EPPLER 327 AIRFOIL (e327-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 327 AIRFOIL (e327-il) Reynolds number: 100,000 Max Cl/Cd: 38.78 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e327-il-100000.txt Download as CSV file: xf-e327-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 327 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 -0.4358 0.11482 0.10998 -0.0151 1.0000 0.0836
-10.250 -0.4557 0.11115 0.10640 -0.0216 1.0000 0.0849
-10.000 -0.4744 0.10671 0.10203 -0.0278 1.0000 0.0852
-9.750 -0.4362 0.10248 0.09780 -0.0199 1.0000 0.0883
-9.500 -0.4288 0.09914 0.09449 -0.0197 1.0000 0.0913
-9.250 -0.4317 0.09519 0.09061 -0.0217 1.0000 0.0947
-9.000 -0.4442 0.09066 0.08614 -0.0262 1.0000 0.0970
-8.750 -0.4750 0.08649 0.08201 -0.0301 1.0000 0.0984
-8.500 -0.5046 0.08437 0.07986 -0.0289 1.0000 0.0990
-8.250 -0.5369 0.08323 0.07856 -0.0265 1.0000 0.0996
-8.000 -0.4995 0.07579 0.07139 -0.0272 1.0000 0.1033
-7.750 -0.4973 0.07286 0.06849 -0.0257 1.0000 0.1066
-7.500 -0.5081 0.07023 0.06583 -0.0239 1.0000 0.1107
-7.000 -0.5273 0.06439 0.05987 -0.0190 1.0000 0.1181
-6.750 -0.5217 0.06172 0.05726 -0.0168 1.0000 0.1230
-6.250 -0.5371 0.05728 0.05272 -0.0099 1.0000 0.1343
-6.000 -0.5486 0.05600 0.05154 -0.0052 1.0000 0.1369
-5.750 -0.5357 0.05311 0.04848 -0.0063 0.9897 0.1502
-5.500 -0.4986 0.04913 0.04439 -0.0106 0.9742 0.1699
-4.750 -0.3607 0.03267 0.02505 -0.0157 0.9305 0.0577
-4.500 -0.3166 0.02943 0.02139 -0.0180 0.9147 0.0562
-4.250 -0.2730 0.02690 0.01844 -0.0199 0.8965 0.0562
-4.000 -0.2320 0.02476 0.01596 -0.0211 0.8755 0.0567
-3.750 -0.1919 0.02293 0.01384 -0.0219 0.8543 0.0586
-3.500 -0.1559 0.02123 0.01210 -0.0225 0.8341 0.0633
-3.250 -0.1289 0.02025 0.01108 -0.0216 0.8124 0.0732
-3.000 -0.1079 0.01918 0.01009 -0.0198 0.7929 0.0897
-2.750 0.2034 0.01934 0.01235 -0.0568 0.7627 1.0000
-2.500 0.2233 0.01923 0.01198 -0.0558 0.7425 1.0000
-2.250 0.2434 0.01914 0.01165 -0.0549 0.7245 1.0000
-2.000 0.2636 0.01907 0.01137 -0.0540 0.7081 1.0000
-1.750 0.2841 0.01902 0.01113 -0.0531 0.6928 1.0000
-1.500 0.3045 0.01899 0.01094 -0.0522 0.6785 1.0000
-1.250 0.3251 0.01899 0.01077 -0.0513 0.6651 1.0000
-1.000 0.3459 0.01900 0.01063 -0.0504 0.6532 1.0000
-0.750 0.3669 0.01903 0.01050 -0.0495 0.6419 1.0000
-0.500 0.3881 0.01908 0.01045 -0.0487 0.6300 1.0000
-0.250 0.4094 0.01915 0.01041 -0.0479 0.6196 1.0000
0.000 0.4310 0.01922 0.01036 -0.0470 0.6100 1.0000
0.250 0.4525 0.01934 0.01043 -0.0463 0.5997 1.0000
0.500 0.4742 0.01945 0.01041 -0.0454 0.5915 1.0000
0.750 0.4958 0.01958 0.01053 -0.0447 0.5816 1.0000
1.000 0.5177 0.01974 0.01061 -0.0439 0.5738 1.0000
1.250 0.5394 0.01991 0.01076 -0.0432 0.5650 1.0000
1.500 0.5612 0.02010 0.01089 -0.0424 0.5575 1.0000
1.750 0.5829 0.02030 0.01109 -0.0416 0.5492 1.0000
2.000 0.6049 0.02052 0.01125 -0.0408 0.5424 1.0000
2.250 0.6263 0.02077 0.01155 -0.0401 0.5341 1.0000
2.500 0.6487 0.02097 0.01165 -0.0393 0.5281 1.0000
2.750 0.6694 0.02131 0.01211 -0.0385 0.5198 1.0000
3.000 0.6918 0.02151 0.01223 -0.0376 0.5138 1.0000
3.250 0.7122 0.02191 0.01276 -0.0368 0.5060 1.0000
3.500 0.7341 0.02216 0.01299 -0.0360 0.4996 1.0000
