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WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il)

WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) - Wortmann FX 66-17AII-182 airfoil (as tested at NASA)


Airfoil fx6617ai-il
Details Dat file Parser  
(fx6617ai-il) WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA)
Wortmann FX 66-17AII-182 airfoil (as tested at NASA)
Max thickness 18.8% at 35.3% chord.
Max camber 3.7% at 40.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA)
       35.       32.

  0.000000  0.000000
  0.000830  0.003470
  0.001660  0.005630
  0.002770  0.007860
  0.003880  0.009660
  0.004990  0.011340
  0.005850  0.012590
  0.013530  0.021200
  0.017810  0.025210
  0.024750  0.031060
  0.034670  0.038410
  0.050130  0.048610
  0.060900  0.055100
  0.075740  0.063280
  0.101990  0.076080
  0.151060  0.095480
  0.200350  0.110420
  0.253200  0.121650
  0.303110  0.128190
  0.352830  0.130660
  0.401850  0.129020
  0.452440  0.123350
  0.500430  0.115060
  0.551780  0.104270
  0.600950  0.093280
  0.650560  0.081970
  0.701370  0.070280
  0.744420  0.060260
  0.800120  0.047370
  0.849970  0.035850
  0.900090  0.024330
  0.949940  0.012570
  0.976130  0.006290
  0.990330  0.002850
  0.999640  0.000210

  0.000000  0.000000
  0.000830 -0.005160
  0.001660 -0.006910
  0.002770 -0.008560
  0.003880 -0.009920
  0.005270 -0.011360
  0.006410 -0.012310
  0.013520 -0.016760
  0.035880 -0.025730
  0.051130 -0.030400
  0.076430 -0.036510
  0.101690 -0.041310
  0.150670 -0.048330
  0.200550 -0.053210
  0.250320 -0.056170
  0.301660 -0.057790
  0.350470 -0.057820
  0.400690 -0.055970
  0.450070 -0.052530
  0.499980 -0.047720
  0.550560 -0.041340
  0.599700 -0.033960
  0.649520 -0.026300
  0.700120 -0.018920
  0.749950 -0.012340
  0.798080 -0.007320
  0.848980 -0.003640
  0.899070 -0.001330
  0.947580 -0.000800
  0.970260 -0.000950
  0.978320 -0.001040
  1.000000 -0.000590
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Polars for WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx6617ai-il50,00094.7 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx6617ai-il50,00058.3 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx6617ai-il100,00096.1 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx6617ai-il100,000529.3 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx6617ai-il200,000962.9 at α=11°Mach=0 Ncrit=9Xfoil predictionDetails
   fx6617ai-il200,000568.8 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx6617ai-il500,0009109.2 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx6617ai-il500,0005105.5 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx6617ai-il1,000,0009137.9 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx6617ai-il1,000,0005130.7 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
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