AH21 7% version (Andrew Hollom) (ah21-7-il)
AH21 7% version (Andrew Hollom) - Andrew Hollom AH 21 airfoil (7% version)
| Details | Dat file | Parser | |
|
(ah21-7-il) AH21 7% version (Andrew Hollom) Andrew Hollom AH 21 airfoil (7% version) Max thickness 9% at 34.9% chord. Max camber 2.3% at 54.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AH21 7% version (Andrew Hollom) 1.0000000 0.0000000 0.9967100 0.0009314 0.9872600 0.0035706 0.9723700 0.0075969 0.9524800 0.0126863 0.9276400 0.0185609 0.8981000 0.0248808 0.8642700 0.0313127 0.8266000 0.0375827 0.7855700 0.0434800 0.7416500 0.0488517 0.6953700 0.0535828 0.6472300 0.0575969 0.5977800 0.0608404 0.5475300 0.0632834 0.4970200 0.0649109 0.4467600 0.0657221 0.3972700 0.0657269 0.3490400 0.0649449 0.3024800 0.0634012 0.2580900 0.0611299 0.2162400 0.0581671 0.1773000 0.0545534 0.1416100 0.0503329 0.1094500 0.0455491 0.0810800 0.0402484 0.0567300 0.0344806 0.0365800 0.0282955 0.0207600 0.0217406 0.0093200 0.0148312 0.0023500 0.0075710 0.0000000 0.0000000 0.0033600 -0.0057599 0.0124700 -0.0104865 0.0267000 -0.0144754 0.0459600 -0.0178557 0.0701000 -0.0206495 0.0989600 -0.0228677 0.1322400 -0.0245135 0.1696300 -0.0255990 0.2107300 -0.0261407 0.2550900 -0.0261625 0.3022100 -0.0256954 0.3515600 -0.0247772 0.4025700 -0.0234525 0.4546300 -0.0217730 0.5071300 -0.0197961 0.5594400 -0.0175855 0.6112800 -0.0151937 0.6624400 -0.0126711 0.7123700 -0.0100895 0.7603700 -0.0075383 0.8057500 -0.0051168 0.8477900 -0.0029367 0.8858300 -0.0011146 0.9192500 0.0002332 0.9474800 0.0010094 0.9700300 0.0011751 0.9865300 0.0008241 0.9966000 0.0002719 1.0000000 0.0000000 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for AH21 7% version (Andrew Hollom) (ah21-7-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah21-7-il | 50,000 | 9 | 35.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 50,000 | 5 | 35.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 100,000 | 9 | 55.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 100,000 | 5 | 51.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 200,000 | 9 | 78.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 200,000 | 5 | 69.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 500,000 | 9 | 111.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 500,000 | 5 | 82.9 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 1,000,000 | 9 | 119.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 1,000,000 | 5 | 84.7 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||