E212 (10.55%) (e212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E212 (10.55%) (e212-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.78 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e212-il-1000000.txt Download as CSV file: xf-e212-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E212 (10.55%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4035 0.08455 0.08306 -0.0362 1.0000 0.0159
-10.250 -0.4106 0.08019 0.07873 -0.0366 1.0000 0.0162
-10.000 -0.4298 0.07269 0.07125 -0.0382 1.0000 0.0162
-9.500 -0.6769 0.03073 0.02783 -0.0833 0.9899 0.0101
-9.250 -0.6569 0.02445 0.02086 -0.0883 0.9871 0.0097
-9.000 -0.6269 0.02229 0.01844 -0.0909 0.9859 0.0098
-8.750 -0.5956 0.02044 0.01636 -0.0932 0.9851 0.0099
-8.500 -0.5677 0.01909 0.01486 -0.0942 0.9831 0.0102
-8.250 -0.5410 0.01785 0.01346 -0.0948 0.9801 0.0103
-8.000 -0.5105 0.01672 0.01220 -0.0961 0.9783 0.0105
-7.750 -0.4784 0.01572 0.01109 -0.0976 0.9769 0.0106
-7.500 -0.4454 0.01479 0.01006 -0.0992 0.9757 0.0108
-7.250 -0.4115 0.01394 0.00912 -0.1010 0.9748 0.0110
-7.000 -0.3769 0.01316 0.00826 -0.1028 0.9740 0.0111
-6.750 -0.3416 0.01269 0.00774 -0.1046 0.9733 0.0114
-6.500 -0.3167 0.01169 0.00664 -0.1045 0.9690 0.0117
-6.250 -0.2851 0.01086 0.00573 -0.1056 0.9665 0.0123
-6.000 -0.2515 0.01033 0.00515 -0.1071 0.9649 0.0130
-5.750 -0.2168 0.00988 0.00466 -0.1086 0.9635 0.0137
-5.500 -0.1814 0.00948 0.00422 -0.1103 0.9624 0.0144
-5.250 -0.1456 0.00912 0.00382 -0.1121 0.9615 0.0151
-5.000 -0.1093 0.00869 0.00335 -0.1139 0.9607 0.0173
-4.750 -0.0843 0.00835 0.00302 -0.1132 0.9549 0.0222
-4.500 -0.0511 0.00765 0.00259 -0.1147 0.9524 0.0747
-4.250 -0.0160 0.00721 0.00231 -0.1165 0.9504 0.1149
-4.000 0.0202 0.00684 0.00208 -0.1184 0.9485 0.1521
-3.750 0.0520 0.00654 0.00189 -0.1193 0.9440 0.1864
-3.500 0.0835 0.00629 0.00173 -0.1201 0.9383 0.2162
-3.250 0.1205 0.00601 0.00156 -0.1222 0.9345 0.2547
-3.000 0.1520 0.00580 0.00144 -0.1230 0.9268 0.2896
-2.750 0.1873 0.00561 0.00132 -0.1246 0.9201 0.3235
-2.500 0.2182 0.00546 0.00124 -0.1252 0.9098 0.3539
-2.250 0.2497 0.00536 0.00116 -0.1259 0.8991 0.3790
-2.000 0.2801 0.00529 0.00110 -0.1264 0.8868 0.4014
-1.750 0.3094 0.00524 0.00105 -0.1266 0.8728 0.4235
-1.500 0.3378 0.00522 0.00102 -0.1266 0.8578 0.4451
-1.250 0.3656 0.00520 0.00100 -0.1265 0.8418 0.4671
-1.000 0.3931 0.00521 0.00099 -0.1263 0.8251 0.4885
-0.500 0.4473 0.00526 0.00101 -0.1257 0.7900 0.5298
-0.250 0.4740 0.00531 0.00103 -0.1254 0.7718 0.5502
0.000 0.5007 0.00536 0.00106 -0.1250 0.7530 0.5700
0.250 0.5272 0.00542 0.00110 -0.1247 0.7331 0.5896
0.500 0.5536 0.00550 0.00115 -0.1242 0.7127 0.6095
0.750 0.5799 0.00559 0.00120 -0.1238 0.6918 0.6293
1.000 0.6062 0.00568 0.00127 -0.1234 0.6699 0.6485
1.250 0.6323 0.00579 0.00134 -0.1230 0.6480 0.6680
1.500 0.6585 0.00590 0.00142 -0.1225 0.6250 0.6876
1.750 0.6844 0.00603 0.00152 -0.1221 0.6020 0.7073
2.000 0.7104 0.00616 0.00162 -0.1216 0.5780 0.7266
2.250 0.7363 0.00631 0.00173 -0.1212 0.5543 0.7460
2.500 0.7619 0.00648 0.00185 -0.1206 0.5291 0.7656
2.750 0.7876 0.00664 0.00198 -0.1201 0.5031 0.7849
3.000 0.8130 0.00682 0.00212 -0.1196 0.4777 0.8038
