NACA 64-012A AIRFOIL (n64012a-il)
NACA 64-012A AIRFOIL - NACA 64(1)-012A airfoil
| Details | Dat file | Parser | |
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(n64012a-il) NACA 64-012A AIRFOIL NACA 64(1)-012A 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 |
NACA 64-012A AIRFOIL
26. 26.
0.000000 0.000000
0.005000 0.009610
0.007500 0.011580
0.012500 0.014640
0.025000 0.020180
0.050000 0.027880
0.075000 0.033640
0.100000 0.038390
0.150000 0.045800
0.200000 0.051320
0.250000 0.055340
0.300000 0.058090
0.350000 0.059650
0.400000 0.059930
0.450000 0.058630
0.500000 0.056050
0.550000 0.052440
0.600000 0.048010
0.650000 0.042890
0.700000 0.037210
0.750000 0.031180
0.800000 0.025000
0.850000 0.018820
0.900000 0.012630
0.950000 0.006440
1.000000 0.000250
0.000000 0.000000
0.005000 -0.009610
0.007500 -0.011580
0.012500 -0.014640
0.025000 -0.020180
0.050000 -0.027880
0.075000 -0.033640
0.100000 -0.038390
0.150000 -0.045800
0.200000 -0.051320
0.250000 -0.055340
0.300000 -0.058090
0.350000 -0.059650
0.400000 -0.059930
0.450000 -0.058630
0.500000 -0.056050
0.550000 -0.052440
0.600000 -0.048010
0.650000 -0.042890
0.700000 -0.037210
0.750000 -0.031180
0.800000 -0.025000
0.850000 -0.018820
0.900000 -0.012630
0.950000 -0.006440
1.000000 -0.000250
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Polars for NACA 64-012A AIRFOIL (n64012a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n64012a-il | 50,000 | 9 | 27.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64012a-il | 50,000 | 5 | 27.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64012a-il | 100,000 | 9 | 40 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64012a-il | 100,000 | 5 | 35.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64012a-il | 200,000 | 9 | 47.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64012a-il | 200,000 | 5 | 39.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64012a-il | 500,000 | 9 | 56.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64012a-il | 500,000 | 5 | 52.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64012a-il | 1,000,000 | 9 | 61.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64012a-il | 1,000,000 | 5 | 64.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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