AH21 9% version (Andrew Hollom) (ah21-9-il)
AH21 9% version (Andrew Hollom) - Andrew Hollom AH 21 airfoil (original 9% version)
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(ah21-9-il) AH21 9% version (Andrew Hollom) Andrew Hollom AH 21 airfoil (original 9% version) Max thickness 7% at 34.9% chord. Max camber 1.8% at 54.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH21 9% version (Andrew Hollom) 1.0000000 0.0000000 0.9967100 0.0007263 0.9872600 0.0027842 0.9723700 0.0059238 0.9524800 0.0098924 0.9276400 0.0144732 0.8981000 0.0194013 0.8642700 0.0244167 0.8266000 0.0293058 0.7855700 0.0339044 0.7416500 0.0380931 0.6953700 0.0417822 0.6472300 0.0449123 0.5977800 0.0474415 0.5475300 0.0493465 0.4970200 0.0506155 0.4467600 0.0512481 0.3972700 0.0512518 0.3490400 0.0506421 0.3024800 0.0494383 0.2580900 0.0476672 0.2162400 0.0453569 0.1773000 0.0425391 0.1416100 0.0392481 0.1094500 0.0355178 0.0810800 0.0313845 0.0567300 0.0268869 0.0365800 0.0220640 0.0207600 0.0169527 0.0093200 0.0115649 0.0023500 0.0059036 0.0000000 0.0000000 0.0033600 -0.0044914 0.0124700 -0.0081771 0.0267000 -0.0112875 0.0459600 -0.0139233 0.0701000 -0.0161019 0.0989600 -0.0178315 0.1322400 -0.0191149 0.1696300 -0.0199613 0.2107300 -0.0203837 0.2550900 -0.0204007 0.3022100 -0.0200365 0.3515600 -0.0193205 0.4025700 -0.0182875 0.4546300 -0.0169779 0.5071300 -0.0154364 0.5594400 -0.0137126 0.6112800 -0.0118476 0.6624400 -0.0098805 0.7123700 -0.0078675 0.7603700 -0.0058781 0.8057500 -0.0039899 0.8477900 -0.0022899 0.8858300 -0.0008691 0.9192500 0.0001818 0.9474800 0.0007871 0.9700300 0.0009163 0.9865300 0.0006426 0.9966000 0.0002120 1.0000000 0.0000000 |
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Polars for AH21 9% version (Andrew Hollom) (ah21-9-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah21-9-il | 50,000 | 9 | 34.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-9-il | 50,000 | 5 | 34.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-9-il | 100,000 | 9 | 51.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-9-il | 100,000 | 5 | 49 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-9-il | 200,000 | 9 | 73.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-9-il | 200,000 | 5 | 65 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-9-il | 500,000 | 9 | 103.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-9-il | 500,000 | 5 | 78.4 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-9-il | 1,000,000 | 9 | 113.5 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-9-il | 1,000,000 | 5 | 79.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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