AH 83-159 (ah83159-il)
AH 83-159 - Althaus AH 83-159 airfoil
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(ah83159-il) AH 83-159 Althaus AH 83-159 airfoil Max thickness 15.9% at 40.2% chord. Max camber 3.8% at 40.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH 83-159 1.00000 0.00000 0.99893 0.00029 0.99572 0.00119 0.99039 0.00256 0.98296 0.00428 0.97347 0.00622 0.96194 0.00843 0.94844 0.01101 0.93301 0.01408 0.91573 0.01798 0.89668 0.02267 0.87592 0.02811 0.85355 0.03428 0.82967 0.04108 0.80438 0.04841 0.77779 0.05616 0.75000 0.06420 0.72114 0.07236 0.69134 0.08044 0.66072 0.08822 0.62941 0.09548 0.59755 0.10196 0.56526 0.10747 0.53270 0.11185 0.50000 0.11505 0.46730 0.11713 0.43474 0.11815 0.40245 0.11816 0.37059 0.11724 0.33928 0.11547 0.30866 0.11290 0.27886 0.10959 0.25000 0.10559 0.22221 0.10091 0.19562 0.09560 0.17033 0.08970 0.14645 0.08330 0.12408 0.07647 0.10332 0.06930 0.08427 0.06186 0.06699 0.05426 0.05156 0.04654 0.03806 0.03884 0.02653 0.03123 0.01704 0.02387 0.00961 0.01689 0.00428 0.01036 0.00107 0.00459 0.00000 0.00000 0.00107 -0.00356 0.00428 -0.00670 0.00961 -0.00973 0.01704 -0.01268 0.02653 -0.01551 0.03806 -0.01824 0.05156 -0.02088 0.06699 -0.02336 0.08427 -0.02573 0.10332 -0.02795 0.12408 -0.03002 0.14645 -0.03195 0.17033 -0.03372 0.19562 -0.03531 0.22221 -0.03674 0.25000 -0.03797 0.27886 -0.03904 0.30866 -0.03990 0.33928 -0.04057 0.37059 -0.04102 0.40245 -0.04126 0.43474 -0.04127 0.46730 -0.04105 0.50000 -0.04059 0.53270 -0.03986 0.56526 -0.03885 0.59755 -0.03751 0.62941 -0.03582 0.66072 -0.03370 0.69134 -0.03107 0.72114 -0.02792 0.75000 -0.02420 0.77779 -0.01983 0.80438 -0.01484 0.82967 -0.00976 0.85355 -0.00532 0.87592 -0.00197 0.89668 0.00035 0.91573 0.00175 0.93301 0.00239 0.94844 0.00246 0.96194 0.00215 0.97347 0.00162 0.98296 0.00101 0.99039 0.00048 0.99572 0.00019 0.99893 0.00005 1.00000 0.00000 |
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Polars for AH 83-159 (ah83159-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah83159-il | 50,000 | 9 | 17.1 at α=13.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83159-il | 50,000 | 5 | 15.5 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83159-il | 100,000 | 9 | 31.4 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83159-il | 100,000 | 5 | 29 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83159-il | 200,000 | 9 | 64.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83159-il | 200,000 | 5 | 63.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83159-il | 500,000 | 9 | 106.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83159-il | 500,000 | 5 | 105.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83159-il | 1,000,000 | 9 | 136.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83159-il | 1,000,000 | 5 | 133.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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