NACA 63-215 AIRFOIL (n63215-il)
NACA 63-215 AIRFOIL - NACA 63(2)-215 airfoil
| Details | Dat file | Parser | |
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(n63215-il) NACA 63-215 AIRFOIL NACA 63(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 63-215 AIRFOIL
26. 26.
0.000000 0.000000
0.003990 0.012500
0.006370 0.015280
0.011200 0.019800
0.023480 0.027920
0.048290 0.039600
0.073230 0.048470
0.098230 0.055690
0.148340 0.066820
0.198520 0.074870
0.248750 0.080490
0.299000 0.083920
0.349260 0.085300
0.399520 0.084570
0.449770 0.081940
0.500000 0.077680
0.550190 0.072030
0.600350 0.065240
0.650470 0.057510
0.700530 0.049060
0.750550 0.040140
0.800510 0.031050
0.850430 0.022130
0.900300 0.013680
0.950140 0.006160
1.000000 0.000000
0.000000 0.000000
0.006010 -0.011500
0.008630 -0.013880
0.013800 -0.017660
0.026520 -0.024200
0.051710 -0.033280
0.076770 -0.039990
0.101770 -0.045350
0.151660 -0.053360
0.201480 -0.058950
0.251250 -0.062590
0.301000 -0.064480
0.350740 -0.064700
0.400480 -0.063150
0.450230 -0.060040
0.500000 -0.055620
0.549810 -0.050130
0.599650 -0.043820
0.649530 -0.036910
0.699470 -0.029620
0.749450 -0.022240
0.799490 -0.015130
0.849570 -0.008670
0.899700 -0.003340
0.949860 0.000160
1.000000 0.000000
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Polars for NACA 63-215 AIRFOIL (n63215-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n63215-il | 50,000 | 9 | 29.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215-il | 50,000 | 5 | 28.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215-il | 100,000 | 9 | 48.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215-il | 100,000 | 5 | 46.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215-il | 200,000 | 9 | 65.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215-il | 200,000 | 5 | 59.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215-il | 500,000 | 9 | 85.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215-il | 500,000 | 5 | 73.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215-il | 1,000,000 | 9 | 98.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215-il | 1,000,000 | 5 | 80.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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