E212 (10.55%) (e212-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E212 (10.55%) (e212-il) Reynolds number: 500,000 Max Cl/Cd: 91.75 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e212-il-500000-n5.txt Download as CSV file: xf-e212-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5991 0.08555 0.08299 -0.0415 1.0000 0.0077
-11.750 -0.6371 0.07409 0.07146 -0.0474 1.0000 0.0076
-11.500 -0.6689 0.06425 0.06150 -0.0531 1.0000 0.0076
-11.250 -0.6930 0.05665 0.05379 -0.0577 1.0000 0.0076
-11.000 -0.7163 0.05001 0.04703 -0.0617 1.0000 0.0076
-10.750 -0.7389 0.04504 0.04198 -0.0638 1.0000 0.0075
-10.500 -0.7610 0.04090 0.03772 -0.0657 0.9992 0.0075
-10.250 -0.7426 0.03505 0.03145 -0.0765 0.9949 0.0076
-10.000 -0.7247 0.03168 0.02775 -0.0804 0.9916 0.0076
-9.750 -0.7017 0.02915 0.02491 -0.0834 0.9887 0.0077
-9.500 -0.6756 0.02698 0.02246 -0.0860 0.9867 0.0078
-9.250 -0.6479 0.02480 0.02001 -0.0886 0.9851 0.0079
-9.000 -0.6255 0.02269 0.01767 -0.0897 0.9821 0.0081
-8.750 -0.5997 0.02119 0.01602 -0.0908 0.9793 0.0083
-8.500 -0.5709 0.02007 0.01481 -0.0922 0.9772 0.0086
-8.250 -0.5404 0.01905 0.01367 -0.0937 0.9755 0.0089
-8.000 -0.5090 0.01800 0.01250 -0.0953 0.9742 0.0091
-7.750 -0.4786 0.01704 0.01141 -0.0965 0.9725 0.0092
-7.500 -0.4541 0.01620 0.01048 -0.0964 0.9681 0.0095
-7.250 -0.4239 0.01540 0.00959 -0.0974 0.9656 0.0097
-7.000 -0.3920 0.01466 0.00876 -0.0988 0.9637 0.0100
-6.750 -0.3590 0.01399 0.00799 -0.1003 0.9622 0.0103
-6.500 -0.3251 0.01338 0.00731 -0.1019 0.9609 0.0106
-6.250 -0.3010 0.01287 0.00674 -0.1013 0.9551 0.0109
-6.000 -0.2693 0.01220 0.00600 -0.1025 0.9523 0.0114
-5.750 -0.2361 0.01168 0.00542 -0.1038 0.9502 0.0120
-5.500 -0.2023 0.01126 0.00495 -0.1052 0.9485 0.0131
-5.250 -0.1754 0.01092 0.00456 -0.1051 0.9431 0.0140
-5.000 -0.1445 0.01055 0.00413 -0.1058 0.9393 0.0152
-4.750 -0.1108 0.01016 0.00373 -0.1071 0.9366 0.0180
-4.500 -0.0749 0.00964 0.00332 -0.1090 0.9345 0.0396
-4.250 -0.0461 0.00923 0.00302 -0.1094 0.9280 0.0697
-4.000 -0.0110 0.00880 0.00275 -0.1112 0.9239 0.1058
-3.750 0.0268 0.00841 0.00250 -0.1135 0.9205 0.1459
-3.500 0.0589 0.00813 0.00231 -0.1145 0.9135 0.1781
-3.250 0.0951 0.00785 0.00212 -0.1164 0.9074 0.2139
-3.000 0.1290 0.00758 0.00197 -0.1178 0.8992 0.2575
-2.750 0.1648 0.00735 0.00182 -0.1196 0.8906 0.2948
-2.500 0.1968 0.00722 0.00171 -0.1204 0.8790 0.3196
-2.250 0.2285 0.00711 0.00162 -0.1212 0.8668 0.3418
-2.000 0.2593 0.00703 0.00154 -0.1217 0.8534 0.3651
-1.750 0.2892 0.00697 0.00148 -0.1221 0.8390 0.3873
-1.500 0.3182 0.00693 0.00143 -0.1222 0.8234 0.4102
-1.250 0.3465 0.00692 0.00140 -0.1223 0.8067 0.4316
-1.000 0.3743 0.00692 0.00139 -0.1221 0.7891 0.4528
-0.750 0.4017 0.00695 0.00138 -0.1219 0.7708 0.4733
-0.500 0.4287 0.00698 0.00139 -0.1216 0.7520 0.4933
-0.250 0.4555 0.00703 0.00142 -0.1213 0.7324 0.5131
0.000 0.4820 0.00710 0.00145 -0.1209 0.7126 0.5327
0.250 0.5084 0.00718 0.00149 -0.1205 0.6929 0.5522
0.500 0.5348 0.00725 0.00155 -0.1201 0.6728 0.5717
0.750 0.5609 0.00735 0.00162 -0.1197 0.6519 0.5913
1.000 0.5870 0.00745 0.00170 -0.1192 0.6310 0.6112
1.500 0.6386 0.00770 0.00189 -0.1183 0.5862 0.6504
