E591 (e591-il)
E591 - Eppler E591 airfoil
| Details | Dat file | Parser | |
|
(e591-il) E591 Eppler E591 airfoil Max thickness 15.7% at 25% chord. Max camber 6% at 52.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E591 1.0000 0.0000 .99670 .00151 .98763 .00596 .97400 .01261 .95603 .02021 .93329 .02833 .90580 .03709 .87400 .04649 .83835 .05635 .79931 .06650 .75738 .07674 .71308 .08683 .66693 .09655 .61945 .10567 .57115 .11396 .52254 .12120 .47411 .12720 .42634 .13177 .37968 .13476 .33458 .13601 .29138 .13535 .25036 .13275 .21180 .12821 .17596 .12177 .14305 .11353 .11326 .10364 .08675 .09230 .06364 .07972 .04403 .06620 .02798 .05207 .01550 .03772 .00666 .02364 .00149 .01035 .00004 -.00146 .00255 -.01054 .01087 -.01687 .02578 -.02178 .04618 -.02567 .07166 -.02847 .10182 -.03016 .13624 -.03061 .17460 -.02955 .21678 -.02692 .26259 -.02276 .31189 -.01726 .36440 -.01086 .41959 -.00404 .47679 .00277 .53527 .00917 .59420 .01477 .65267 .01924 .70971 .02232 .76431 .02384 .81546 .02372 .86213 .02201 .90338 .01888 .93829 .01454 .96583 .00941 .98516 .00454 .99636 .00118 1.0000 0.00000 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for E591 (e591-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e591-il | 50,000 | 9 | 10 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e591-il | 50,000 | 5 | 34.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e591-il | 100,000 | 9 | 52.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e591-il | 100,000 | 5 | 57.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e591-il | 200,000 | 9 | 77.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e591-il | 200,000 | 5 | 76.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e591-il | 500,000 | 9 | 107.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e591-il | 500,000 | 5 | 99.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e591-il | 1,000,000 | 9 | 129.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e591-il | 1,000,000 | 5 | 118.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||