NACA 66(4)-221 (naca664221-il)
NACA 66(4)-221 - NACA 66(4)-221 airfoil
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(naca664221-il) NACA 66(4)-221 NACA 66(4)-221 airfoil Max thickness 21% 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(4)-221 1.00000 0.00000 0.95034 0.01032 0.90067 0.02440 0.85092 0.03996 0.80106 0.05591 0.75109 0.07145 0.70103 0.08581 0.65087 0.09823 0.60063 0.10763 0.55032 0.11281 0.50000 0.11537 0.44967 0.11595 0.39933 0.11478 0.34900 0.11183 0.29869 0.10709 0.24840 0.10047 0.19815 0.09170 0.14797 0.08039 0.09788 0.06565 0.07291 0.05653 0.04800 0.04580 0.02323 0.03226 0.01095 0.02342 0.00610 0.01869 0.00372 0.01570 0.00000 0.00000 0.00628 -0.01470 0.00890 -0.01729 0.01405 -0.02128 0.02677 -0.02854 0.05200 -0.03948 0.07709 -0.04805 0.10212 -0.05531 0.15203 -0.06693 0.20185 -0.07578 0.25160 -0.08257 0.30131 -0.08765 0.35100 -0.09123 0.40067 -0.09339 0.45033 -0.09405 0.50000 -0.09331 0.54968 -0.09091 0.59937 -0.08621 0.64913 -0.07763 0.69897 -0.06637 0.74891 -0.05355 0.79894 -0.03999 0.84908 -0.02650 0.89933 -0.01406 0.94966 -0.00400 1.00000 0.00000 |
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Polars for NACA 66(4)-221 (naca664221-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca664221-il | 50,000 | 9 | 16.5 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca664221-il | 50,000 | 5 | 12.2 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca664221-il | 100,000 | 9 | 19.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca664221-il | 100,000 | 5 | 18.1 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca664221-il | 200,000 | 9 | 29.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca664221-il | 200,000 | 5 | 30.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca664221-il | 500,000 | 9 | 68.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca664221-il | 500,000 | 5 | 69.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca664221-il | 1,000,000 | 9 | 100.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca664221-il | 1,000,000 | 5 | 91.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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