
   fx61168-il100,000944.7 at α=11.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx61168-il100,000548.4 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx61168-il200,000971 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   fx61168-il200,000573 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx61168-il500,0009104.5 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   fx61168-il500,0005101.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx61168-il1,000,0009129.7 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx61168-il1,000,0005120.4 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
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