E230 (9.96%) (e230-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E230 (9.96%) (e230-il) Reynolds number: 500,000 Max Cl/Cd: 49.74 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e230-il-500000-n5.txt Download as CSV file: xf-e230-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E230 (9.96%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.9038 0.12856 0.12634 0.0473 1.0000 0.0054
-14.250 -0.9449 0.11181 0.10947 0.0379 1.0000 0.0053
-14.000 -0.9733 0.09949 0.09703 0.0305 1.0000 0.0052
-13.750 -0.9983 0.08861 0.08601 0.0236 1.0000 0.0050
-13.500 -1.0221 0.07839 0.07562 0.0166 1.0000 0.0051
-13.250 -1.0422 0.06979 0.06685 0.0106 1.0000 0.0050
-13.000 -1.0616 0.06218 0.05905 0.0055 1.0000 0.0050
-12.750 -1.0785 0.05595 0.05263 0.0018 1.0000 0.0050
-12.500 -1.0927 0.05097 0.04746 -0.0004 1.0000 0.0050
-12.250 -1.1060 0.04675 0.04304 -0.0012 1.0000 0.0050
-12.000 -1.1170 0.04332 0.03941 -0.0007 1.0000 0.0050
-11.750 -1.1250 0.04055 0.03643 0.0007 1.0000 0.0051
-11.500 -1.1316 0.03807 0.03375 0.0030 1.0000 0.0051
-11.250 -1.1356 0.03589 0.03137 0.0058 1.0000 0.0052
-11.000 -1.1361 0.03401 0.02929 0.0088 1.0000 0.0052
-10.750 -1.1326 0.03231 0.02739 0.0115 1.0000 0.0053
-10.500 -1.1242 0.03056 0.02543 0.0136 1.0000 0.0054
-10.250 -1.1130 0.02895 0.02362 0.0154 1.0000 0.0054
-10.000 -1.0989 0.02758 0.02207 0.0169 1.0000 0.0055
-9.750 -1.0838 0.02618 0.02050 0.0184 1.0000 0.0056
-9.500 -1.0668 0.02496 0.01913 0.0197 1.0000 0.0056
-9.250 -1.0481 0.02393 0.01795 0.0208 1.0000 0.0057
-9.000 -1.0322 0.02238 0.01626 0.0223 1.0000 0.0059
-8.750 -1.0152 0.02100 0.01477 0.0236 1.0000 0.0062
-8.500 -0.9958 0.01998 0.01368 0.0247 1.0000 0.0064
-8.250 -0.9755 0.01904 0.01266 0.0257 1.0000 0.0066
-8.000 -0.9545 0.01818 0.01172 0.0267 1.0000 0.0067
-7.750 -0.9329 0.01736 0.01083 0.0276 1.0000 0.0069
-7.500 -0.9108 0.01660 0.01000 0.0284 1.0000 0.0071
-7.250 -0.8881 0.01590 0.00921 0.0291 1.0000 0.0073
-7.000 -0.8648 0.01525 0.00849 0.0298 1.0000 0.0076
-6.750 -0.8409 0.01466 0.00784 0.0304 1.0000 0.0078
-6.500 -0.8165 0.01412 0.00724 0.0309 1.0000 0.0081
-6.250 -0.7915 0.01365 0.00671 0.0314 1.0000 0.0084
-6.000 -0.7667 0.01312 0.00611 0.0318 1.0000 0.0089
-5.750 -0.7415 0.01266 0.00560 0.0322 1.0000 0.0096
-5.500 -0.7097 0.01226 0.00516 0.0312 0.9675 0.0110
-5.250 -0.6821 0.01193 0.00477 0.0313 0.9491 0.0129
-5.000 -0.6592 0.01152 0.00438 0.0323 0.9326 0.0220
-4.750 -0.6381 0.01100 0.00399 0.0337 0.9173 0.0514
-4.500 -0.6160 0.01057 0.00368 0.0348 0.9034 0.0821
-4.250 -0.5932 0.01018 0.00340 0.0358 0.8898 0.1127
-4.000 -0.5698 0.00980 0.00313 0.0366 0.8766 0.1484
-3.750 -0.5466 0.00938 0.00288 0.0375 0.8633 0.1935
-3.500 -0.5226 0.00904 0.00267 0.0382 0.8502 0.2339
-3.250 -0.4987 0.00867 0.00246 0.0390 0.8369 0.2824
-3.000 -0.4744 0.00834 0.00228 0.0396 0.8234 0.3290
-2.750 -0.4492 0.00812 0.00212 0.0402 0.8097 0.3618
-2.500 -0.4236 0.00792 0.00198 0.0407 0.7959 0.3925
-2.250 -0.3981 0.00773 0.00184 0.0412 0.7818 0.4252
-2.000 -0.3724 0.00754 0.00172 0.0417 0.7673 0.4577
-1.750 -0.3467 0.00738 0.00161 0.0422 0.7522 0.4891
-1.500 -0.3209 0.00722 0.00151 0.0427 0.7368 0.5216
-1.250 -0.2951 0.00707 0.00143 0.0432 0.7208 0.5538
-1.000 -0.2694 0.00694 0.00136 0.0437 0.7041 0.5872
