NACA 66(2)-215 (naca662215-il)
NACA 66(2)-215 - NACA 66(2)-215 airfoil
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(naca662215-il) NACA 66(2)-215 NACA 66(2)-215 airfoil Max thickness 15% 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(2)-215 1.00000 0.00000 0.95026 0.00881 0.90052 0.02005 0.85070 0.03202 0.80079 0.04393 0.75081 0.05526 0.70075 0.06547 0.65063 0.07402 0.60045 0.08030 0.55023 0.08378 0.50000 0.08553 0.44976 0.08590 0.39952 0.08501 0.34952 0.08280 0.29906 0.07927 0.24886 0.07437 0.19868 0.06790 0.14854 0.05957 0.09848 0.04872 0.07349 0.04202 0.04855 0.03413 0.02370 0.02417 0.01134 0.01778 0.00646 0.01409 0.00406 0.01168 0.00000 0.00000 0.00594 -0.01068 0.00854 -0.01269 0.01366 -0.01564 0.02630 -0.02045 0.05145 -0.02781 0.07651 -0.03354 0.10152 -0.03838 0.15146 -0.04611 0.20132 -0.05198 0.25114 -0.05647 0.30094 -0.05983 0.35071 -0.06220 0.40048 -0.06359 0.45024 -0.06400 0.50000 -0.06347 0.54977 -0.06188 0.59955 -0.05888 0.64937 -0.05342 0.69925 -0.04603 0.74919 -0.03736 0.79921 -0.02801 0.84930 -0.01856 0.89948 -0.00971 0.94974 -0.00249 1.00000 0.00000 |
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Polars for NACA 66(2)-215 (naca662215-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca662215-il | 50,000 | 9 | 21.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca662215-il | 50,000 | 5 | 21 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca662215-il | 100,000 | 9 | 37.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca662215-il | 100,000 | 5 | 28.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca662215-il | 200,000 | 9 | 44.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca662215-il | 200,000 | 5 | 46.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca662215-il | 500,000 | 9 | 72.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca662215-il | 500,000 | 5 | 66.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca662215-il | 1,000,000 | 9 | 91.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca662215-il | 1,000,000 | 5 | 76.2 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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