EPPLER 336 AIRFOIL (e336-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 336 AIRFOIL (e336-il) Reynolds number: 100,000 Max Cl/Cd: 35.73 at α=11.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e336-il-100000.txt Download as CSV file: xf-e336-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 336 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4387 0.11766 0.11293 -0.0065 1.0000 0.0767
-10.250 -0.4500 0.11443 0.10978 -0.0114 1.0000 0.0779
-10.000 -0.4665 0.11061 0.10605 -0.0175 1.0000 0.0784
-9.750 -0.4564 0.10522 0.10071 -0.0165 1.0000 0.0796
-9.500 -0.4318 0.10200 0.09747 -0.0123 1.0000 0.0826
-9.250 -0.4286 0.09848 0.09401 -0.0132 1.0000 0.0852
-9.000 -0.4312 0.09463 0.09022 -0.0156 1.0000 0.0878
-8.750 -0.4460 0.09002 0.08568 -0.0207 1.0000 0.0902
-8.500 -0.4719 0.08652 0.08218 -0.0235 1.0000 0.0913
-8.250 -0.5026 0.08473 0.08033 -0.0222 1.0000 0.0920
-8.000 -0.5286 0.08364 0.07905 -0.0199 1.0000 0.0925
-7.750 -0.4875 0.07559 0.07136 -0.0209 1.0000 0.0961
-7.500 -0.4846 0.07266 0.06846 -0.0197 1.0000 0.0990
-7.250 -0.4914 0.06993 0.06569 -0.0182 1.0000 0.1033
-7.000 -0.5289 0.07178 0.06697 -0.0130 1.0000 0.1074
-6.750 -0.5055 0.06403 0.05966 -0.0141 1.0000 0.1103
-6.500 -0.4983 0.06125 0.05698 -0.0122 1.0000 0.1148
-6.250 -0.5172 0.06141 0.05697 -0.0071 1.0000 0.1217
-6.000 -0.5001 0.05647 0.05212 -0.0091 0.9856 0.1269
-5.750 -0.4657 0.05230 0.04771 -0.0136 0.9596 0.1422
-5.500 -0.4321 0.04834 0.04362 -0.0167 0.9329 0.1598
-4.750 -0.3408 0.03586 0.02878 -0.0145 0.8588 0.0805
-4.500 -0.3136 0.03264 0.02493 -0.0122 0.8371 0.0638
-4.250 -0.2893 0.03006 0.02196 -0.0106 0.8174 0.0599
-4.000 -0.2628 0.02812 0.01924 -0.0082 0.7987 0.0553
-3.750 -0.2346 0.02654 0.01732 -0.0071 0.7804 0.0544
-3.500 -0.2043 0.02488 0.01536 -0.0065 0.7635 0.0546
-3.250 -0.1708 0.02283 0.01330 -0.0070 0.7476 0.0577
-3.000 -0.1423 0.02199 0.01232 -0.0064 0.7323 0.0650
-2.750 0.1587 0.01914 0.01216 -0.0461 0.6990 1.0000
-2.500 0.1790 0.01903 0.01177 -0.0451 0.6842 1.0000
-2.250 0.1994 0.01895 0.01143 -0.0442 0.6708 1.0000
-2.000 0.2201 0.01888 0.01115 -0.0433 0.6570 1.0000
-1.750 0.2411 0.01885 0.01094 -0.0424 0.6439 1.0000
-1.500 0.2623 0.01885 0.01075 -0.0416 0.6317 1.0000
-1.250 0.2834 0.01887 0.01055 -0.0406 0.6206 1.0000
-1.000 0.3050 0.01889 0.01043 -0.0398 0.6089 1.0000
-0.750 0.3269 0.01896 0.01038 -0.0390 0.5976 1.0000
-0.500 0.3488 0.01905 0.01028 -0.0382 0.5887 1.0000
-0.250 0.3710 0.01915 0.01029 -0.0375 0.5781 1.0000
0.000 0.3933 0.01929 0.01032 -0.0368 0.5693 1.0000
0.250 0.4157 0.01941 0.01033 -0.0360 0.5605 1.0000
0.500 0.4383 0.01960 0.01046 -0.0354 0.5525 1.0000
0.750 0.4608 0.01976 0.01053 -0.0346 0.5448 1.0000
1.000 0.4835 0.01998 0.01069 -0.0340 0.5380 1.0000
1.250 0.5062 0.02020 0.01089 -0.0334 0.5306 1.0000
1.500 0.5291 0.02040 0.01095 -0.0326 0.5254 1.0000
1.750 0.5516 0.02074 0.01138 -0.0321 0.5181 1.0000
2.000 0.5745 0.02098 0.01157 -0.0315 0.5124 1.0000
2.250 0.5972 0.02129 0.01184 -0.0308 0.5072 1.0000
