NACA 64-209 (naca64209-il)
NACA 64-209 - NACA 64-209 airfoil
| Details | Dat file | Parser | |
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(naca64209-il) NACA 64-209 NACA 64-209 airfoil Max thickness 9% 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 64-209 1.00000 0.00000 0.95011 0.00543 0.90021 0.01128 0.85030 0.01742 0.80035 0.02360 0.75036 0.02964 0.70035 0.03533 0.65030 0.04056 0.60022 0.04523 0.55012 0.04921 0.50000 0.05239 0.44986 0.05459 0.39971 0.05561 0.34956 0.05509 0.29941 0.05345 0.24927 0.05064 0.19915 0.04663 0.14905 0.04127 0.09899 0.03413 0.07398 0.02965 0.04901 0.02423 0.02411 0.01716 0.01172 0.01232 0.00680 0.00959 0.00438 0.00786 0.00000 0.00000 0.00562 -0.00686 0.00820 -0.00819 0.01328 -0.01108 0.02589 -0.01334 0.05099 -0.01791 0.07602 -0.02117 0.10101 -0.02379 0.15095 -0.02781 0.20085 -0.03071 0.25073 -0.03274 0.30059 -0.03401 0.35044 -0.03449 0.40029 -0.03419 0.45014 -0.03269 0.50000 -0.03033 0.54988 -0.02731 0.59978 -0.02381 0.64970 -0.01996 0.69965 -0.01589 0.74964 -0.01174 0.79965 -0.00768 0.84970 -0.00396 0.89979 -0.00094 0.94989 0.00089 1.00000 0.00000 |
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Polars for NACA 64-209 (naca64209-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca64209-il | 50,000 | 9 | 31.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64209-il | 50,000 | 5 | 32 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64209-il | 100,000 | 9 | 45.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64209-il | 100,000 | 5 | 43.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64209-il | 200,000 | 9 | 60.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64209-il | 200,000 | 5 | 53.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64209-il | 500,000 | 9 | 75.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64209-il | 500,000 | 5 | 60.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64209-il | 1,000,000 | 9 | 82.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64209-il | 1,000,000 | 5 | 70.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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