NACA 66-210 (naca66210-il)
NACA 66-210 - NACA 66-210 airfoil
| Details | Dat file | Parser | |
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(naca66210-il) NACA 66-210 NACA 66-210 airfoil Max thickness 10% 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 66-210 1.00000 0.00000 0.95019 0.00724 0.90037 0.01570 0.85049 0.02445 0.80055 0.03289 0.75056 0.04071 0.70051 0.04759 0.65042 0.05332 0.60030 0.05736 0.55016 0.05960 0.50000 0.06074 0.44984 0.06095 0.39968 0.06024 0.34952 0.05862 0.29937 0.05608 0.24924 0.05257 0.19912 0.04796 0.14903 0.04202 0.09898 0.03432 0.07399 0.02958 0.04902 0.02401 0.02412 0.01699 0.01171 0.01245 0.00679 0.00980 0.00436 0.00806 0.00000 0.00000 0.00564 -0.00706 0.00821 -0.00840 0.01329 -0.01031 0.02588 -0.01327 0.05098 -0.01769 0.07601 -0.02110 0.10102 -0.02389 0.15097 -0.02856 0.20088 -0.03204 0.25076 -0.03467 0.30063 -0.03664 0.35048 -0.03802 0.40032 -0.03882 0.45016 -0.03905 0.50000 -0.03868 0.54984 -0.03770 0.59970 -0.03594 0.64958 -0.03272 0.69949 -0.02815 0.74944 -0.02281 0.79945 -0.01697 0.84951 -0.01099 0.89963 -0.00536 0.94981 -0.00092 1.00000 0.00000 |
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Polars for NACA 66-210 (naca66210-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca66210-il | 50,000 | 9 | 22.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 50,000 | 5 | 27.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 100,000 | 9 | 32.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 100,000 | 5 | 36.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 200,000 | 9 | 51.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 200,000 | 5 | 46.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 500,000 | 5 | 61.9 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 500,000 | 0 | 67.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 1,000,000 | 9 | 82.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 1,000,000 | 5 | 67.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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