EPPLER 1210 AIRFOIL (e1210-il)
EPPLER 1210 AIRFOIL - Eppler E1210 general aviation airfoil
| Details | Dat file | Parser | |
|
(e1210-il) EPPLER 1210 AIRFOIL Eppler E1210 general aviation airfoil Max thickness 15.9% at 21.1% chord. Max camber 5.2% at 33.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 1210 AIRFOIL
33.0 29.0
0.0000000 0.0000000
0.0019187 0.0120735
0.0075094 0.0260532
0.0167402 0.0405828
0.0296010 0.0551821
0.0459818 0.0694713
0.0657626 0.0830502
0.0887533 0.0955690
0.1147539 0.1065476
0.1437745 0.1155061
0.1759049 0.1222544
0.2110452 0.1267325
0.2491054 0.1288605
0.2899455 0.1287383
0.3333054 0.1265160
0.3788753 0.1223235
0.4263151 0.1163710
0.4752148 0.1089283
0.5251344 0.1002656
0.5755740 0.0907229
0.6259636 0.0806202
0.6756831 0.0703075
0.7240927 0.0600849
0.7705122 0.0502424
0.8142418 0.0410200
0.8545914 0.0325879
0.8909011 0.0250659
0.9225708 0.0184942
0.9490406 0.0127528
0.9701403 0.0076216
0.9860602 0.0033908
0.9963701 0.0007902
1.0000000 -.0000000
0.0000000 0.0000000
0.0024474 -.0110466
0.0102570 -.0194770
0.0232366 -.0268977
0.0408363 -.0326487
0.0631962 -.0363399
0.0905362 -.0377614
0.1232563 -.0371431
0.1612764 -.0351551
0.2040367 -.0322874
0.2509370 -.0288099
0.3013373 -.0249726
0.3545476 -.0209555
0.4098679 -.0169584
0.4665383 -.0130914
0.5238185 -.0095045
0.5809288 -.0062876
0.6370991 -.0035006
0.6915894 -.0012235
0.7436395 0.0005237
0.7925397 0.0017411
0.8376198 0.0024487
0.8782199 0.0026765
0.9137599 0.0025146
0.9437100 0.0020730
0.9676700 0.0015317
0.9853400 0.0009208
0.9962800 0.0003002
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 EPPLER 1210 AIRFOIL (e1210-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1210-il | 50,000 | 9 | 8.9 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 50,000 | 5 | 25.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 100,000 | 9 | 35.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 100,000 | 5 | 45.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 200,000 | 9 | 60.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 200,000 | 5 | 65.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 500,000 | 9 | 92.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 500,000 | 5 | 93.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 1,000,000 | 9 | 119.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 1,000,000 | 5 | 117.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||