NACA 63(4)-221 (naca634221-il)
NACA 63(4)-221 - NACA 63(4)-221 airfoil
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(naca634221-il) NACA 63(4)-221 NACA 63(4)-221 airfoil Max thickness 21% at 34.9% chord. Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 63(4)-221 1.00000 0.00000 0.95018 0.00708 0.90039 0.01629 0.85056 0.02693 0.80067 0.03849 0.75073 0.05054 0.70071 0.06262 0.65063 0.07426 0.60048 0.08512 0.55027 0.09485 0.50000 0.10309 0.44969 0.10949 0.39934 0.11369 0.34897 0.11529 0.29860 0.11383 0.24824 0.10946 0.19792 0.10204 0.14767 0.09111 0.09753 0.07593 0.07253 0.06601 0.04763 0.05375 0.02292 0.03757 0.01075 0.02628 0.00600 0.02001 0.00367 0.01627 0.00000 0.00000 0.00633 -0.01527 0.00900 -0.01861 0.01425 -0.02414 0.02708 -0.03385 0.05237 -0.04743 0.07747 -0.05753 0.10247 -0.06559 0.15233 -0.07765 0.20208 -0.08612 0.25176 -0.09156 0.30140 -0.09439 0.35103 -0.09469 0.40066 -0.09227 0.45031 -0.08759 0.50000 -0.08103 0.54973 -0.07295 0.59952 -0.06370 0.64937 -0.05366 0.69929 -0.04318 0.74927 -0.03264 0.79933 -0.02257 0.84944 -0.01347 0.89961 -0.00595 0.94982 -0.00076 1.00000 0.00000 |
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Polars for NACA 63(4)-221 (naca634221-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca634221-il | 50,000 | 9 | 4.8 at α=-3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca634221-il | 50,000 | 5 | 10.8 at α=14.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca634221-il | 100,000 | 9 | 28.9 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca634221-il | 100,000 | 5 | 34 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca634221-il | 200,000 | 9 | 58.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca634221-il | 200,000 | 5 | 58.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca634221-il | 500,000 | 9 | 88 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca634221-il | 500,000 | 5 | 82 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca634221-il | 1,000,000 | 9 | 108 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca634221-il | 1,000,000 | 5 | 95.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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