E231 (e231-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E231 (e231-il) Reynolds number: 100,000 Max Cl/Cd: 51.1 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e231-il-100000-n5.txt Download as CSV file: xf-e231-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E231
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2972 0.11045 0.10596 -0.0456 1.0000 0.0212
-11.000 -0.3673 0.10980 0.10481 -0.0483 1.0000 0.0210
-10.750 -0.3657 0.10667 0.10173 -0.0488 1.0000 0.0204
-10.500 -0.3672 0.10325 0.09838 -0.0494 1.0000 0.0198
-10.250 -0.3721 0.09980 0.09502 -0.0498 1.0000 0.0194
-10.000 -0.3807 0.09686 0.09216 -0.0494 1.0000 0.0187
-9.750 -0.3944 0.09440 0.08980 -0.0480 1.0000 0.0183
-9.500 -0.4035 0.09001 0.08546 -0.0497 0.9968 0.0177
-9.000 -0.4123 0.07061 0.06594 -0.0695 0.9807 0.0155
-8.750 -0.4153 0.06594 0.06117 -0.0733 0.9732 0.0153
-8.500 -0.4200 0.06184 0.05692 -0.0752 0.9651 0.0151
-8.250 -0.4214 0.05746 0.05234 -0.0766 0.9581 0.0149
-8.000 -0.4227 0.05409 0.04876 -0.0761 0.9505 0.0147
-7.750 -0.4200 0.05022 0.04458 -0.0758 0.9445 0.0146
-7.500 -0.4193 0.04697 0.04102 -0.0740 0.9376 0.0145
-7.250 -0.4136 0.04367 0.03734 -0.0723 0.9319 0.0144
-7.000 -0.4035 0.04051 0.03375 -0.0709 0.9273 0.0143
-6.750 -0.3972 0.03805 0.03089 -0.0680 0.9207 0.0146
-6.500 -0.3811 0.03542 0.02759 -0.0662 0.9166 0.0156
-6.250 -0.3642 0.03333 0.02512 -0.0647 0.9125 0.0157
-6.000 -0.3516 0.03199 0.02369 -0.0631 0.9070 0.0175
-5.750 -0.3290 0.03028 0.02166 -0.0623 0.9036 0.0186
-5.500 -0.3014 0.02827 0.01927 -0.0621 0.9012 0.0194
-5.250 -0.2826 0.02701 0.01779 -0.0604 0.8964 0.0199
-5.000 -0.2596 0.02566 0.01623 -0.0593 0.8924 0.0209
-4.750 -0.2337 0.02449 0.01491 -0.0588 0.8894 0.0221
-4.500 -0.2086 0.02338 0.01375 -0.0586 0.8869 0.0254
-4.250 -0.1945 0.02296 0.01320 -0.0560 0.8810 0.0303
-4.000 -0.1756 0.02207 0.01229 -0.0545 0.8767 0.0363
-3.750 -0.1514 0.02127 0.01146 -0.0537 0.8738 0.0535
-3.500 -0.1365 0.02042 0.01091 -0.0515 0.8689 0.0993
-3.250 -0.1231 0.01935 0.01060 -0.0494 0.8638 0.2465
-3.000 -0.1106 0.01786 0.01040 -0.0467 0.8603 0.5264
-2.750 -0.0453 0.01813 0.01154 -0.0507 0.8615 0.8218
-2.500 -0.0162 0.01857 0.01178 -0.0498 0.8590 0.8668
-2.250 0.0242 0.01906 0.01203 -0.0513 0.8565 0.8939
-2.000 0.0606 0.01945 0.01223 -0.0526 0.8526 0.9144
-1.750 0.1122 0.01964 0.01221 -0.0570 0.8507 0.9286
-1.500 0.1652 0.01968 0.01204 -0.0620 0.8490 0.9389
-1.250 0.2111 0.01962 0.01183 -0.0657 0.8468 0.9478
-1.000 0.2498 0.01955 0.01163 -0.0679 0.8444 0.9568
-0.750 0.2890 0.01955 0.01154 -0.0707 0.8395 0.9636
-0.500 0.3222 0.01953 0.01144 -0.0722 0.8349 0.9710
-0.250 0.3634 0.01930 0.01114 -0.0751 0.8316 0.9757
0.000 0.3963 0.01925 0.01103 -0.0766 0.8268 0.9817
0.250 0.4305 0.01915 0.01089 -0.0783 0.8208 0.9864
0.500 0.4672 0.01890 0.01061 -0.0803 0.8168 0.9906
0.750 0.4981 0.01886 0.01057 -0.0814 0.8098 0.9953
1.000 0.5327 0.01863 0.01033 -0.0830 0.8042 0.9992
1.250 0.5547 0.01861 0.01031 -0.0821 0.7971 1.0000
1.500 0.5750 0.01853 0.01025 -0.0807 0.7897 1.0000
1.750 0.5928 0.01856 0.01029 -0.0790 0.7813 1.0000
2.000 0.6154 0.01838 0.01011 -0.0778 0.7744 1.0000
2.250 0.6315 0.01844 0.01021 -0.0758 0.7646 1.0000
