AH 80-129 (ah80129-il)
AH 80-129 - Althaus AH 80-129 airfoil
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(ah80129-il) AH 80-129 Althaus AH 80-129 airfoil Max thickness 12.9% at 40.2% chord. Max camber 4.1% at 43.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH 80-129 1.00000 0.00000 0.99893 0.00095 0.99572 0.00125 0.99039 0.00180 0.98296 0.00258 0.97347 0.00380 0.96194 0.00550 0.94844 0.00774 0.93301 0.01057 0.91573 0.01404 0.89668 0.01817 0.87592 0.02299 0.85355 0.02848 0.82967 0.03465 0.80438 0.04149 0.77779 0.04890 0.75000 0.05666 0.72114 0.06448 0.69134 0.07200 0.66072 0.07897 0.62941 0.08524 0.59755 0.09072 0.56526 0.09535 0.53270 0.09909 0.50000 0.10191 0.46730 0.10383 0.43474 0.10482 0.40245 0.10490 0.37059 0.10408 0.33928 0.10240 0.30866 0.09993 0.27886 0.09670 0.25000 0.09277 0.22221 0.08818 0.19562 0.08303 0.17033 0.07740 0.14645 0.07139 0.12408 0.06508 0.10332 0.05853 0.08427 0.05181 0.06699 0.04499 0.05156 0.03816 0.03806 0.03139 0.02653 0.02479 0.01704 0.01848 0.00961 0.01269 0.00428 0.00756 0.00107 0.00330 0.00000 0.00000 0.00107 -0.00271 0.00428 -0.00517 0.00961 -0.00769 0.01704 -0.01017 0.02653 -0.01238 0.03806 -0.01429 0.05156 -0.01592 0.06699 -0.01734 0.08427 -0.01860 0.10332 -0.01971 0.12408 -0.02066 0.14645 -0.02147 0.17033 -0.02216 0.19562 -0.02273 0.22221 -0.02318 0.25000 -0.02352 0.27886 -0.02375 0.30866 -0.02389 0.33928 -0.02393 0.37059 -0.02388 0.40245 -0.02375 0.43474 -0.02354 0.46730 -0.02325 0.50000 -0.02287 0.53270 -0.02241 0.56526 -0.02186 0.59755 -0.02121 0.62941 -0.02046 0.66072 -0.01961 0.69134 -0.01862 0.72114 -0.01749 0.75000 -0.01619 0.77779 -0.01476 0.80438 -0.01323 0.82967 -0.01168 0.85355 -0.01015 0.87592 -0.00867 0.89668 -0.00730 0.91573 -0.00605 0.93301 -0.00495 0.94844 -0.00400 0.96194 -0.00318 0.97347 -0.00250 0.98296 -0.00195 0.99039 -0.00156 0.99572 -0.00118 0.99893 -0.00093 1.00000 0.00000 |
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Polars for AH 80-129 (ah80129-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah80129-il | 50,000 | 9 | 18.2 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80129-il | 50,000 | 5 | 19 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80129-il | 100,000 | 9 | 37.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80129-il | 100,000 | 5 | 39.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80129-il | 200,000 | 9 | 79 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80129-il | 200,000 | 5 | 78.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80129-il | 500,000 | 9 | 124.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80129-il | 500,000 | 5 | 121.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80129-il | 1,000,000 | 9 | 152.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80129-il | 1,000,000 | 5 | 143.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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