NACA 66-018 (naca66-018-il)
NACA 66-018 - NACA 66-018 airfoil
| Details | Dat file | Parser | |
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(naca66-018-il) NACA 66-018 NACA 66-018 airfoil Max thickness 18% at 45% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 66-018
1.00000 0.00000
0.99435 0.00062
0.97752 0.00254
0.95000 0.00646
0.92689 0.01096
0.90000 0.01713
0.85000 0.02934
0.80000 0.04206
0.75000 0.05451
0.70000 0.06597
0.64999 0.07580
0.60000 0.08323
0.55000 0.08733
0.50000 0.08942
0.45000 0.08998
0.40000 0.08918
0.35000 0.08701
0.30000 0.08346
0.25000 0.07848
0.20000 0.07188
0.15000 0.06333
0.10000 0.05210
0.07500 0.04513
0.05000 0.03690
0.02500 0.02646
0.01250 0.01952
0.00750 0.01571
0.00500 0.01323
0.00127 0.00708
0.00000 0.00000
0.00127 -0.00708
0.00500 -0.01323
0.00750 -0.01571
0.01250 -0.01952
0.02500 -0.02646
0.05000 -0.03690
0.07500 -0.04513
0.10000 -0.05210
0.15000 -0.06333
0.20000 -0.07188
0.25000 -0.07848
0.30000 -0.08346
0.35000 -0.08701
0.40000 -0.08918
0.45000 -0.08998
0.50000 -0.08942
0.55000 -0.08733
0.60000 -0.08323
0.64999 -0.07580
0.70000 -0.06597
0.75000 -0.05451
0.80000 -0.04206
0.85000 -0.02934
0.87607 -0.02290
0.90000 -0.01713
0.95000 -0.00646
0.97752 -0.00254
0.99435 -0.00062
1.00000 0.00000
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Similar airfoils
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Polars for NACA 66-018 (naca66-018-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca66-018-il | 50,000 | 9 | 20.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 50,000 | 5 | 15.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 100,000 | 9 | 31.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 100,000 | 5 | 18.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 200,000 | 9 | 31 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 200,000 | 5 | 34.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 500,000 | 9 | 57.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 500,000 | 5 | 50.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66-018-il | 1,000,000 | 9 | 72 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66-018-il | 1,000,000 | 5 | 57.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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