NASA/LANGLEY 64-012 AIRFOIL (n64012-il)
NASA/LANGLEY 64-012 AIRFOIL - NACA 64(1)-012 airfoil
| Details | Dat file | Parser | |
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(n64012-il) NASA/LANGLEY 64-012 AIRFOIL NACA 64(1)-012 airfoil Max thickness 12% at 40% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NASA/LANGLEY 64-012 AIRFOIL
26. 26.
0.000000 0.000000
0.005000 0.009780
0.007500 0.011790
0.012500 0.014900
0.025000 0.020350
0.050000 0.028100
0.075000 0.033940
0.100000 0.038710
0.150000 0.046200
0.200000 0.051730
0.250000 0.055760
0.300000 0.058440
0.350000 0.059780
0.400000 0.059810
0.450000 0.057980
0.500000 0.054800
0.550000 0.050560
0.600000 0.045480
0.650000 0.039740
0.700000 0.033500
0.750000 0.026950
0.800000 0.020290
0.850000 0.013820
0.900000 0.007860
0.950000 0.002880
1.000000 0.000000
0.000000 0.000000
0.005000 -0.009780
0.007500 -0.011790
0.012500 -0.014900
0.025000 -0.020350
0.050000 -0.028100
0.075000 -0.033940
0.100000 -0.038710
0.150000 -0.046200
0.200000 -0.051730
0.250000 -0.055760
0.300000 -0.058440
0.350000 -0.059780
0.400000 -0.059810
0.450000 -0.057980
0.500000 -0.054800
0.550000 -0.050560
0.600000 -0.045480
0.650000 -0.039740
0.700000 -0.033500
0.750000 -0.026950
0.800000 -0.020290
0.850000 -0.013820
0.900000 -0.007860
0.950000 -0.002880
1.000000 0.000000
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Polars for NASA/LANGLEY 64-012 AIRFOIL (n64012-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n64012-il | 50,000 | 9 | 26.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64012-il | 50,000 | 5 | 27.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64012-il | 100,000 | 9 | 39.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64012-il | 100,000 | 5 | 32.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64012-il | 200,000 | 9 | 43.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64012-il | 200,000 | 5 | 39.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64012-il | 500,000 | 9 | 56.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64012-il | 500,000 | 5 | 51.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64012-il | 1,000,000 | 9 | 60.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64012-il | 1,000,000 | 5 | 65.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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