E471 (6.25%) (e471-il)
E471 (6.25%) - Eppler E471 airfoil
| Details | Dat file | Parser | |
|
(e471-il) E471 (6.25%) Eppler E471 airfoil Max thickness 6.3% at 29.8% chord. Max camber 4.5% at 53.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E471 (6.25%) 1.00000 0.00000 0.99699 0.00085 0.98831 0.00344 0.97463 0.00763 0.95649 0.01293 0.93407 0.01878 0.90737 0.02492 0.87660 0.03135 0.84217 0.03797 0.80453 0.04461 0.76414 0.05108 0.72144 0.05712 0.67681 0.06252 0.63065 0.06712 0.58334 0.07077 0.53527 0.07339 0.48681 0.07494 0.43840 0.07550 0.39052 0.07508 0.34368 0.07372 0.29833 0.07143 0.25493 0.06826 0.21391 0.06425 0.17566 0.05946 0.14054 0.05397 0.10888 0.04785 0.08095 0.04121 0.05695 0.03417 0.03707 0.02688 0.02141 0.01953 0.01002 0.01238 0.00292 0.00573 0.00001 0.00023 0.00239 -0.00342 0.01071 -0.00580 0.02439 -0.00732 0.04344 -0.00777 0.06777 -0.00722 0.09726 -0.00574 0.13171 -0.00347 0.17080 -0.00059 0.21417 0.00270 0.26132 0.00621 0.31171 0.00975 0.36472 0.01316 0.41971 0.01627 0.47597 0.01894 0.53279 0.02105 0.58940 0.02252 0.64507 0.02328 0.69902 0.02330 0.75054 0.02256 0.79889 0.02112 0.84341 0.01902 0.88346 0.01635 0.91844 0.01322 0.94783 0.00975 0.97096 0.00610 0.98730 0.00287 0.99687 0.00072 1.00000 0.00000 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for E471 (6.25%) (e471-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e471-il | 50,000 | 9 | 46.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e471-il | 50,000 | 5 | 46.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e471-il | 100,000 | 9 | 73 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e471-il | 100,000 | 5 | 72 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e471-il | 200,000 | 9 | 105.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e471-il | 200,000 | 5 | 101.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e471-il | 500,000 | 9 | 153.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e471-il | 500,000 | 5 | 138.5 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e471-il | 1,000,000 | 9 | 189.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e471-il | 1,000,000 | 5 | 152 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||