NACA 65(2)-215 (naca652215-il)
NACA 65(2)-215 - NACA 65(2)-215 airfoil
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(naca652215-il) NACA 65(2)-215 NACA 65(2)-215 airfoil Max thickness 15% at 40% chord. Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 65(2)-215 1.00000 0.00000 0.95020 0.00744 0.90040 0.01660 0.85055 0.02649 0.80063 0.03653 0.75065 0.04638 0.70062 0.05572 0.65053 0.06433 0.60069 0.07189 0.55021 0.07815 0.50000 0.08271 0.44976 0.08522 0.39952 0.08569 0.34927 0.08426 0.29904 0.08123 0.24882 0.07658 0.19863 0.07018 0.14848 0.06175 0.09841 0.05069 0.07342 0.04380 0.04848 0.03557 0.02365 0.02506 0.01132 0.01805 0.00645 0.01422 0.00406 0.01170 0.00000 0.00000 0.00594 -0.01070 0.00855 -0.01282 0.01368 -0.01591 0.02635 -0.02134 0.05152 -0.02925 0.07658 -0.03532 0.10159 -0.04035 0.15152 -0.04829 0.20137 -0.05426 0.25118 -0.05868 0.30096 -0.06179 0.35073 -0.06366 0.40048 -0.06427 0.45024 -0.06332 0.50000 -0.06065 0.54979 -0.05625 0.59961 -0.05047 0.64947 -0.04373 0.69938 -0.03628 0.74935 -0.02848 0.79937 -0.02061 0.84945 -0.01303 0.89960 -0.00626 0.94980 -0.00112 1.00000 0.00000 |
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Polars for NACA 65(2)-215 (naca652215-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca652215-il | 50,000 | 9 | 22.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652215-il | 50,000 | 5 | 23.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652215-il | 100,000 | 9 | 46.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652215-il | 100,000 | 5 | 39.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652215-il | 200,000 | 9 | 57.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652215-il | 200,000 | 5 | 55.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652215-il | 500,000 | 9 | 82.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652215-il | 500,000 | 5 | 71.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca652215-il | 1,000,000 | 9 | 96.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca652215-il | 1,000,000 | 5 | 79 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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