1.750 0.6643 0.00784 0.00200 -0.1178 0.5633 0.6699
2.000 0.6898 0.00800 0.00212 -0.1172 0.5401 0.6895
2.250 0.7153 0.00816 0.00226 -0.1167 0.5163 0.7088
2.750 0.7656 0.00853 0.00257 -0.1155 0.4680 0.7473
3.000 0.7905 0.00873 0.00273 -0.1149 0.4426 0.7669
3.250 0.8151 0.00896 0.00291 -0.1142 0.4172 0.7863
3.500 0.8392 0.00920 0.00312 -0.1134 0.3912 0.8060
3.750 0.8632 0.00943 0.00332 -0.1126 0.3659 0.8266
4.000 0.8866 0.00967 0.00353 -0.1116 0.3418 0.8475
4.250 0.9092 0.00991 0.00375 -0.1105 0.3187 0.8700
4.500 0.9296 0.01022 0.00398 -0.1089 0.2875 0.8956
4.750 0.9468 0.01057 0.00421 -0.1067 0.2492 0.9308
5.000 0.9692 0.01102 0.00447 -0.1058 0.2082 1.0000
5.250 0.9931 0.01151 0.00481 -0.1052 0.1760 1.0000
5.500 1.0172 0.01197 0.00515 -0.1047 0.1512 1.0000
6.000 1.0638 0.01302 0.00593 -0.1034 0.1000 1.0000
6.250 1.0864 0.01359 0.00637 -0.1026 0.0763 1.0000
6.500 1.1095 0.01410 0.00680 -0.1019 0.0599 1.0000
6.750 1.1314 0.01472 0.00730 -0.1010 0.0419 1.0000
7.000 1.1532 0.01534 0.00784 -0.1001 0.0274 1.0000
7.250 1.1737 0.01606 0.00848 -0.0989 0.0141 1.0000
7.500 1.1956 0.01663 0.00906 -0.0980 0.0113 1.0000
7.750 1.2172 0.01720 0.00966 -0.0970 0.0099 1.0000
8.000 1.2386 0.01778 0.01028 -0.0959 0.0091 1.0000
8.250 1.2599 0.01833 0.01090 -0.0949 0.0086 1.0000
8.500 1.2804 0.01891 0.01156 -0.0937 0.0082 1.0000
8.750 1.3002 0.01955 0.01226 -0.0925 0.0079 1.0000
9.000 1.3189 0.02024 0.01302 -0.0911 0.0075 1.0000
9.250 1.3364 0.02099 0.01384 -0.0895 0.0073 1.0000
9.500 1.3511 0.02182 0.01474 -0.0874 0.0071 1.0000
9.750 1.3628 0.02280 0.01582 -0.0849 0.0068 1.0000
10.000 1.3737 0.02380 0.01691 -0.0824 0.0067 1.0000
10.250 1.3858 0.02470 0.01789 -0.0801 0.0066 1.0000
10.500 1.3966 0.02568 0.01897 -0.0777 0.0065 1.0000
10.750 1.4065 0.02675 0.02013 -0.0753 0.0064 1.0000
11.000 1.4150 0.02792 0.02140 -0.0728 0.0063 1.0000
11.250 1.4226 0.02918 0.02277 -0.0704 0.0062 1.0000
11.500 1.4292 0.03055 0.02426 -0.0681 0.0061 1.0000
11.750 1.4352 0.03201 0.02584 -0.0658 0.0059 1.0000
12.000 1.4402 0.03362 0.02755 -0.0637 0.0058 1.0000
12.250 1.4445 0.03533 0.02937 -0.0618 0.0057 1.0000
12.500 1.4475 0.03726 0.03142 -0.0600 0.0056 1.0000
12.750 1.4499 0.03932 0.03360 -0.0584 0.0055 1.0000
13.000 1.4511 0.04162 0.03602 -0.0571 0.0054 1.0000
13.250 1.4509 0.04418 0.03870 -0.0560 0.0053 1.0000
13.500 1.4497 0.04699 0.04164 -0.0552 0.0053 1.0000
13.750 1.4475 0.05010 0.04488 -0.0548 0.0052 1.0000
14.000 1.4444 0.05346 0.04837 -0.0547 0.0052 1.0000
14.250 1.4398 0.05720 0.05227 -0.0549 0.0051 1.0000
14.500 1.4347 0.06122 0.05643 -0.0556 0.0051 1.0000
14.750 1.4282 0.06566 0.06101 -0.0566 0.0051 1.0000
15.000 1.4209 0.07045 0.06594 -0.0581 0.0050 1.0000
15.250 1.4128 0.07562 0.07126 -0.0600 0.0050 1.0000
15.500 1.4037 0.08117 0.07696 -0.0622 0.0050 1.0000
15.750 1.3935 0.08713 0.08307 -0.0649 0.0050 1.0000
16.000 1.3829 0.09342 0.08950 -0.0679 0.0049 1.0000
16.250 1.3717 0.10005 0.09628 -0.0713 0.0049 1.0000
16.500 1.3599 0.10696 0.10334 -0.0749 0.0049 1.0000
16.750 1.3479 0.11415 0.11068 -0.0789 0.0049 1.0000
17.000 1.3358 0.12154 0.11822 -0.0831 0.0049 1.0000
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