E212 (10.55%) (e212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E212 (10.55%) (e212-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.98 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e212-il-1000000-n5.txt Download as CSV file: xf-e212-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7060 0.08252 0.08040 -0.0439 1.0000 0.0054
-13.000 -0.7308 0.07415 0.07194 -0.0482 1.0000 0.0054
-12.750 -0.7627 0.06514 0.06284 -0.0531 1.0000 0.0054
-12.500 -0.7862 0.05776 0.05536 -0.0572 1.0000 0.0054
-12.250 -0.8116 0.05039 0.04786 -0.0615 1.0000 0.0054
-12.000 -0.8438 0.04296 0.04028 -0.0656 1.0000 0.0053
-11.750 -0.8460 0.03637 0.03348 -0.0749 0.9975 0.0053
-11.500 -0.8277 0.03220 0.02910 -0.0838 0.9947 0.0054
-11.250 -0.8098 0.02958 0.02629 -0.0876 0.9917 0.0054
-11.000 -0.7923 0.02641 0.02286 -0.0912 0.9889 0.0055
-10.750 -0.7695 0.02399 0.02021 -0.0940 0.9871 0.0055
-10.500 -0.7439 0.02194 0.01796 -0.0965 0.9859 0.0056
-10.250 -0.7155 0.02051 0.01638 -0.0986 0.9850 0.0057
-10.000 -0.6940 0.01938 0.01514 -0.0987 0.9822 0.0058
-9.750 -0.6686 0.01842 0.01409 -0.0993 0.9797 0.0059
-9.500 -0.6406 0.01747 0.01304 -0.1004 0.9779 0.0060
-9.250 -0.6110 0.01666 0.01215 -0.1016 0.9765 0.0061
-9.000 -0.5806 0.01583 0.01121 -0.1030 0.9753 0.0062
-8.750 -0.5496 0.01505 0.01035 -0.1044 0.9744 0.0063
-8.500 -0.5177 0.01438 0.00960 -0.1059 0.9736 0.0065
-8.250 -0.4949 0.01384 0.00901 -0.1052 0.9697 0.0067
-8.000 -0.4670 0.01328 0.00838 -0.1056 0.9669 0.0069
-7.750 -0.4368 0.01269 0.00772 -0.1065 0.9650 0.0071
-7.500 -0.4054 0.01213 0.00710 -0.1077 0.9634 0.0074
-7.250 -0.3731 0.01161 0.00651 -0.1089 0.9621 0.0075
-7.000 -0.3402 0.01115 0.00599 -0.1102 0.9609 0.0077
-6.750 -0.3184 0.01077 0.00558 -0.1091 0.9545 0.0078
-6.500 -0.2881 0.01024 0.00498 -0.1098 0.9517 0.0081
-6.250 -0.2555 0.00973 0.00442 -0.1111 0.9496 0.0085
-6.000 -0.2207 0.00934 0.00400 -0.1128 0.9480 0.0088
-5.750 -0.1931 0.00904 0.00367 -0.1128 0.9422 0.0092
-5.500 -0.1584 0.00874 0.00333 -0.1143 0.9387 0.0097
-5.250 -0.1215 0.00846 0.00301 -0.1164 0.9355 0.0102
-5.000 -0.0876 0.00823 0.00275 -0.1177 0.9301 0.0108
-4.750 -0.0527 0.00796 0.00245 -0.1193 0.9235 0.0124
-4.500 -0.0184 0.00774 0.00220 -0.1207 0.9159 0.0146
-4.250 0.0149 0.00736 0.00190 -0.1220 0.9062 0.0403
-4.000 0.0457 0.00708 0.00170 -0.1228 0.8943 0.0649
-3.750 0.0757 0.00686 0.00152 -0.1233 0.8811 0.0917
-3.500 0.1048 0.00666 0.00138 -0.1237 0.8669 0.1221
-3.250 0.1330 0.00649 0.00126 -0.1238 0.8517 0.1554
-3.000 0.1608 0.00637 0.00117 -0.1238 0.8361 0.1840
-2.750 0.1883 0.00629 0.00109 -0.1237 0.8201 0.2086
-2.500 0.2154 0.00616 0.00103 -0.1237 0.8033 0.2489
-2.250 0.2425 0.00609 0.00098 -0.1235 0.7863 0.2798
-2.000 0.2694 0.00608 0.00095 -0.1232 0.7681 0.3003
-1.750 0.2962 0.00609 0.00093 -0.1230 0.7492 0.3182
-1.500 0.3230 0.00611 0.00092 -0.1227 0.7297 0.3375
-1.250 0.3496 0.00614 0.00091 -0.1224 0.7103 0.3579
-1.000 0.3765 0.00617 0.00092 -0.1222 0.6908 0.3775
-0.750 0.4033 0.00621 0.00093 -0.1219 0.6708 0.3967
-0.500 0.4301 0.00626 0.00096 -0.1217 0.6511 0.4157
-0.250 0.4570 0.00632 0.00099 -0.1214 0.6316 0.4349
0.000 0.4839 0.00639 0.00102 -0.1212 0.6114 0.4536
0.250 0.5107 0.00647 0.00107 -0.1209 0.5906 0.4720
0.500 0.5375 0.00656 0.00113 -0.1207 0.5700 0.4900
0.750 0.5643 0.00666 0.00119 -0.1205 0.5477 0.5080
1.000 0.5909 0.00677 0.00127 -0.1202 0.5259 0.5257
1.250 0.6177 0.00688 0.00135 -0.1200 0.5037 0.5448
1.500 0.6442 0.00703 0.00144 -0.1197 0.4805 0.5634
