NACA 4415 (naca4415-il)
NACA 4415 - NACA 4415 airfoil
| Details | Dat file | Parser | |
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(naca4415-il) NACA 4415 NACA 4415 airfoil Max thickness 15% at 30.9% chord. Max camber 4% at 40.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 4415 1.00000 0.00000 0.99893 0.00039 0.99572 0.00156 0.99039 0.00349 0.98296 0.00610 0.97347 0.00932 0.96194 0.01303 0.94844 0.01716 0.93301 0.02166 0.91573 0.02652 0.89668 0.03171 0.87592 0.03717 0.85355 0.04283 0.82967 0.04863 0.80438 0.05453 0.77779 0.06048 0.75000 0.06642 0.72114 0.07227 0.69134 0.07795 0.66072 0.08341 0.62941 0.08858 0.59755 0.09341 0.56526 0.09785 0.53270 0.10185 0.50000 0.10538 0.46730 0.10837 0.43474 0.11076 0.40245 0.11248 0.37059 0.11345 0.33928 0.11361 0.30866 0.11294 0.27886 0.11141 0.25000 0.10903 0.22221 0.10584 0.19562 0.10190 0.17033 0.09726 0.14645 0.09195 0.12408 0.08607 0.10332 0.07970 0.08427 0.07283 0.06699 0.06541 0.05156 0.05753 0.03806 0.04937 0.02653 0.04118 0.01704 0.03303 0.00961 0.02489 0.00428 0.01654 0.00107 0.00825 0.00000 0.00075 0.00107 -0.00566 0.00428 -0.01102 0.00961 -0.01590 0.01704 -0.02061 0.02653 -0.02502 0.03806 -0.02915 0.05156 -0.03281 0.06699 -0.03582 0.08427 -0.03817 0.10332 -0.03991 0.12408 -0.04106 0.14645 -0.04166 0.17033 -0.04177 0.19562 -0.04147 0.22221 -0.04078 0.25000 -0.03974 0.27886 -0.03845 0.30866 -0.03700 0.33928 -0.03547 0.37059 -0.03390 0.40245 -0.03229 0.43474 -0.03063 0.46730 -0.02891 0.50000 -0.02713 0.53270 -0.02529 0.56526 -0.02340 0.59755 -0.02149 0.62941 -0.01958 0.66072 -0.01772 0.69134 -0.01596 0.72114 -0.01430 0.75000 -0.01277 0.77779 -0.01136 0.80438 -0.01006 0.82967 -0.00886 0.85355 -0.00775 0.87592 -0.00674 0.89668 -0.00583 0.91573 -0.00502 0.93301 -0.00431 0.94844 -0.00364 0.96194 -0.00297 0.97347 -0.00227 0.98296 -0.00156 0.99039 -0.00092 0.99572 -0.00042 0.99893 -0.00011 1.00000 0.00000 |
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Polars for NACA 4415 (naca4415-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca4415-il | 50,000 | 9 | 7.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 50,000 | 5 | 27.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 100,000 | 9 | 48.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 100,000 | 5 | 50.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 200,000 | 9 | 71.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 200,000 | 5 | 68.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 500,000 | 9 | 97 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 500,000 | 5 | 90.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4415-il | 1,000,000 | 9 | 119.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4415-il | 1,000,000 | 5 | 109.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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