NACA 63A010 AIRFOIL (n63010a-il)
NACA 63A010 AIRFOIL - NACA 63-010A airfoil
| Details | Dat file | Parser | |
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(n63010a-il) NACA 63A010 AIRFOIL NACA 63-010A airfoil Max thickness 10% 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 63A010 AIRFOIL
26. 26.
0.000000 0.000000
0.005000 0.008160
0.007500 0.009830
0.012500 0.012500
0.025000 0.017370
0.050000 0.024120
0.075000 0.029170
0.100000 0.033240
0.150000 0.039500
0.200000 0.044000
0.250000 0.047140
0.300000 0.049130
0.350000 0.049950
0.400000 0.049680
0.450000 0.048370
0.500000 0.046130
0.550000 0.043110
0.600000 0.039430
0.650000 0.035170
0.700000 0.030440
0.750000 0.025450
0.800000 0.020400
0.850000 0.015350
0.900000 0.010300
0.950000 0.005250
1.000000 0.000210
0.000000 0.000000
0.005000 -0.008160
0.007500 -0.009830
0.012500 -0.012500
0.025000 -0.017370
0.050000 -0.024120
0.075000 -0.029170
0.100000 -0.033240
0.150000 -0.039500
0.200000 -0.044000
0.250000 -0.047140
0.300000 -0.049130
0.350000 -0.049950
0.400000 -0.049680
0.450000 -0.048370
0.500000 -0.046130
0.550000 -0.043110
0.600000 -0.039430
0.650000 -0.035170
0.700000 -0.030440
0.750000 -0.025450
0.800000 -0.020400
0.850000 -0.015350
0.900000 -0.010300
0.950000 -0.005250
1.000000 -0.000210
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Polars for NACA 63A010 AIRFOIL (n63010a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n63010a-il | 50,000 | 9 | 27.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63010a-il | 50,000 | 5 | 26.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63010a-il | 100,000 | 9 | 37.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63010a-il | 100,000 | 5 | 34.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63010a-il | 200,000 | 9 | 47.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63010a-il | 200,000 | 5 | 39.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63010a-il | 500,000 | 9 | 52.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63010a-il | 500,000 | 5 | 51 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63010a-il | 1,000,000 | 9 | 59.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63010a-il | 1,000,000 | 5 | 64.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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