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FX 66-182 AIRFOIL (fx66182-il)

FX 66-182 AIRFOIL - Wortmann FX 66-182 airfoil


Airfoil fx66182-il
Details Dat file Parser  
(fx66182-il) FX 66-182 AIRFOIL
Wortmann FX 66-182 airfoil
Max thickness 18.2% 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 66-182 AIRFOIL
       44.       44.

 0.0000000 0.0000000
 0.0010700 0.0061600
 0.0042800 0.0121100
 0.0096100 0.0186600
 0.0170400 0.0268600
 0.0265300 0.0349200
 0.0380600 0.0433500
 0.0515600 0.0520100
 0.0669900 0.0607600
 0.0842700 0.0694900
 0.1033200 0.0780500
 0.1240800 0.0863500
 0.1464500 0.0942600
 0.1703300 0.1016900
 0.1956200 0.1085000
 0.2222100 0.1146000
 0.2500000 0.1198400
 0.2786600 0.1240900
 0.3086600 0.1270500
 0.3392800 0.1287400
 0.3705900 0.1289700
 0.4024500 0.1277400
 0.4347400 0.1249200
 0.4673000 0.1206500
 0.5000000 0.1151200
 0.5327000 0.1087300
 0.5652600 0.1018500
 0.5975500 0.0947600
 0.6294100 0.0875500
 0.6607200 0.0803200
 0.6913400 0.0731500
 0.7211400 0.0661400
 0.7500000 0.0593400
 0.7777900 0.0528200
 0.8043801 0.0466200
 0.8296700 0.0407800
 0.8535500 0.0353100
 0.8759201 0.0302600
 0.9157300 0.0213900
 0.9484400 0.0139600
 0.9734700 0.0075900
 0.9903900 0.0025800
 0.9989300 0.0001600
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0010700 -.0034000
 0.0042800 -.0074100
 0.0096100 -.0115800
 0.0170400 -.0151400
 0.0265300 -.0191100
 0.0380600 -.0229800
 0.0515600 -.0267400
 0.0669900 -.0303500
 0.0842700 -.0337900
 0.1033200 -.0370200
 0.1240800 -.0400400
 0.1464500 -.0428000
 0.1703300 -.0453200
 0.1956200 -.0475200
 0.2222100 -.0494400
 0.2500000 -.0509800
 0.2786600 -.0521800
 0.3086600 -.0529200
 0.3392800 -.0532100
 0.3705900 -.0528800
 0.4024500 -.0519800
 0.4347400 -.0503700
 0.4673000 -.0479600
 0.5000000 -.0446400
 0.5327000 -.0405000
 0.5652600 -.0357300
 0.5975500 -.0307200
 0.6294100 -.0257500
 0.6607200 -.0211200
 0.6913400 -.0169300
 0.7211400 -.0132600
 0.7500000 -.0101000
 0.7777900 -.0074400
 0.8043801 -.0052200
 0.8296700 -.0034200
 0.8535500 -.0020100
 0.8759201 -.0009700
 0.9157300 0.0001900
 0.9484400 0.0006300
 0.9734700 0.0006800
 0.9903900 0.0005100
 0.9989300 0.0001600
 1.0000000 0.0000000
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Polars for FX 66-182 AIRFOIL (fx66182-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx66182-il50,00094.7 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66182-il50,00058.2 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66182-il100,00095.9 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66182-il100,000530.2 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66182-il200,000961.8 at α=11°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66182-il200,000567.9 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66182-il500,0009107.3 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66182-il500,0005104.4 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx66182-il1,000,0009134.6 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx66182-il1,000,0005128.2 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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