AH 81-131 (ah81131-il)
AH 81-131 - Althaus AH 81-131 airfoil
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(ah81131-il) AH 81-131 Althaus AH 81-131 airfoil Max thickness 13.1% at 40.2% chord. Max camber 2.8% at 40.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH 81-131 1.00000 0.00000 0.99893 -0.00014 0.99572 -0.00043 0.99039 -0.00070 0.98296 -0.00083 0.97347 -0.00073 0.96194 -0.00032 0.94844 0.00049 0.93301 0.00180 0.91573 0.00375 0.89668 0.00641 0.87592 0.00989 0.85355 0.01427 0.82967 0.01962 0.80438 0.02601 0.77779 0.03342 0.75000 0.04168 0.72114 0.05039 0.69134 0.05898 0.66072 0.06686 0.62941 0.07371 0.59755 0.07948 0.56526 0.08426 0.53270 0.08806 0.50000 0.09083 0.46730 0.09259 0.43474 0.09337 0.40245 0.09349 0.37059 0.09303 0.33928 0.09199 0.30866 0.09024 0.27886 0.08771 0.25000 0.08461 0.22221 0.08102 0.19562 0.07696 0.17033 0.07244 0.14645 0.06746 0.12408 0.06206 0.10332 0.05634 0.08427 0.05039 0.06699 0.04437 0.05156 0.03836 0.03806 0.03249 0.02653 0.02680 0.01704 0.02103 0.00961 0.01514 0.00428 0.00934 0.00107 0.00428 0.00000 0.00058 0.00107 -0.00222 0.00428 -0.00460 0.00961 -0.00698 0.01704 -0.00948 0.02653 -0.01186 0.03806 -0.01419 0.05156 -0.01649 0.06699 -0.01878 0.08427 -0.02106 0.10332 -0.02329 0.12408 -0.02537 0.14645 -0.02729 0.17033 -0.02913 0.19562 -0.03083 0.22221 -0.03239 0.25000 -0.03375 0.27886 -0.03484 0.30866 -0.03567 0.33928 -0.03634 0.37059 -0.03680 0.40245 -0.03703 0.43474 -0.03702 0.46730 -0.03671 0.50000 -0.03624 0.53270 -0.03555 0.56526 -0.03467 0.59755 -0.03362 0.62941 -0.03238 0.66072 -0.03103 0.69134 -0.02956 0.72114 -0.02801 0.75000 -0.02642 0.77779 -0.02477 0.80438 -0.02305 0.82967 -0.02124 0.85355 -0.01935 0.87592 -0.01738 0.89668 -0.01529 0.91573 -0.01312 0.93301 -0.01092 0.94844 -0.00878 0.96194 -0.00678 0.97347 -0.00498 0.98296 -0.00343 0.99039 -0.00215 0.99572 -0.00114 0.99893 -0.00043 1.00000 0.00000 |
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Polars for AH 81-131 (ah81131-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah81131-il | 50,000 | 9 | 23.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81131-il | 50,000 | 5 | 21.5 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81131-il | 100,000 | 9 | 37.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81131-il | 100,000 | 5 | 38.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81131-il | 200,000 | 9 | 72.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81131-il | 200,000 | 5 | 70.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81131-il | 500,000 | 9 | 110 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81131-il | 500,000 | 5 | 95.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81131-il | 1,000,000 | 9 | 126.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81131-il | 1,000,000 | 5 | 104.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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