E231 (e231-il)
E231 - Eppler E231 R/C sailplane airfoil
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(e231-il) E231 Eppler E231 R/C sailplane airfoil Max thickness 12.3% at 39.4% chord. Max camber 2.5% at 39.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E231 1 0 .9963 .00039 .98554 .00187 .96845 .00477 .94569 .00903 .91774 .0146 .88524 .02148 .84897 .02952 .80968 .03837 .7681 .04759 .72481 .05653 .68007 .06458 .63395 .07143 .58671 .07701 .53865 .08126 .49016 .08419 .44164 .08584 .39357 .08628 .34646 .08556 .30081 .08370 .2571 .08074 .21576 .07671 .17721 .07166 .14182 .06565 .10989 .05877 .08171 .05111 .05750 .04282 .03741 .03407 .02158 .02508 .01005 .01613 .00284 .00764 .00018 .00152 0 0 .00020 -.00139 .00093 -.00259 .00217 -.00382 .00325 -.00466 .01291 -.00966 .02804 -.01448 .04843 -.01890 .07381 -.02288 .10394 -.02638 .13848 -.02938 .17704 -.03189 .21921 -.03389 .26450 -.03541 .31240 -.03644 .36238 -.03700 .41385 -.03711 .46624 -.03677 .51892 -.03599 .5713 -.03477 .62279 -.03312 .67278 -.03104 .72067 -.02851 .76591 -.02537 .80826 -.02146 .84766 -.01692 .88392 -.01224 .91658 -.00796 .94488 -.00453 .96803 -.00209 .98539 -.00063 .99628 -.00007 1 0 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for E231 (e231-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e231-il | 50,000 | 9 | 32.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e231-il | 50,000 | 5 | 30.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e231-il | 100,000 | 9 | 53 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e231-il | 100,000 | 5 | 51.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e231-il | 200,000 | 9 | 77.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e231-il | 200,000 | 5 | 68.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e231-il | 500,000 | 9 | 93.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e231-il | 500,000 | 5 | 76.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e231-il | 1,000,000 | 9 | 102.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e231-il | 1,000,000 | 5 | 85.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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