NACA 63012A AIRFOIL (n63012a-il)
NACA 63012A AIRFOIL - NACA 63-012A airfoil
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(n63012a-il) NACA 63012A AIRFOIL NACA 63-012A airfoil Max thickness 12% at 35% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA 63012A AIRFOIL 26.0000 26.0000 0.000000 0.000000 0.005000 0.009730 0.007500 0.011730 0.012500 0.014920 0.025000 0.020780 0.050000 0.028950 0.075000 0.035040 0.100000 0.039940 0.150000 0.047470 0.200000 0.052870 0.250000 0.056640 0.300000 0.059010 0.350000 0.059950 0.400000 0.059570 0.450000 0.057920 0.500000 0.055170 0.550000 0.051480 0.600000 0.047000 0.650000 0.041860 0.700000 0.036210 0.750000 0.030260 0.800000 0.024260 0.850000 0.018260 0.900000 0.012250 0.950000 0.006250 1.000000 0.000250 0.000000 0.000000 0.005000 -0.009730 0.007500 -0.011730 0.012500 -0.014920 0.025000 -0.020780 0.050000 -0.028950 0.075000 -0.035040 0.100000 -0.039940 0.150000 -0.047470 0.200000 -0.052870 0.250000 -0.056640 0.300000 -0.059010 0.350000 -0.059950 0.400000 -0.059570 0.450000 -0.057920 0.500000 -0.055170 0.550000 -0.051480 0.600000 -0.047000 0.650000 -0.041860 0.700000 -0.036210 0.750000 -0.030260 0.800000 -0.024260 0.850000 -0.018260 0.900000 -0.012250 0.950000 -0.006250 1.000000 -0.000250 |
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Polars for NACA 63012A AIRFOIL (n63012a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n63012a-il | 50,000 | 9 | 28.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63012a-il | 50,000 | 5 | 28.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63012a-il | 100,000 | 9 | 41.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63012a-il | 100,000 | 5 | 38.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63012a-il | 200,000 | 9 | 52 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63012a-il | 200,000 | 5 | 41.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63012a-il | 500,000 | 9 | 58.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63012a-il | 500,000 | 5 | 54.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63012a-il | 1,000,000 | 9 | 64.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63012a-il | 1,000,000 | 5 | 66.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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