NACA 63(3)-018 (naca633018-il)
NACA 63(3)-018 - NACA 63(3)-018 airfoil
| Details | Dat file | Parser | |
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(naca633018-il) NACA 63(3)-018 NACA 63(3)-018 airfoil Max thickness 18% at 33.9% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 63(3)-018 1.00000 0.00000 0.99893 0.00006 0.99572 0.00024 0.99039 0.00053 0.98296 0.00096 0.97347 0.00157 0.96194 0.00244 0.94844 0.00368 0.93301 0.00539 0.91573 0.00761 0.89668 0.01035 0.87592 0.01359 0.85355 0.01730 0.82967 0.02149 0.80438 0.02613 0.77779 0.03117 0.75000 0.03655 0.72114 0.04216 0.69134 0.04793 0.66072 0.05373 0.62941 0.05947 0.59755 0.06502 0.56526 0.07029 0.53270 0.07515 0.50000 0.07949 0.46730 0.08321 0.43474 0.08620 0.40245 0.08839 0.37059 0.08969 0.33928 0.09007 0.30866 0.08955 0.27886 0.08820 0.25000 0.08611 0.22221 0.08336 0.19562 0.07999 0.17033 0.07607 0.14645 0.07168 0.12408 0.06688 0.10332 0.06171 0.08427 0.05620 0.06699 0.05041 0.05156 0.04442 0.03806 0.03833 0.02653 0.03214 0.01704 0.02561 0.00961 0.01861 0.00428 0.01164 0.00107 0.00539 0.00000 0.00000 0.00107 -0.00539 0.00428 -0.01164 0.00961 -0.01861 0.01704 -0.02561 0.02653 -0.03214 0.03806 -0.03833 0.05156 -0.04442 0.06699 -0.05041 0.08427 -0.05620 0.10332 -0.06171 0.12408 -0.06688 0.14645 -0.07168 0.17033 -0.07607 0.19562 -0.07999 0.22221 -0.08336 0.25000 -0.08611 0.27886 -0.08820 0.30866 -0.08955 0.33928 -0.09007 0.37059 -0.08969 0.40245 -0.08839 0.43474 -0.08620 0.46730 -0.08321 0.50000 -0.07949 0.53270 -0.07515 0.56526 -0.07029 0.59755 -0.06502 0.62941 -0.05947 0.66072 -0.05373 0.69134 -0.04793 0.72114 -0.04216 0.75000 -0.03655 0.77779 -0.03117 0.80438 -0.02613 0.82967 -0.02149 0.85355 -0.01730 0.87592 -0.01359 0.89668 -0.01035 0.91573 -0.00761 0.93301 -0.00539 0.94844 -0.00368 0.96194 -0.00244 0.97347 -0.00157 0.98296 -0.00096 0.99039 -0.00053 0.99572 -0.00024 0.99893 -0.00006 1.00000 0.00000 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for NACA 63(3)-018 (naca633018-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca633018-il | 50,000 | 9 | 23.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 50,000 | 5 | 20.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 100,000 | 9 | 40.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 100,000 | 5 | 36.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 200,000 | 9 | 53.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 200,000 | 5 | 50.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 500,000 | 9 | 73 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 500,000 | 5 | 61.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 1,000,000 | 9 | 83 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 1,000,000 | 5 | 65.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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