AH 82-150 A (ah82150a-il)
AH 82-150 A - Althaus AH 82-150 A airfoil
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(ah82150a-il) AH 82-150 A Althaus AH 82-150 A airfoil Max thickness 15% at 40.2% chord. Max camber 3.3% at 43.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH 82-150 A 1.00000 0.00000 0.99893 0.00046 0.99572 0.00150 0.99039 0.00298 0.98296 0.00487 0.97347 0.00714 0.96194 0.00984 0.94844 0.01300 0.93301 0.01666 0.91573 0.02083 0.89668 0.02549 0.87592 0.03065 0.85355 0.03628 0.82967 0.04234 0.80438 0.04876 0.77779 0.05550 0.75000 0.06246 0.72114 0.06950 0.69134 0.07643 0.66072 0.08304 0.62941 0.08914 0.59755 0.09450 0.56526 0.09901 0.53270 0.10258 0.50000 0.10523 0.46730 0.10695 0.43474 0.10778 0.40245 0.10779 0.37059 0.10704 0.33928 0.10556 0.30866 0.10337 0.27886 0.10045 0.25000 0.09682 0.22221 0.09249 0.19562 0.08751 0.17033 0.08196 0.14645 0.07590 0.12408 0.06943 0.10332 0.06262 0.08427 0.05558 0.06699 0.04843 0.05156 0.04126 0.03806 0.03409 0.02653 0.02698 0.01704 0.02016 0.00961 0.01397 0.00428 0.00861 0.00107 0.00406 0.00000 0.00000 0.00107 -0.00395 0.00428 -0.00790 0.00961 -0.01169 0.01704 -0.01511 0.02653 -0.01808 0.03806 -0.02078 0.05156 -0.02332 0.06699 -0.02572 0.08427 -0.02799 0.10332 -0.03011 0.12408 -0.03209 0.14645 -0.03389 0.17033 -0.03550 0.19562 -0.03692 0.22221 -0.03817 0.25000 -0.03924 0.27886 -0.04016 0.30866 -0.04093 0.33928 -0.04155 0.37059 -0.04199 0.40245 -0.04220 0.43474 -0.04216 0.46730 -0.04184 0.50000 -0.04122 0.53270 -0.04023 0.56526 -0.03880 0.59755 -0.03674 0.62941 -0.03384 0.66072 -0.03006 0.69134 -0.02562 0.72114 -0.02089 0.75000 -0.01624 0.77779 -0.01192 0.80438 -0.00808 0.82967 -0.00482 0.85355 -0.00217 0.87592 -0.00013 0.89668 0.00134 0.91573 0.00229 0.93301 0.00279 0.94844 0.00291 0.96194 0.00271 0.97347 0.00229 0.98296 0.00176 0.99039 0.00120 0.99572 0.00070 0.99893 0.00026 1.00000 0.00000 |
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Polars for AH 82-150 A (ah82150a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah82150a-il | 50,000 | 9 | 17.8 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 50,000 | 5 | 20.2 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 100,000 | 9 | 42.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 100,000 | 5 | 41.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 200,000 | 9 | 72.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 200,000 | 5 | 73.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 500,000 | 9 | 108.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 500,000 | 5 | 107.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 1,000,000 | 9 | 137.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 1,000,000 | 5 | 129.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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