EPPLER 1230 AIRFOIL (e1230-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1230 AIRFOIL (e1230-il) Reynolds number: 50,000 Max Cl/Cd: 16.72 at α=0.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1230-il-50000.txt Download as CSV file: xf-e1230-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1230 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2744 0.10889 0.10265 -0.0228 1.0000 0.3294
-8.750 -0.2679 0.10636 0.10019 -0.0212 1.0000 0.3446
-8.500 -0.3557 0.09090 0.08496 -0.0362 1.0000 0.1895
-8.250 -0.5173 0.07912 0.07336 -0.0409 1.0000 0.1449
-8.000 -0.5256 0.07630 0.07058 -0.0382 1.0000 0.1418
-7.750 -0.5425 0.07369 0.06803 -0.0353 1.0000 0.1399
-7.500 -0.6105 0.06830 0.06201 -0.0322 1.0000 0.1279
-7.250 -0.6165 0.06541 0.05906 -0.0301 1.0000 0.1273
-7.000 -0.6229 0.06252 0.05603 -0.0281 1.0000 0.1269
-6.750 -0.6270 0.05956 0.05284 -0.0264 1.0000 0.1266
-6.500 -0.6278 0.05661 0.04957 -0.0250 1.0000 0.1266
-6.250 -0.6248 0.05372 0.04629 -0.0237 1.0000 0.1268
-6.000 -0.5899 0.04954 0.04136 -0.0277 0.9903 0.1283
-5.750 -0.5416 0.04670 0.03853 -0.0330 0.9775 0.1374
-5.500 -0.5009 0.04355 0.03469 -0.0366 0.9636 0.1460
-5.250 -0.4562 0.04142 0.03220 -0.0403 0.9493 0.1611
-5.000 -0.4120 0.03929 0.03008 -0.0438 0.9356 0.1818
-4.750 -0.3688 0.03763 0.02841 -0.0468 0.9214 0.2100
-4.500 -0.3275 0.03607 0.02698 -0.0492 0.9071 0.2437
-4.250 -0.2885 0.03471 0.02578 -0.0511 0.8929 0.2852
-4.000 -0.2491 0.03323 0.02469 -0.0530 0.8795 0.3449
-3.750 -0.2103 0.03156 0.02437 -0.0533 0.8681 0.4813
-3.500 -0.1992 0.03296 0.02640 -0.0462 0.8525 0.6297
-3.250 -0.1856 0.03398 0.02738 -0.0399 0.8380 0.7106
-3.000 -0.1533 0.03462 0.02788 -0.0354 0.8268 0.7723
-2.750 -0.1041 0.03539 0.02843 -0.0338 0.8147 0.8233
-2.500 0.1904 0.03536 0.02730 -0.0688 0.8073 0.9137
-2.250 0.3163 0.03356 0.02501 -0.0850 0.7922 0.9513
-2.000 0.3850 0.03257 0.02373 -0.0931 0.7742 0.9737
-1.750 0.4436 0.03182 0.02274 -0.0998 0.7567 0.9917
-1.500 0.4822 0.03153 0.02228 -0.1032 0.7406 1.0000
-1.250 0.4982 0.03172 0.02234 -0.1022 0.7274 1.0000
-1.000 0.5163 0.03181 0.02229 -0.1013 0.7153 1.0000
-0.750 0.5263 0.03246 0.02289 -0.0998 0.7019 1.0000
-0.500 0.5434 0.03270 0.02299 -0.0987 0.6915 1.0000
-0.250 0.5540 0.03332 0.02357 -0.0971 0.6796 1.0000
0.000 0.5647 0.03401 0.02422 -0.0954 0.6693 1.0000
0.250 0.5774 0.03454 0.02467 -0.0939 0.6592 1.0000
0.500 0.5829 0.03552 0.02564 -0.0916 0.6494 1.0000
0.750 0.5924 0.03622 0.02629 -0.0897 0.6402 1.0000
1.000 0.5976 0.03721 0.02725 -0.0873 0.6319 1.0000
1.250 0.5890 0.03880 0.02889 -0.0834 0.6228 1.0000
1.500 0.6165 0.03864 0.02857 -0.0831 0.6168 1.0000
1.750 0.5562 0.04235 0.03249 -0.0739 0.6072 1.0000
2.000 0.5546 0.04322 0.03332 -0.0704 0.6006 1.0000
2.250 0.5209 0.04518 0.03528 -0.0635 0.5949 1.0000
2.500 0.3778 0.05196 0.04209 -0.0483 0.5887 1.0000
2.750 0.3815 0.05408 0.04412 -0.0474 0.5830 1.0000
3.000 0.4378 0.05339 0.04327 -0.0491 0.5772 1.0000
3.250 0.3789 0.05954 0.04941 -0.0459 0.5730 1.0000
3.500 0.3687 0.06305 0.05287 -0.0453 0.5712 1.0000
3.750 0.3647 0.06628 0.05606 -0.0451 0.5706 1.0000
4.000 0.3634 0.06941 0.05914 -0.0451 0.5708 1.0000
4.250 0.3659 0.07253 0.06221 -0.0455 0.5728 1.0000
4.500 0.3832 0.07551 0.06514 -0.0467 0.5766 1.0000
4.750 0.2680 0.08502 0.07495 -0.0483 0.6979 1.0000
5.000 0.2810 0.08733 0.07719 -0.0484 0.6905 1.0000
5.250 0.2972 0.08912 0.07892 -0.0485 0.6788 1.0000
5.500 0.3356 0.09349 0.08319 -0.0516 0.6745 1.0000
5.750 0.3202 0.09316 0.08285 -0.0482 0.6615 1.0000
6.000 0.3623 0.09755 0.08717 -0.0514 0.6556 1.0000
6.250 0.3472 0.09744 0.08703 -0.0483 0.6427 1.0000
6.500 0.3853 0.10151 0.09104 -0.0509 0.6366 1.0000
6.750 0.3711 0.10185 0.09137 -0.0483 0.6262 1.0000
7.000 0.3990 0.10497 0.09446 -0.0497 0.6189 1.0000
7.250 0.3988 0.10669 0.09615 -0.0487 0.6109 1.0000
7.500 0.4186 0.10909 0.09852 -0.0492 0.6009 1.0000
7.750 0.4458 0.11320 0.10260 -0.0508 0.5963 1.0000
8.000 0.4357 0.11332 0.10272 -0.0488 0.5844 1.0000
8.250 0.4684 0.11741 0.10680 -0.0507 0.5791 1.0000
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Polar data table (+)
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