AH 85-L-120/17 (ah85l120-il)
AH 85-L-120/17 - Althaus AH 85-L-120/17 symmetrical airfoil
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(ah85l120-il) AH 85-L-120/17 Althaus AH 85-L-120/17 symmetrical airfoil Max thickness 12.1% at 43.5% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH 85-L-120/17 1.00000 0.00000 0.99893 0.00080 0.99572 0.00112 0.99039 0.00167 0.98296 0.00229 0.97347 0.00314 0.96194 0.00422 0.94844 0.00564 0.93301 0.00746 0.91573 0.00976 0.89668 0.01260 0.87592 0.01602 0.85355 0.02003 0.82967 0.02455 0.80438 0.02941 0.77779 0.03434 0.75000 0.03903 0.72114 0.04330 0.69134 0.04707 0.66072 0.05032 0.62941 0.05308 0.59755 0.05538 0.56526 0.05725 0.53270 0.05870 0.50000 0.05975 0.46730 0.06036 0.43474 0.06055 0.40245 0.06032 0.37059 0.05971 0.33928 0.05871 0.30866 0.05738 0.27886 0.05573 0.25000 0.05380 0.22221 0.05160 0.19562 0.04913 0.17033 0.04640 0.14645 0.04344 0.12408 0.04027 0.10332 0.03690 0.08427 0.03335 0.06699 0.02966 0.05156 0.02585 0.03806 0.02196 0.02653 0.01807 0.01704 0.01427 0.00961 0.01060 0.00428 0.00706 0.00107 0.00354 0.00000 0.00000 0.00107 -0.00354 0.00428 -0.00706 0.00961 -0.01060 0.01704 -0.01427 0.02653 -0.01807 0.03806 -0.02196 0.05156 -0.02585 0.06699 -0.02966 0.08427 -0.03335 0.10332 -0.03690 0.12408 -0.04027 0.14645 -0.04344 0.17033 -0.04640 0.19562 -0.04913 0.22221 -0.05160 0.25000 -0.05380 0.27886 -0.05573 0.30866 -0.05738 0.33928 -0.05871 0.37059 -0.05971 0.40245 -0.06032 0.43474 -0.06055 0.46730 -0.06036 0.50000 -0.05975 0.53270 -0.05870 0.56526 -0.05725 0.59755 -0.05538 0.62941 -0.05308 0.66072 -0.05032 0.69134 -0.04707 0.72114 -0.04330 0.75000 -0.03903 0.77779 -0.03434 0.80438 -0.02941 0.82967 -0.02455 0.85355 -0.02003 0.87592 -0.01602 0.89668 -0.01260 0.91573 -0.00976 0.93301 -0.00746 0.94844 -0.00564 0.96194 -0.00422 0.97347 -0.00314 0.98296 -0.00229 0.99039 -0.00167 0.99572 -0.00112 0.99893 -0.00080 1.00000 0.00000 |
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Polars for AH 85-L-120/17 (ah85l120-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah85l120-il | 50,000 | 9 | 21.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 50,000 | 5 | 27.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 100,000 | 9 | 37.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 100,000 | 5 | 29.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 200,000 | 5 | 35 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 500,000 | 9 | 48.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 500,000 | 5 | 43.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 1,000,000 | 9 | 55.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 1,000,000 | 5 | 52 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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