NACA 64-215 AIRFOIL (n64215-il)
NACA 64-215 AIRFOIL - NACA 64(2)-215 airfoil
| Details | Dat file | Parser | |
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(n64215-il) NACA 64-215 AIRFOIL NACA 64(2)-215 airfoil Max thickness 15% at 34.9% chord. Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA 64-215 AIRFOIL
26. 26.
0.000000 0.000000
0.003990 0.012540
0.006370 0.015220
0.011220 0.019450
0.023530 0.027100
0.048360 0.038160
0.073310 0.046610
0.098310 0.053560
0.148400 0.064560
0.198570 0.072740
0.248780 0.078790
0.299010 0.082900
0.349260 0.085120
0.399520 0.085440
0.449770 0.083190
0.500000 0.079130
0.550200 0.073610
0.600360 0.066910
0.650480 0.059250
0.700550 0.050850
0.750580 0.041910
0.800550 0.032670
0.850460 0.023490
0.900330 0.014660
0.950160 0.006620
1.000000 0.000000
0.000000 0.000000
0.006010 -0.011540
0.008630 -0.013820
0.013780 -0.017310
0.026470 -0.023380
0.051640 -0.031840
0.076690 -0.038130
0.101690 -0.043220
0.151600 -0.051100
0.201430 -0.056820
0.251220 -0.060890
0.300990 -0.063460
0.350740 -0.064520
0.400480 -0.064020
0.450230 -0.061290
0.500000 -0.057070
0.549800 -0.051710
0.599640 -0.045490
0.649520 -0.038650
0.699450 -0.031410
0.749420 -0.024010
0.799450 -0.016750
0.849540 -0.010030
0.899670 -0.004320
0.949840 -0.000300
1.000000 0.000000
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Polars for NACA 64-215 AIRFOIL (n64215-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n64215-il | 50,000 | 9 | 28.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64215-il | 50,000 | 5 | 26.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64215-il | 100,000 | 9 | 47.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64215-il | 100,000 | 5 | 44.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64215-il | 200,000 | 9 | 63.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64215-il | 200,000 | 5 | 58.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64215-il | 500,000 | 9 | 85.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64215-il | 500,000 | 5 | 73.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64215-il | 1,000,000 | 9 | 99.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64215-il | 1,000,000 | 5 | 79.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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