NACA 63-412 AIRFOIL (n63412-il)
NACA 63-412 AIRFOIL - NACA 63(1)-412 airfoil
| Details | Dat file | Parser | |
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(n63412-il) NACA 63-412 AIRFOIL NACA 63(1)-412 airfoil Max thickness 12% at 34.9% chord. Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA 63-412 AIRFOIL
26. 26.
0.000000 0.000000
0.003360 0.010710
0.005670 0.013200
0.010410 0.017190
0.022570 0.024600
0.047270 0.035440
0.072180 0.043790
0.097180 0.050630
0.147350 0.061380
0.197650 0.069290
0.248000 0.074990
0.298400 0.078720
0.348820 0.080590
0.399240 0.080620
0.449640 0.078940
0.500000 0.075670
0.550310 0.071250
0.600570 0.065620
0.650760 0.058990
0.700870 0.051530
0.750890 0.043440
0.800840 0.034920
0.850700 0.026180
0.900490 0.017390
0.950230 0.008810
1.000000 0.000000
0.000000 0.000000
0.006640 -0.008710
0.009330 -0.010400
0.014590 -0.012910
0.027430 -0.017160
0.052730 -0.022800
0.077820 -0.026850
0.102820 -0.029950
0.152650 -0.034460
0.202350 -0.037450
0.252000 -0.039190
0.301600 -0.039840
0.351118 -0.039390
0.400760 -0.037780
0.450350 -0.035140
0.500000 -0.031640
0.549690 -0.027450
0.599430 -0.022780
0.649240 -0.017990
0.699130 -0.012650
0.749110 -0.007640
0.799160 -0.003080
0.849300 0.000740
0.899510 0.003290
0.949770 0.003300
1.000000 0.000000
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Polars for NACA 63-412 AIRFOIL (n63412-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n63412-il | 50,000 | 9 | 36.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63412-il | 50,000 | 5 | 36 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63412-il | 100,000 | 9 | 56.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63412-il | 100,000 | 5 | 54.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63412-il | 200,000 | 9 | 77.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63412-il | 200,000 | 5 | 70.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63412-il | 500,000 | 9 | 99.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63412-il | 500,000 | 5 | 88.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63412-il | 1,000,000 | 9 | 115.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63412-il | 1,000,000 | 5 | 98.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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