AH 80-136 (ah80136-il)
AH 80-136 - Althaus AH 80-136 airfoil
| Details | Dat file | Parser | |
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(ah80136-il) AH 80-136 Althaus AH 80-136 airfoil Max thickness 13.5% at 33.9% chord. Max camber 3.4% at 33.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH 80-136 1.00000 0.00146 0.99893 0.00146 0.99572 0.00144 0.99039 0.00123 0.98296 0.00098 0.97347 0.00083 0.96194 0.00096 0.94844 0.00146 0.93301 0.00232 0.91573 0.00355 0.89668 0.00525 0.87592 0.00757 0.85355 0.01058 0.82967 0.01429 0.80438 0.01868 0.77779 0.02374 0.75000 0.02948 0.72114 0.03588 0.69134 0.04290 0.66072 0.05042 0.62941 0.05823 0.59755 0.06616 0.56526 0.07398 0.53270 0.08141 0.50000 0.08802 0.46730 0.09344 0.43474 0.09749 0.40245 0.10017 0.37059 0.10156 0.33928 0.10177 0.30866 0.10093 0.27886 0.09918 0.25000 0.09659 0.22221 0.09316 0.19562 0.08890 0.17033 0.08388 0.14645 0.07824 0.12408 0.07204 0.10332 0.06536 0.08427 0.05829 0.06699 0.05097 0.05156 0.04361 0.03806 0.03635 0.02653 0.02929 0.01704 0.02243 0.00961 0.01583 0.00428 0.00972 0.00107 0.00441 0.00000 0.00000 0.00107 -0.00373 0.00428 -0.00707 0.00961 -0.01008 0.01704 -0.01270 0.02653 -0.01495 0.03806 -0.01703 0.05156 -0.01913 0.06699 -0.02124 0.08427 -0.02326 0.10332 -0.02510 0.12408 -0.02673 0.14645 -0.02817 0.17033 -0.02945 0.19562 -0.03058 0.22221 -0.03155 0.25000 -0.03233 0.27886 -0.03295 0.30866 -0.03342 0.33928 -0.03372 0.37059 -0.03382 0.40245 -0.03365 0.43474 -0.03318 0.46730 -0.03241 0.50000 -0.03136 0.53270 -0.03013 0.56526 -0.02885 0.59755 -0.02756 0.62941 -0.02625 0.66072 -0.02491 0.69134 -0.02353 0.72114 -0.02205 0.75000 -0.02043 0.77779 -0.01865 0.80438 -0.01682 0.82967 -0.01504 0.85355 -0.01334 0.87592 -0.01168 0.89668 -0.00999 0.91573 -0.00828 0.93301 -0.00666 0.94844 -0.00524 0.96194 -0.00402 0.97347 -0.00296 0.98296 -0.00201 0.99039 -0.00123 0.99572 -0.00061 0.99893 -0.00049 1.00000 -0.00029 |
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Polars for AH 80-136 (ah80136-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah80136-il | 50,000 | 9 | 14.9 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80136-il | 50,000 | 5 | 13.8 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80136-il | 100,000 | 9 | 32.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80136-il | 100,000 | 5 | 33.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80136-il | 200,000 | 9 | 71 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80136-il | 200,000 | 5 | 71.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80136-il | 500,000 | 9 | 110.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80136-il | 500,000 | 5 | 105.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80136-il | 1,000,000 | 9 | 138.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80136-il | 1,000,000 | 5 | 127.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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