NACA 64-108 AIRFOIL (n64108-il)
NACA 64-108 AIRFOIL - NACA 64-108 airfoil
| Details | Dat file | Parser | |
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(n64108-il) NACA 64-108 AIRFOIL NACA 64-108 airfoil Max thickness 8% at 40% chord. Max camber 0.6% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA 64-108 AIRFOIL
26. 26.
0.000000 0.000000
0.004720 0.006820
0.007190 0.008280
0.012150 0.010580
0.024600 0.014570
0.049560 0.020320
0.074550 0.024710
0.099550 0.028320
0.149580 0.034050
0.199620 0.038350
0.249680 0.041520
0.299740 0.043700
0.349800 0.044940
0.399870 0.045280
0.449940 0.044310
0.500000 0.042360
0.550050 0.039590
0.600100 0.036170
0.650130 0.032190
0.700150 0.027770
0.750160 0.023020
0.800150 0.018020
0.850130 0.012970
0.900100 0.008080
0.950050 0.003640
1.000000 0.000000
0.000000 0.000000
0.005280 -0.006320
0.007810 -0.007580
0.012850 -0.009500
0.025400 -0.012710
0.050440 -0.017160
0.075450 -0.020470
0.100450 -0.023160
0.150420 -0.027330
0.200380 -0.030390
0.250320 -0.032560
0.300260 -0.033980
0.350200 -0.034640
0.400130 -0.034560
0.450060 -0.033350
0.500000 -0.031320
0.549950 -0.028630
0.599900 -0.025450
0.649870 -0.021890
0.699850 -0.018050
0.749840 -0.014060
0.799850 -0.010060
0.849870 -0.006250
0.899900 -0.002920
0.949950 -0.000480
1.000000 0.000000
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Polars for NACA 64-108 AIRFOIL (n64108-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n64108-il | 50,000 | 9 | 26.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64108-il | 50,000 | 5 | 27.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64108-il | 100,000 | 9 | 39 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64108-il | 100,000 | 5 | 36.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64108-il | 200,000 | 9 | 49.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64108-il | 200,000 | 5 | 43.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64108-il | 500,000 | 9 | 60 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64108-il | 500,000 | 5 | 50.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64108-il | 1,000,000 | 9 | 63.1 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64108-il | 1,000,000 | 5 | 65.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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