AH 80-140 (ah80140-il)
AH 80-140 - Althaus AH 80-140 airfoil
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(ah80140-il) AH 80-140 Althaus AH 80-140 airfoil Max thickness 14% at 30.9% chord. Max camber 4.4% at 33.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH 80-140 1.00000 0.00000 0.99893 0.00097 0.99572 0.00161 0.99039 0.00246 0.98296 0.00347 0.97347 0.00477 0.96194 0.00625 0.94844 0.00806 0.93301 0.01008 0.91573 0.01247 0.89668 0.01511 0.87592 0.01816 0.85355 0.02152 0.82967 0.02535 0.80438 0.02953 0.77779 0.03420 0.75000 0.03927 0.72114 0.04487 0.69134 0.05082 0.66072 0.05724 0.62941 0.06395 0.59755 0.07105 0.56526 0.07822 0.53270 0.08550 0.50000 0.09256 0.46730 0.09927 0.43474 0.10497 0.40245 0.10925 0.37059 0.11184 0.33928 0.11315 0.30866 0.11312 0.27886 0.11200 0.25000 0.10968 0.22221 0.10635 0.19562 0.10198 0.17033 0.09691 0.14645 0.09105 0.12408 0.08470 0.10332 0.07767 0.08427 0.07024 0.06699 0.06229 0.05156 0.05421 0.03806 0.04584 0.02653 0.03774 0.01704 0.02975 0.00961 0.02234 0.00428 0.01511 0.00107 0.00812 0.00000 0.00000 0.00107 -0.00587 0.00428 -0.01064 0.00961 -0.01476 0.01704 -0.01798 0.02653 -0.02065 0.03806 -0.02257 0.05156 -0.02423 0.06699 -0.02540 0.08427 -0.02644 0.10332 -0.02710 0.12408 -0.02766 0.14645 -0.02792 0.17033 -0.02812 0.19562 -0.02804 0.22221 -0.02787 0.25000 -0.02748 0.27886 -0.02708 0.30866 -0.02651 0.33928 -0.02595 0.37059 -0.02523 0.40245 -0.02454 0.43474 -0.02369 0.46730 -0.02280 0.50000 -0.02175 0.53270 -0.02066 0.56526 -0.01939 0.59755 -0.01812 0.62941 -0.01672 0.66072 -0.01536 0.69134 -0.01392 0.72114 -0.01252 0.75000 -0.01107 0.77779 -0.00967 0.80438 -0.00828 0.82967 -0.00703 0.85355 -0.00582 0.87592 -0.00479 0.89668 -0.00382 0.91573 -0.00306 0.93301 -0.00239 0.94844 -0.00193 0.96194 -0.00152 0.97347 -0.00128 0.98296 -0.00108 0.99039 -0.00101 0.99572 -0.00093 0.99893 -0.00080 1.00000 0.00000 |
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Polars for AH 80-140 (ah80140-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah80140-il | 50,000 | 9 | 5.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 50,000 | 5 | 14.3 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 100,000 | 9 | 22.5 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 100,000 | 5 | 35.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 200,000 | 9 | 70.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 200,000 | 5 | 74.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 500,000 | 9 | 116.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 500,000 | 5 | 113.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 1,000,000 | 9 | 149.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 1,000,000 | 5 | 139 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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