2.500 0.6195 0.02167 0.01230 -0.0302 0.5006 1.0000
2.750 0.6425 0.02194 0.01253 -0.0295 0.4957 1.0000
3.000 0.6649 0.02234 0.01295 -0.0289 0.4907 1.0000
3.250 0.6867 0.02280 0.01351 -0.0283 0.4844 1.0000
3.500 0.7096 0.02306 0.01374 -0.0275 0.4795 1.0000
3.750 0.7315 0.02356 0.01429 -0.0269 0.4746 1.0000
4.000 0.7526 0.02412 0.01496 -0.0262 0.4684 1.0000
4.250 0.7754 0.02438 0.01522 -0.0254 0.4635 1.0000
4.500 0.7962 0.02498 0.01592 -0.0246 0.4582 1.0000
4.750 0.8164 0.02560 0.01666 -0.0238 0.4520 1.0000
5.000 0.8393 0.02585 0.01690 -0.0230 0.4474 1.0000
5.250 0.8580 0.02666 0.01787 -0.0220 0.4412 1.0000
5.500 0.8778 0.02724 0.01856 -0.0210 0.4351 1.0000
5.750 0.9012 0.02744 0.01871 -0.0201 0.4307 1.0000
6.000 0.9161 0.02857 0.02010 -0.0189 0.4237 1.0000
6.250 0.9367 0.02899 0.02057 -0.0178 0.4179 1.0000
6.500 0.9617 0.02904 0.02054 -0.0170 0.4137 1.0000
6.750 0.9710 0.03054 0.02240 -0.0153 0.4054 1.0000
7.000 0.9946 0.03059 0.02245 -0.0143 0.4002 1.0000
7.250 1.0085 0.03164 0.02367 -0.0127 0.3937 1.0000
7.500 1.0258 0.03221 0.02435 -0.0113 0.3871 1.0000
7.750 1.0549 0.03179 0.02384 -0.0107 0.3825 1.0000
8.000 1.0571 0.03359 0.02600 -0.0081 0.3738 1.0000
8.250 1.0866 0.03299 0.02532 -0.0074 0.3686 1.0000
8.500 1.0898 0.03460 0.02724 -0.0048 0.3603 1.0000
8.750 1.1200 0.03384 0.02642 -0.0041 0.3544 1.0000
9.000 1.1235 0.03526 0.02810 -0.0014 0.3460 1.0000
9.250 1.1550 0.03438 0.02714 -0.0009 0.3395 1.0000
9.500 1.1563 0.03584 0.02887 0.0022 0.3312 1.0000
9.750 1.1898 0.03481 0.02776 0.0025 0.3239 1.0000
10.000 1.1876 0.03628 0.02951 0.0061 0.3152 1.0000
10.250 1.2274 0.03490 0.02795 0.0057 0.3071 1.0000
10.500 1.2155 0.03663 0.03006 0.0105 0.2982 1.0000
10.750 1.2420 0.03589 0.02928 0.0115 0.2893 1.0000
11.000 1.2483 0.03611 0.02965 0.0146 0.2799 1.0000
11.250 1.2489 0.03664 0.03033 0.0184 0.2712 1.0000
11.500 1.2689 0.03577 0.02945 0.0203 0.2612 1.0000
11.750 1.2741 0.03566 0.02941 0.0238 0.2517 1.0000
12.000 1.2645 0.03642 0.03031 0.0287 0.2435 1.0000
12.250 1.2730 0.03613 0.02995 0.0319 0.2335 1.0000
12.500 1.2504 0.03718 0.03111 0.0384 0.2273 1.0000
12.750 1.2460 0.03754 0.03141 0.0426 0.2186 1.0000
13.000 1.2326 0.03865 0.03256 0.0468 0.2107 1.0000
13.250 1.2191 0.04030 0.03425 0.0499 0.2030 1.0000
13.500 1.2200 0.04118 0.03502 0.0519 0.1925 1.0000
13.750 1.1972 0.04429 0.03830 0.0536 0.1859 1.0000
14.000 1.1925 0.04621 0.04017 0.0547 0.1766 1.0000
14.250 1.1946 0.04767 0.04150 0.0556 0.1660 1.0000
14.500 1.1702 0.05207 0.04612 0.0554 0.1604 1.0000
14.750 1.1693 0.05414 0.04811 0.0559 0.1508 1.0000
15.000 1.1546 0.05795 0.05202 0.0553 0.1440 1.0000
15.250 1.1476 0.06104 0.05511 0.0551 0.1365 1.0000
15.500 1.1542 0.06251 0.05641 0.0557 0.1265 1.0000
15.750 1.1283 0.06827 0.06243 0.0538 0.1232 1.0000
16.000 0.7305 0.15038 0.14442 0.0141 0.1492 1.0000
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Polar data table (+)
Polar graphs
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