-0.750 -0.2438 0.00680 0.00129 0.0442 0.6872 0.6211
-0.500 -0.2182 0.00668 0.00124 0.0448 0.6699 0.6549
-0.250 -0.1926 0.00658 0.00120 0.0454 0.6521 0.6885
0.000 -0.1669 0.00649 0.00117 0.0460 0.6342 0.7207
0.250 -0.1411 0.00641 0.00116 0.0466 0.6157 0.7521
0.500 -0.1149 0.00635 0.00116 0.0471 0.5963 0.7825
0.750 -0.0884 0.00632 0.00117 0.0475 0.5762 0.8115
1.000 -0.0609 0.00632 0.00120 0.0478 0.5553 0.8390
1.250 -0.0319 0.00635 0.00125 0.0477 0.5324 0.8643
1.500 -0.0010 0.00642 0.00132 0.0472 0.5095 0.8870
1.750 0.0335 0.00655 0.00142 0.0459 0.4842 0.9050
2.000 0.0695 0.00671 0.00152 0.0442 0.4574 0.9190
2.250 0.1055 0.00690 0.00164 0.0424 0.4294 0.9301
2.500 0.1420 0.00712 0.00177 0.0406 0.3987 0.9376
2.750 0.1741 0.00732 0.00190 0.0397 0.3712 0.9462
3.000 0.2091 0.00755 0.00204 0.0381 0.3428 0.9512
3.250 0.2368 0.00785 0.00220 0.0381 0.3041 0.9594
3.500 0.2707 0.00829 0.00239 0.0365 0.2414 0.9630
3.750 0.3025 0.00862 0.00258 0.0355 0.2049 0.9677
4.000 0.3314 0.00896 0.00280 0.0350 0.1686 0.9731
4.250 0.3655 0.00942 0.00305 0.0334 0.1226 0.9759
4.500 0.3980 0.00981 0.00330 0.0321 0.0911 0.9794
4.750 0.4278 0.01025 0.00361 0.0314 0.0609 0.9835
5.000 0.4603 0.01073 0.00395 0.0301 0.0335 0.9858
5.250 0.4937 0.01122 0.00435 0.0286 0.0166 0.9879
5.500 0.5267 0.01157 0.00472 0.0273 0.0141 0.9902
5.750 0.5589 0.01194 0.00514 0.0262 0.0127 0.9927
6.000 0.5905 0.01239 0.00564 0.0251 0.0116 0.9949
6.250 0.6235 0.01287 0.00618 0.0238 0.0111 0.9966
6.500 0.6559 0.01331 0.00670 0.0225 0.0108 0.9983
6.750 0.6879 0.01383 0.00731 0.0213 0.0103 0.9999
7.000 0.7107 0.01437 0.00791 0.0220 0.0101 1.0000
7.250 0.7325 0.01496 0.00857 0.0229 0.0098 1.0000
7.500 0.7538 0.01560 0.00928 0.0238 0.0095 1.0000
7.750 0.7745 0.01630 0.01005 0.0248 0.0093 1.0000
8.000 0.7947 0.01704 0.01088 0.0258 0.0091 1.0000
8.250 0.8144 0.01779 0.01169 0.0269 0.0088 1.0000
8.500 0.8334 0.01861 0.01258 0.0280 0.0085 1.0000
8.750 0.8509 0.01962 0.01366 0.0293 0.0082 1.0000
9.000 0.8663 0.02094 0.01508 0.0308 0.0080 1.0000
9.250 0.8807 0.02238 0.01666 0.0324 0.0079 1.0000
9.500 0.8969 0.02341 0.01783 0.0338 0.0078 1.0000
9.750 0.9123 0.02447 0.01903 0.0353 0.0077 1.0000
10.000 0.9263 0.02564 0.02035 0.0369 0.0076 1.0000
10.250 0.9384 0.02695 0.02182 0.0386 0.0075 1.0000
10.500 0.9488 0.02832 0.02335 0.0404 0.0074 1.0000
10.750 0.9559 0.02992 0.02513 0.0424 0.0074 1.0000
11.000 0.9602 0.03158 0.02698 0.0445 0.0073 1.0000
11.250 0.9601 0.03330 0.02888 0.0470 0.0072 1.0000
11.500 0.9514 0.03509 0.03084 0.0501 0.0071 1.0000
11.750 0.9439 0.03736 0.03326 0.0517 0.0071 1.0000
12.000 0.9352 0.04029 0.03638 0.0520 0.0071 1.0000
12.250 0.9248 0.04397 0.04024 0.0510 0.0071 1.0000
12.500 0.9135 0.04835 0.04480 0.0487 0.0070 1.0000
12.750 0.9018 0.05337 0.04999 0.0456 0.0070 1.0000
13.000 0.8849 0.05987 0.05666 0.0411 0.0070 1.0000
13.250 0.8666 0.06720 0.06415 0.0359 0.0071 1.0000
13.500 0.8466 0.07533 0.07243 0.0304 0.0071 1.0000
13.750 0.8198 0.08533 0.08255 0.0241 0.0071 1.0000
14.000 0.7917 0.09587 0.09321 0.0181 0.0073 1.0000
14.250 0.7439 0.11214 0.10961 0.0097 0.0074 1.0000
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Polar data table (+)
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