3.750 0.7549 0.02255 0.01344 -0.0351 0.4929 1.0000
4.000 0.7757 0.02289 0.01384 -0.0342 0.4859 1.0000
4.250 0.7983 0.02315 0.01405 -0.0333 0.4806 1.0000
4.500 0.8166 0.02371 0.01481 -0.0323 0.4727 1.0000
4.750 0.8389 0.02392 0.01498 -0.0314 0.4669 1.0000
5.000 0.8571 0.02453 0.01576 -0.0302 0.4598 1.0000
5.250 0.8777 0.02486 0.01614 -0.0292 0.4533 1.0000
5.500 0.8980 0.02527 0.01659 -0.0281 0.4473 1.0000
5.750 0.9153 0.02585 0.01733 -0.0267 0.4398 1.0000
6.000 0.9386 0.02599 0.01742 -0.0258 0.4345 1.0000
6.250 0.9518 0.02684 0.01852 -0.0241 0.4263 1.0000
6.500 0.9735 0.02702 0.01870 -0.0230 0.4204 1.0000
6.750 0.9877 0.02778 0.01965 -0.0212 0.4128 1.0000
7.000 1.0073 0.02805 0.01997 -0.0199 0.4061 1.0000
7.250 1.0234 0.02860 0.02063 -0.0182 0.3990 1.0000
7.500 1.0399 0.02900 0.02114 -0.0165 0.3915 1.0000
7.750 1.0583 0.02934 0.02154 -0.0150 0.3847 1.0000
8.000 1.0714 0.02986 0.02222 -0.0129 0.3766 1.0000
8.250 1.0909 0.03003 0.02241 -0.0114 0.3697 1.0000
8.500 1.1021 0.03053 0.02308 -0.0090 0.3611 1.0000
8.750 1.1198 0.03071 0.02332 -0.0073 0.3537 1.0000
9.000 1.1325 0.03099 0.02372 -0.0049 0.3451 1.0000
9.250 1.1448 0.03132 0.02415 -0.0025 0.3370 1.0000
9.500 1.1637 0.03114 0.02398 -0.0007 0.3283 1.0000
9.750 1.1668 0.03177 0.02481 0.0029 0.3195 1.0000
10.000 1.1934 0.03117 0.02409 0.0038 0.3106 1.0000
10.250 1.1886 0.03186 0.02504 0.0085 0.3014 1.0000
10.500 1.1989 0.03189 0.02511 0.0115 0.2923 1.0000
10.750 1.2186 0.03142 0.02456 0.0133 0.2821 1.0000
11.000 1.2075 0.03219 0.02558 0.0189 0.2731 1.0000
11.250 1.2153 0.03224 0.02563 0.0220 0.2629 1.0000
11.500 1.2276 0.03211 0.02543 0.0245 0.2516 1.0000
11.750 1.2255 0.03265 0.02608 0.0285 0.2410 1.0000
12.000 1.2224 0.03337 0.02690 0.0323 0.2302 1.0000
12.250 1.2212 0.03397 0.02749 0.0359 0.2197 1.0000
12.500 1.2223 0.03462 0.02809 0.0388 0.2085 1.0000
12.750 1.2168 0.03580 0.02931 0.0417 0.1979 1.0000
13.000 1.2068 0.03764 0.03125 0.0441 0.1882 1.0000
13.250 1.2022 0.03942 0.03303 0.0457 0.1781 1.0000
13.500 1.2012 0.04114 0.03465 0.0468 0.1675 1.0000
13.750 1.1900 0.04386 0.03749 0.0475 0.1588 1.0000
14.000 1.1822 0.04663 0.04031 0.0478 0.1502 1.0000
14.250 1.1825 0.04879 0.04236 0.0482 0.1406 1.0000
14.500 1.1694 0.05240 0.04612 0.0478 0.1336 1.0000
14.750 1.1662 0.05521 0.04892 0.0477 0.1258 1.0000
15.000 1.1617 0.05816 0.05187 0.0473 0.1183 1.0000
15.250 1.1532 0.06187 0.05569 0.0466 0.1125 1.0000
15.500 1.1530 0.06453 0.05831 0.0463 0.1053 1.0000
15.750 1.1419 0.06879 0.06273 0.0452 0.1007 1.0000
16.000 1.1292 0.07337 0.06748 0.0436 0.0967 1.0000
16.250 1.1363 0.07548 0.06949 0.0437 0.0900 1.0000
16.500 1.1155 0.08149 0.07576 0.0411 0.0879 1.0000
16.750 1.0970 0.08750 0.08197 0.0383 0.0856 1.0000
17.000 1.1137 0.08834 0.08265 0.0393 0.0790 1.0000
17.250 1.0874 0.09577 0.09034 0.0354 0.0783 1.0000
17.500 1.0580 0.10426 0.09907 0.0310 0.0782 1.0000
17.750 1.0226 0.11440 0.10940 0.0254 0.0788 1.0000
18.000 0.9811 0.12654 0.12166 0.0187 0.0799 1.0000
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Polar data table (+)
Polar graphs
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