1.750 0.6710 0.00715 0.00154 -0.1195 0.4583 0.5824
2.000 0.6974 0.00731 0.00165 -0.1192 0.4360 0.6009
2.250 0.7240 0.00745 0.00177 -0.1190 0.4132 0.6197
2.500 0.7502 0.00764 0.00191 -0.1186 0.3890 0.6387
2.750 0.7764 0.00783 0.00205 -0.1183 0.3636 0.6571
3.000 0.8025 0.00803 0.00220 -0.1180 0.3402 0.6754
3.250 0.8284 0.00824 0.00237 -0.1176 0.3165 0.6935
3.500 0.8543 0.00846 0.00255 -0.1173 0.2930 0.7117
3.750 0.8792 0.00876 0.00276 -0.1168 0.2607 0.7302
4.000 0.9032 0.00916 0.00301 -0.1161 0.2218 0.7488
4.250 0.9272 0.00954 0.00328 -0.1155 0.1864 0.7677
4.500 0.9515 0.00989 0.00355 -0.1148 0.1582 0.7867
4.750 0.9755 0.01026 0.00383 -0.1141 0.1313 0.8061
5.000 0.9993 0.01061 0.00412 -0.1134 0.1080 0.8261
5.250 1.0227 0.01099 0.00444 -0.1126 0.0870 0.8465
5.500 1.0458 0.01131 0.00474 -0.1117 0.0697 0.8683
5.750 1.0672 0.01172 0.00509 -0.1105 0.0504 0.8930
6.000 1.0870 0.01204 0.00541 -0.1088 0.0372 0.9244
6.250 1.1070 0.01236 0.00572 -0.1072 0.0256 1.0000
6.500 1.1290 0.01300 0.00625 -0.1063 0.0099 1.0000
6.750 1.1535 0.01337 0.00662 -0.1057 0.0083 1.0000
7.000 1.1777 0.01375 0.00702 -0.1051 0.0074 1.0000
7.250 1.2015 0.01416 0.00746 -0.1044 0.0067 1.0000
7.500 1.2254 0.01453 0.00786 -0.1037 0.0065 1.0000
7.750 1.2490 0.01492 0.00828 -0.1030 0.0063 1.0000
8.000 1.2721 0.01535 0.00874 -0.1023 0.0060 1.0000
8.250 1.2948 0.01579 0.00923 -0.1014 0.0058 1.0000
8.500 1.3170 0.01627 0.00974 -0.1005 0.0056 1.0000
8.750 1.3387 0.01677 0.01028 -0.0995 0.0054 1.0000
9.000 1.3596 0.01732 0.01087 -0.0984 0.0052 1.0000
9.250 1.3797 0.01791 0.01151 -0.0972 0.0051 1.0000
9.500 1.3985 0.01859 0.01225 -0.0958 0.0049 1.0000
9.750 1.4151 0.01943 0.01316 -0.0940 0.0047 1.0000
10.000 1.4321 0.02014 0.01394 -0.0923 0.0046 1.0000
10.250 1.4486 0.02073 0.01458 -0.0905 0.0045 1.0000
10.500 1.4636 0.02136 0.01528 -0.0885 0.0044 1.0000
10.750 1.4777 0.02205 0.01603 -0.0863 0.0043 1.0000
11.000 1.4905 0.02280 0.01685 -0.0841 0.0043 1.0000
11.250 1.5023 0.02363 0.01776 -0.0817 0.0042 1.0000
11.500 1.5130 0.02453 0.01874 -0.0793 0.0041 1.0000
11.750 1.5228 0.02551 0.01980 -0.0769 0.0040 1.0000
12.000 1.5315 0.02658 0.02096 -0.0744 0.0040 1.0000
12.250 1.5392 0.02774 0.02220 -0.0720 0.0039 1.0000
12.500 1.5460 0.02901 0.02357 -0.0697 0.0038 1.0000
12.750 1.5519 0.03039 0.02504 -0.0674 0.0038 1.0000
13.000 1.5566 0.03191 0.02667 -0.0652 0.0037 1.0000
13.250 1.5600 0.03361 0.02847 -0.0631 0.0037 1.0000
13.500 1.5629 0.03546 0.03041 -0.0613 0.0036 1.0000
13.750 1.5643 0.03752 0.03258 -0.0596 0.0036 1.0000
14.000 1.5654 0.03973 0.03489 -0.0582 0.0036 1.0000
14.250 1.5643 0.04230 0.03758 -0.0571 0.0035 1.0000
14.500 1.5630 0.04504 0.04043 -0.0563 0.0035 1.0000
14.750 1.5601 0.04815 0.04366 -0.0558 0.0035 1.0000
15.000 1.5558 0.05161 0.04724 -0.0557 0.0034 1.0000
15.250 1.5508 0.05539 0.05114 -0.0560 0.0034 1.0000
15.500 1.5440 0.05965 0.05553 -0.0568 0.0034 1.0000
15.750 1.5355 0.06444 0.06045 -0.0581 0.0034 1.0000
16.000 1.5261 0.06963 0.06577 -0.0598 0.0034 1.0000
16.250 1.5155 0.07529 0.07157 -0.0620 0.0033 1.0000
16.500 1.5027 0.08165 0.07807 -0.0648 0.0033 1.0000
16.750 1.4886 0.08850 0.08507 -0.0681 0.0033 1.0000
17.000 1.4732 0.09587 0.09259 -0.0718 0.0033 1.0000
17.250 1.4572 0.10364 0.10050 -0.0758 0.0033 1.0000
17.500 1.4410 0.11163 0.10863 -0.0802 0.0033 1.0000
17.750 1.4234 0.12011 0.11725 -0.0849 0.0033 1.0000
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Polar data table (+)
Polar graphs
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