NACA 63(2)A-015 (naca632a015-il)
NACA 63(2)A-015 - NACA 63(2)A-015 airfoil
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(naca632a015-il) NACA 63(2)A-015 NACA 63(2)A-015 airfoil Max thickness 15% at 37.1% chord. Max camber 1.7% at 14.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 63(2)A-015 1.00000 0.00000 0.99893 0.00020 0.99572 0.00079 0.99039 0.00176 0.98296 0.00311 0.97347 0.00482 0.96194 0.00686 0.94844 0.00919 0.93301 0.01179 0.91573 0.01466 0.89668 0.01785 0.87592 0.02137 0.85355 0.02518 0.82967 0.02921 0.80438 0.03343 0.77779 0.03786 0.75000 0.04253 0.72114 0.04744 0.69134 0.05245 0.66072 0.05740 0.62941 0.06223 0.59755 0.06691 0.56526 0.07134 0.53270 0.07535 0.50000 0.07891 0.46730 0.08204 0.43474 0.08461 0.40245 0.08652 0.37059 0.08776 0.33928 0.08827 0.30866 0.08808 0.27886 0.08732 0.25000 0.08603 0.22221 0.08421 0.19562 0.08191 0.17033 0.07914 0.14645 0.07580 0.12408 0.07177 0.10332 0.06698 0.08427 0.06150 0.06699 0.05559 0.05156 0.04920 0.03806 0.04250 0.02653 0.03580 0.01704 0.02870 0.00961 0.02175 0.00428 0.01450 0.00107 0.00730 0.00000 0.00000 0.00107 -0.00460 0.00428 -0.00860 0.00961 -0.01224 0.01704 -0.01591 0.02653 -0.01902 0.03806 -0.02196 0.05156 -0.02493 0.06699 -0.02800 0.08427 -0.03116 0.10332 -0.03449 0.12408 -0.03808 0.14645 -0.04191 0.17033 -0.04583 0.19562 -0.04956 0.22221 -0.05288 0.25000 -0.05577 0.27886 -0.05827 0.30866 -0.06020 0.33928 -0.06146 0.37059 -0.06211 0.40245 -0.06211 0.43474 -0.06142 0.46730 -0.06013 0.50000 -0.05828 0.53270 -0.05590 0.56526 -0.05318 0.59755 -0.05016 0.62941 -0.04678 0.66072 -0.04314 0.69134 -0.03939 0.72114 -0.03564 0.75000 -0.03195 0.77779 -0.02841 0.80438 -0.02503 0.82967 -0.02182 0.85355 -0.01878 0.87592 -0.01594 0.89668 -0.01330 0.91573 -0.01087 0.93301 -0.00867 0.94844 -0.00671 0.96194 -0.00498 0.97347 -0.00349 0.98296 -0.00225 0.99039 -0.00127 0.99572 -0.00057 0.99893 -0.00014 1.00000 0.00000 |
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Polars for NACA 63(2)A-015 (naca632a015-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca632a015-il | 50,000 | 9 | 23.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca632a015-il | 50,000 | 5 | 29.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca632a015-il | 100,000 | 9 | 45.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca632a015-il | 100,000 | 5 | 45.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca632a015-il | 200,000 | 9 | 59.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca632a015-il | 200,000 | 5 | 55.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca632a015-il | 500,000 | 9 | 76.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca632a015-il | 500,000 | 5 | 72.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca632a015-il | 1,000,000 | 9 | 93.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca632a015-il | 1,000,000 | 5 | 84.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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