3.250 0.8381 0.00701 0.00227 -0.1190 0.4528 0.8229
3.500 0.8632 0.00721 0.00243 -0.1184 0.4275 0.8425
3.750 0.8876 0.00741 0.00259 -0.1176 0.4021 0.8623
4.000 0.9106 0.00769 0.00278 -0.1166 0.3680 0.8834
4.250 0.9320 0.00801 0.00298 -0.1153 0.3289 0.9069
4.500 0.9511 0.00823 0.00315 -0.1133 0.2992 0.9389
4.750 0.9739 0.00851 0.00332 -0.1123 0.2664 1.0000
5.000 0.9984 0.00895 0.00358 -0.1118 0.2317 1.0000
5.250 1.0229 0.00938 0.00385 -0.1113 0.2000 1.0000
5.500 1.0472 0.00982 0.00415 -0.1108 0.1700 1.0000
5.750 1.0712 0.01028 0.00446 -0.1102 0.1423 1.0000
6.000 1.0950 0.01075 0.00479 -0.1096 0.1173 1.0000
6.250 1.1185 0.01124 0.00516 -0.1089 0.0935 1.0000
6.500 1.1412 0.01180 0.00557 -0.1081 0.0690 1.0000
6.750 1.1631 0.01243 0.00604 -0.1071 0.0451 1.0000
7.000 1.1827 0.01329 0.00670 -0.1058 0.0177 1.0000
7.250 1.2050 0.01387 0.00725 -0.1048 0.0122 1.0000
7.500 1.2283 0.01432 0.00772 -0.1040 0.0110 1.0000
7.750 1.2507 0.01484 0.00827 -0.1031 0.0101 1.0000
8.000 1.2719 0.01549 0.00898 -0.1019 0.0094 1.0000
8.250 1.2942 0.01597 0.00951 -0.1010 0.0091 1.0000
8.500 1.3158 0.01651 0.01011 -0.1000 0.0089 1.0000
8.750 1.3365 0.01710 0.01076 -0.0988 0.0085 1.0000
9.000 1.3564 0.01774 0.01145 -0.0975 0.0083 1.0000
9.250 1.3754 0.01842 0.01219 -0.0960 0.0080 1.0000
9.500 1.3932 0.01915 0.01297 -0.0945 0.0077 1.0000
9.750 1.4092 0.01999 0.01388 -0.0926 0.0074 1.0000
10.000 1.4187 0.02111 0.01509 -0.0896 0.0071 1.0000
10.250 1.4219 0.02253 0.01663 -0.0857 0.0069 1.0000
10.500 1.4290 0.02371 0.01790 -0.0825 0.0069 1.0000
10.750 1.4405 0.02459 0.01886 -0.0801 0.0068 1.0000
11.000 1.4502 0.02561 0.01996 -0.0776 0.0067 1.0000
11.250 1.4589 0.02671 0.02115 -0.0750 0.0067 1.0000
11.500 1.4662 0.02797 0.02250 -0.0724 0.0066 1.0000
11.750 1.4725 0.02933 0.02396 -0.0699 0.0066 1.0000
12.000 1.4776 0.03084 0.02558 -0.0674 0.0065 1.0000
12.250 1.4821 0.03247 0.02731 -0.0651 0.0064 1.0000
12.500 1.4859 0.03422 0.02916 -0.0630 0.0064 1.0000
12.750 1.4883 0.03618 0.03124 -0.0610 0.0063 1.0000
13.000 1.4895 0.03834 0.03352 -0.0592 0.0063 1.0000
13.250 1.4900 0.04069 0.03599 -0.0576 0.0062 1.0000
13.500 1.4897 0.04323 0.03865 -0.0563 0.0062 1.0000
13.750 1.4879 0.04607 0.04162 -0.0553 0.0061 1.0000
14.000 1.4850 0.04918 0.04486 -0.0546 0.0061 1.0000
14.250 1.4817 0.05248 0.04829 -0.0543 0.0060 1.0000
14.500 1.4762 0.05627 0.05222 -0.0543 0.0060 1.0000
14.750 1.4703 0.06030 0.05640 -0.0548 0.0059 1.0000
15.000 1.4627 0.06478 0.06103 -0.0557 0.0059 1.0000
15.250 1.4543 0.06965 0.06604 -0.0571 0.0059 1.0000
15.500 1.4445 0.07502 0.07156 -0.0589 0.0058 1.0000
15.750 1.4338 0.08079 0.07748 -0.0613 0.0058 1.0000
16.000 1.4213 0.08715 0.08400 -0.0642 0.0058 1.0000
16.250 1.4085 0.09390 0.09089 -0.0675 0.0058 1.0000
16.500 1.3942 0.10119 0.09834 -0.0714 0.0058 1.0000
16.750 1.3784 0.10907 0.10639 -0.0758 0.0058 1.0000
17.000 1.3618 0.11746 0.11493 -0.0807 0.0058 1.0000
17.250 1.3438 0.12647 0.12410 -0.0862 0.0058 1.0000
17.500 1.3277 0.13530 0.13308 -0.0918 0.0058 1.0000
17.750 1.3084 0.14524 0.14319 -0.0982 0.0059 1.0000
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