NACA 66-021 AIRFOIL (n66021-il)
NACA 66-021 AIRFOIL - NACA 66(4)-021 airfoil
| Details | Dat file | Parser | |
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(n66021-il) NACA 66-021 AIRFOIL NACA 66(4)-021 airfoil Max thickness 21% at 45% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA 66-021 AIRFOIL
26. 26.
0.000000 0.000000
0.005000 0.015250
0.007500 0.018040
0.012500 0.022400
0.025000 0.030450
0.050000 0.042690
0.075000 0.052330
0.100000 0.060520
0.150000 0.073690
0.200000 0.083760
0.250000 0.091530
0.300000 0.097380
0.350000 0.101540
0.400000 0.104070
0.450000 0.105000
0.500000 0.104340
0.550000 0.101860
0.600000 0.096920
0.650000 0.087930
0.700000 0.076100
0.750000 0.062510
0.800000 0.047960
0.850000 0.033240
0.900000 0.019240
0.950000 0.007170
1.000000 0.000000
0.000000 0.000000
0.005000 -0.015250
0.007500 -0.018040
0.012500 -0.022400
0.025000 -0.030450
0.050000 -0.042690
0.075000 -0.052330
0.100000 -0.060520
0.150000 -0.073690
0.200000 -0.083760
0.250000 -0.091530
0.300000 -0.097380
0.350000 -0.101540
0.400000 -0.104070
0.450000 -0.105000
0.500000 -0.104340
0.550000 -0.101860
0.600000 -0.096920
0.650000 -0.087930
0.700000 -0.076100
0.750000 -0.062510
0.800000 -0.047960
0.850000 -0.033240
0.900000 -0.019240
0.950000 -0.007170
1.000000 0.000000
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Polars for NACA 66-021 AIRFOIL (n66021-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n66021-il | 50,000 | 9 | 18.6 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n66021-il | 50,000 | 5 | 11 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n66021-il | 100,000 | 9 | 23.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n66021-il | 100,000 | 5 | 15.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n66021-il | 200,000 | 9 | 25.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n66021-il | 200,000 | 5 | 26.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n66021-il | 500,000 | 9 | 57.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n66021-il | 500,000 | 5 | 54.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n66021-il | 1,000,000 | 9 | 78.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n66021-il | 1,000,000 | 5 | 64.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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