AH 88-K-130/20 (ah88k130-il)
AH 88-K-130/20 - Althaus AH 88-K-130/20 airfoil for use with flaps (K)
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(ah88k130-il) AH 88-K-130/20 Althaus AH 88-K-130/20 airfoil for use with flaps (K) Max thickness 13% at 43.5% chord. Max camber 3.9% at 46.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH 88-K-130/20 1.00000 0.00000 0.99893 0.00050 0.99572 0.00166 0.99039 0.00324 0.98296 0.00523 0.97347 0.00766 0.96194 0.01054 0.94844 0.01390 0.93301 0.01777 0.91573 0.02216 0.89668 0.02720 0.87592 0.03263 0.85355 0.03865 0.82967 0.04524 0.80438 0.05229 0.77779 0.05983 0.75000 0.06761 0.72114 0.07531 0.69134 0.08191 0.66072 0.08742 0.62941 0.09204 0.59755 0.09600 0.56526 0.09921 0.53270 0.10171 0.50000 0.10345 0.46730 0.10429 0.43474 0.10410 0.40245 0.10321 0.37059 0.10160 0.33928 0.09935 0.30866 0.09648 0.27886 0.09304 0.25000 0.08911 0.22221 0.08467 0.19562 0.07982 0.17033 0.07458 0.14645 0.06905 0.12408 0.06315 0.10332 0.05712 0.08427 0.05086 0.06699 0.04458 0.05156 0.03815 0.03806 0.03190 0.02653 0.02555 0.01704 0.01986 0.00961 0.01400 0.00428 0.00889 0.00107 0.00445 0.00000 0.00000 0.00107 -0.00252 0.00428 -0.00503 0.00961 -0.00747 0.01704 -0.00951 0.02653 -0.01138 0.03806 -0.01339 0.05156 -0.01494 0.06699 -0.01661 0.08427 -0.01803 0.10332 -0.01939 0.12408 -0.02058 0.14645 -0.02174 0.17033 -0.02271 0.19562 -0.02359 0.22221 -0.02436 0.25000 -0.02500 0.27886 -0.02548 0.30866 -0.02588 0.33928 -0.02612 0.37059 -0.02619 0.40245 -0.02614 0.43474 -0.02590 0.46730 -0.02549 0.50000 -0.02484 0.53270 -0.02393 0.56526 -0.02264 0.59755 -0.02120 0.62941 -0.01956 0.66072 -0.01782 0.69134 -0.01584 0.72114 -0.01374 0.75000 -0.01118 0.77779 -0.00793 0.80438 -0.00452 0.82967 -0.00162 0.85355 0.00073 0.87592 0.00246 0.89668 0.00390 0.91573 0.00429 0.93301 0.00450 0.94844 0.00435 0.96194 0.00389 0.97347 0.00323 0.98296 0.00245 0.99039 0.00165 0.99572 0.00095 0.99893 0.00032 1.00000 0.00000 |
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Polars for AH 88-K-130/20 (ah88k130-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah88k130-il | 50,000 | 9 | 23.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k130-il | 50,000 | 5 | 23.9 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k130-il | 100,000 | 9 | 42.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k130-il | 100,000 | 5 | 43 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k130-il | 200,000 | 9 | 80.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k130-il | 200,000 | 5 | 79 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k130-il | 500,000 | 9 | 121.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k130-il | 500,000 | 5 | 113.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k130-il | 1,000,000 | 9 | 147.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k130-il | 1,000,000 | 5 | 136.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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