E63 (4.25%) (e63-il)
E63 (4.25%) - Eppler E63 low Reynolds number airfoil
| Details | Dat file | Parser | |
|
(e63-il) E63 (4.25%) Eppler E63 low Reynolds number airfoil Max thickness 4.3% at 22.8% chord. Max camber 5.3% at 50.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E63 (4.25%) 1.00000 0.00000 0.99719 0.00121 0.98938 0.00473 0.97751 0.00986 0.96173 0.01553 0.94164 0.02126 0.91717 0.02709 0.88861 0.03301 0.85624 0.03885 0.82039 0.04451 0.78141 0.04985 0.73968 0.05480 0.69562 0.05921 0.64967 0.06304 0.60229 0.06617 0.55394 0.06857 0.50509 0.07016 0.45624 0.07094 0.40786 0.07084 0.36043 0.06990 0.31441 0.06809 0.27026 0.06545 0.22840 0.06198 0.18920 0.05775 0.15304 0.05280 0.12023 0.04723 0.09103 0.04111 0.06568 0.03457 0.04435 0.02775 0.02714 0.02083 0.01416 0.01404 0.00536 0.00766 0.00076 0.00218 0.00055 -0.00141 0.00557 -0.00306 0.01651 -0.00330 0.03316 -0.00227 0.05550 -0.00004 0.08342 0.00315 0.11671 0.00708 0.15504 0.01151 0.19800 0.01620 0.24509 0.02093 0.29574 0.02546 0.34931 0.02962 0.40513 0.03319 0.46247 0.03605 0.52056 0.03803 0.57859 0.03907 0.63576 0.03907 0.69125 0.03806 0.74430 0.03604 0.79414 0.03310 0.84004 0.02930 0.88132 0.02482 0.91735 0.01979 0.94756 0.01439 0.97115 0.00887 0.98754 0.00410 0.99695 0.00102 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 E63 (4.25%) (e63-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e63-il | 50,000 | 9 | 52 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 50,000 | 5 | 51.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 100,000 | 9 | 77.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 100,000 | 5 | 77.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 200,000 | 9 | 112.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 200,000 | 5 | 110 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 500,000 | 9 | 176.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 500,000 | 5 | 160 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e63-il | 1,000,000 | 9 | 235.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e63-il | 1,000,000 | 5 | 157.7 at α=0° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||