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)
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(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)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx6617ai-il | 50,000 | 9 | 4.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617ai-il | 50,000 | 5 | 8.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617ai-il | 100,000 | 9 | 6.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617ai-il | 100,000 | 5 | 29.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617ai-il | 200,000 | 9 | 62.9 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617ai-il | 200,000 | 5 | 68.8 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617ai-il | 500,000 | 9 | 109.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617ai-il | 500,000 | 5 | 105.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617ai-il | 1,000,000 | 9 | 137.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617ai-il | 1,000,000 | 5 | 130.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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