2.500 0.6556 0.01819 0.00997 -0.0748 0.7579 1.0000
2.750 0.6720 0.01820 0.01007 -0.0727 0.7474 1.0000
3.000 0.6892 0.01818 0.01010 -0.0707 0.7370 1.0000
3.250 0.7097 0.01803 0.00998 -0.0691 0.7274 1.0000
3.500 0.7309 0.01783 0.00983 -0.0676 0.7173 1.0000
3.750 0.7473 0.01780 0.00989 -0.0654 0.7046 1.0000
4.000 0.7646 0.01772 0.00987 -0.0632 0.6911 1.0000
4.250 0.7825 0.01762 0.00983 -0.0612 0.6768 1.0000
4.500 0.8018 0.01748 0.00974 -0.0593 0.6612 1.0000
4.750 0.8174 0.01748 0.00983 -0.0569 0.6429 1.0000
5.000 0.8349 0.01742 0.00979 -0.0547 0.6228 1.0000
5.250 0.8527 0.01737 0.00976 -0.0525 0.5998 1.0000
5.500 0.8705 0.01736 0.00972 -0.0503 0.5732 1.0000
5.750 0.8866 0.01744 0.00974 -0.0479 0.5427 1.0000
6.000 0.9009 0.01763 0.00985 -0.0452 0.5094 1.0000
6.250 0.9123 0.01794 0.01003 -0.0421 0.4756 1.0000
6.500 0.9207 0.01836 0.01032 -0.0385 0.4424 1.0000
6.750 0.9271 0.01883 0.01067 -0.0347 0.4113 1.0000
7.000 0.9318 0.01935 0.01107 -0.0307 0.3819 1.0000
7.250 0.9361 0.01989 0.01152 -0.0267 0.3551 1.0000
7.500 0.9388 0.02045 0.01200 -0.0224 0.3301 1.0000
7.750 0.9408 0.02102 0.01249 -0.0181 0.3071 1.0000
8.000 0.9450 0.02164 0.01304 -0.0144 0.2840 1.0000
8.250 0.9502 0.02235 0.01368 -0.0110 0.2616 1.0000
8.500 0.9575 0.02310 0.01438 -0.0082 0.2398 1.0000
8.750 0.9650 0.02393 0.01516 -0.0055 0.2198 1.0000
9.000 0.9739 0.02477 0.01599 -0.0031 0.2000 1.0000
9.250 0.9827 0.02568 0.01688 -0.0009 0.1824 1.0000
9.500 0.9906 0.02670 0.01790 0.0013 0.1655 1.0000
9.750 0.9998 0.02771 0.01891 0.0033 0.1497 1.0000
10.000 1.0087 0.02878 0.02001 0.0051 0.1354 1.0000
10.250 1.0171 0.02994 0.02118 0.0070 0.1225 1.0000
10.500 1.0245 0.03120 0.02244 0.0088 0.1113 1.0000
10.750 1.0329 0.03244 0.02377 0.0105 0.1002 1.0000
11.000 1.0407 0.03377 0.02518 0.0121 0.0898 1.0000
11.250 1.0472 0.03524 0.02669 0.0137 0.0813 1.0000
11.500 1.0515 0.03687 0.02834 0.0153 0.0737 1.0000
11.750 1.0588 0.03840 0.03007 0.0166 0.0661 1.0000
12.000 1.0612 0.04031 0.03200 0.0181 0.0602 1.0000
12.250 1.0667 0.04206 0.03391 0.0193 0.0535 1.0000
12.500 1.0672 0.04424 0.03612 0.0206 0.0487 1.0000
12.750 1.0707 0.04628 0.03835 0.0216 0.0429 1.0000
13.000 1.0679 0.04887 0.04097 0.0225 0.0392 1.0000
13.250 1.0702 0.05124 0.04355 0.0234 0.0355 1.0000
13.500 1.0690 0.05389 0.04634 0.0238 0.0319 1.0000
13.750 1.0633 0.05713 0.04962 0.0241 0.0297 1.0000
14.000 1.0623 0.06017 0.05290 0.0245 0.0273 1.0000
14.250 1.0585 0.06356 0.05648 0.0243 0.0248 1.0000
14.500 1.0535 0.06718 0.06023 0.0238 0.0234 1.0000
14.750 1.0448 0.07143 0.06455 0.0228 0.0220 1.0000
15.000 1.0387 0.07565 0.06897 0.0219 0.0209 1.0000
15.250 1.0319 0.08020 0.07376 0.0208 0.0200 1.0000
15.500 1.0227 0.08527 0.07906 0.0192 0.0192 1.0000
15.750 1.0119 0.09083 0.08482 0.0168 0.0182 1.0000
16.000 1.0008 0.09667 0.09088 0.0143 0.0178 1.0000
16.250 0.9893 0.10281 0.09721 0.0113 0.0176 1.0000
16.500 0.9759 0.10962 0.10418 0.0078 0.0172 1.0000
16.750 0.9625 0.11667 0.11136 0.0037 0.0166 1.0000
17.000 0.9451 0.12508 0.11994 -0.0008 0.0170 1.0000
17.250 0.9192 0.13617 0.13127 -0.0069 0.0180 1.0000
17.500 0.8921 0.14845 0.14368 -0.0137 0.0189 1.0000
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