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FX 66-S-171 AIRFOIL (fx66s171-il)

FX 66-S-171 AIRFOIL - Wortmann FX 66-S-171 airfoil


Airfoil fx66s171-il
Details Dat file Parser  
(fx66s171-il) FX 66-S-171 AIRFOIL
Wortmann FX 66-S-171 airfoil
Max thickness 17.1% at 33.9% chord.
Max camber 3.9% at 43.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
FX 66-S-171 AIRFOIL
       44.       44.

 0.0000000 0.0000000
 0.0010700 0.0056800
 0.0042800 0.0116100
 0.0096100 0.0184000
 0.0170400 0.0259600
 0.0265300 0.0340500
 0.0380600 0.0424600
 0.0515600 0.0511100
 0.0669900 0.0597900
 0.0842700 0.0684300
 0.1033200 0.0768400
 0.1240800 0.0849700
 0.1464500 0.0926400
 0.1703300 0.0998000
 0.1956200 0.1062300
 0.2222100 0.1118700
 0.2500000 0.1164400
 0.2786600 0.1199100
 0.3086600 0.1221300
 0.3392800 0.1233100
 0.3705900 0.1230500
 0.4024500 0.1214700
 0.4347400 0.1182800
 0.4673000 0.1139200
 0.5000000 0.1085900
 0.5327000 0.1027500
 0.5652600 0.0962800
 0.5975500 0.0895600
 0.6294100 0.0826600
 0.6607200 0.0758200
 0.6913400 0.0690100
 0.7211400 0.0623600
 0.7500000 0.0559400
 0.7777900 0.0497700
 0.8043801 0.0438600
 0.8296700 0.0383400
 0.8535500 0.0331000
 0.8759201 0.0282800
 0.9157300 0.0197300
 0.9484400 0.0126600
 0.9734700 0.0069700
 0.9903900 0.0026700
 0.9989300 0.0003200
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0010700 -.0034800
 0.0042800 -.0074400
 0.0096100 -.0115000
 0.0170400 -.0154700
 0.0265300 -.0194200
 0.0380600 -.0232300
 0.0515600 -.0269500
 0.0669900 -.0304500
 0.0842700 -.0338100
 0.1033200 -.0368800
 0.1240800 -.0397600
 0.1464500 -.0422800
 0.1703300 -.0445500
 0.1956200 -.0463800
 0.2222100 -.0479100
 0.2500000 -.0489000
 0.2786600 -.0492900
 0.3086600 -.0487500
 0.3392800 -.0477800
 0.3705900 -.0460900
 0.4024500 -.0438200
 0.4347400 -.0405800
 0.4673000 -.0368300
 0.5000000 -.0327000
 0.5327000 -.0286900
 0.5652600 -.0246700
 0.5975500 -.0209200
 0.6294100 -.0172500
 0.6607200 -.0139600
 0.6913400 -.0109400
 0.7211400 -.0083100
 0.7500000 -.0059800
 0.7777900 -.0039900
 0.8043801 -.0023000
 0.8296700 -.0010200
 0.8535500 0.0000200
 0.8759201 0.0006800
 0.9157300 0.0013800
 0.9484400 0.0013700
 0.9734700 0.0010400
 0.9903900 0.0005600
 0.9989300 0.0001100
 1.0000000 0.0000000
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Polars for FX 66-S-171 AIRFOIL (fx66s171-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx66s171-il50,00095 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66s171-il50,000512.7 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66s171-il100,000913.3 at α=1°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66s171-il100,000539.2 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66s171-il200,000970.3 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66s171-il200,000572.4 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66s171-il500,0009113.9 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66s171-il500,0005113.4 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66s171-il1,000,0009147.6 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66s171-il1,000,0005133.8 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
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