NACA 66-209 (naca66209-il)
NACA 66-209 - NACA 66-209 airfoil
| Details | Dat file | Parser | |
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(naca66209-il) NACA 66-209 NACA 66-209 airfoil Max thickness 9% at 45% chord. Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 66-209 1.00000 0.00000 0.95018 0.00690 0.90034 0.01477 0.85044 0.02283 0.80050 0.03058 0.75050 0.03772 0.70046 0.04400 0.65038 0.04912 0.60027 0.05275 0.55014 0.05476 0.50000 0.05578 0.44986 0.05594 0.39971 0.05528 0.34957 0.05378 0.29944 0.05145 0.24931 0.04821 0.19921 0.04396 0.14912 0.03850 0.09908 0.03141 0.07409 0.02705 0.04912 0.02194 0.02420 0.01552 0.01179 0.01135 0.00686 0.00892 0.00442 0.00735 0.00000 0.00000 0.00558 -0.00635 0.00814 -0.00752 0.01321 -0.00921 0.02580 -0.01180 0.05088 -0.01562 0.07591 -0.01857 0.10092 -0.02107 0.15088 -0.02504 0.20079 -0.02804 0.25069 -0.03031 0.30056 -0.03201 0.35043 -0.03318 0.40029 -0.03386 0.45014 -0.03404 0.50000 -0.03372 0.54986 -0.03286 0.59973 -0.03133 0.64962 -0.02852 0.69954 -0.02456 0.74950 -0.01982 0.79980 -0.01466 0.84956 -0.00937 0.89965 -0.00443 0.94982 -0.00058 1.00000 0.00000 |
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Polars for NACA 66-209 (naca66209-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca66209-il | 50,000 | 9 | 22.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66209-il | 50,000 | 5 | 25.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66209-il | 100,000 | 9 | 32.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66209-il | 100,000 | 5 | 40.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66209-il | 200,000 | 9 | 53.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66209-il | 200,000 | 5 | 47.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66209-il | 500,000 | 9 | 67.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66209-il | 500,000 | 5 | 60.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66209-il | 1,000,000 | 9 | 80.4 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66209-il | 1,000,000 | 5 | 64.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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