E210 (13.64%) (e210-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E210 (13.64%) (e210-il) Reynolds number: 200,000 Max Cl/Cd: 78.69 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e210-il-200000.txt Download as CSV file: xf-e210-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E210 (13.64%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3676 0.09457 0.09145 -0.0404 1.0000 0.0655
-8.500 -0.3999 0.09123 0.08825 -0.0420 1.0000 0.0665
-8.250 -0.4292 0.08493 0.08203 -0.0500 0.9960 0.0668
-8.000 -0.4208 0.07709 0.07422 -0.0562 0.9904 0.0682
-7.750 -0.3877 0.07753 0.07463 -0.0513 0.9886 0.0700
-7.500 -0.3661 0.07315 0.07024 -0.0575 0.9830 0.0725
-7.250 -0.3958 0.04160 0.03718 -0.0919 0.9601 0.0463
-7.000 -0.3730 0.03594 0.03106 -0.0942 0.9519 0.0411
-6.750 -0.3402 0.03130 0.02580 -0.0978 0.9470 0.0408
-6.500 -0.3106 0.02835 0.02238 -0.0993 0.9394 0.0415
-6.250 -0.2745 0.02549 0.01906 -0.1015 0.9345 0.0417
-6.000 -0.2335 0.02331 0.01653 -0.1043 0.9317 0.0426
-5.750 -0.2037 0.02214 0.01510 -0.1046 0.9220 0.0443
-5.500 -0.1646 0.02004 0.01292 -0.1070 0.9188 0.0470
-5.250 -0.1333 0.01887 0.01172 -0.1076 0.9103 0.0493
-5.000 -0.0936 0.01768 0.01047 -0.1097 0.9059 0.0527
-4.750 -0.0573 0.01647 0.00925 -0.1114 0.8996 0.0583
-4.500 -0.0190 0.01553 0.00827 -0.1134 0.8924 0.0665
-4.250 0.0220 0.01411 0.00701 -0.1163 0.8862 0.0979
-4.000 0.0595 0.01293 0.00621 -0.1187 0.8765 0.1847
-3.750 0.0965 0.01206 0.00569 -0.1209 0.8654 0.2798
-3.500 0.1344 0.01143 0.00545 -0.1232 0.8539 0.4021
-3.250 0.1712 0.01132 0.00536 -0.1247 0.8407 0.4754
-3.000 0.2051 0.01130 0.00527 -0.1255 0.8261 0.5120
-2.750 0.2367 0.01133 0.00517 -0.1259 0.8110 0.5374
-2.500 0.2666 0.01137 0.00511 -0.1260 0.7960 0.5589
-2.250 0.2954 0.01145 0.00508 -0.1259 0.7817 0.5790
-2.000 0.3233 0.01152 0.00506 -0.1256 0.7678 0.5973
-1.750 0.3501 0.01159 0.00504 -0.1252 0.7542 0.6131
-1.500 0.3768 0.01166 0.00503 -0.1248 0.7415 0.6280
-1.250 0.4038 0.01173 0.00503 -0.1244 0.7299 0.6420
-1.000 0.4314 0.01181 0.00500 -0.1242 0.7194 0.6560
-0.750 0.4578 0.01187 0.00502 -0.1238 0.7085 0.6699
-0.500 0.4842 0.01195 0.00505 -0.1234 0.6984 0.6837
-0.250 0.5121 0.01204 0.00504 -0.1233 0.6896 0.6976
0.000 0.5376 0.01209 0.00510 -0.1227 0.6798 0.7109
0.250 0.5642 0.01217 0.00515 -0.1224 0.6715 0.7248
0.500 0.5903 0.01223 0.00520 -0.1219 0.6629 0.7395
0.750 0.6163 0.01230 0.00528 -0.1215 0.6548 0.7549
1.000 0.6423 0.01236 0.00534 -0.1210 0.6470 0.7714
1.250 0.6678 0.01244 0.00544 -0.1205 0.6396 0.7901
1.500 0.6922 0.01248 0.00552 -0.1196 0.6321 0.8100
1.750 0.7159 0.01255 0.00562 -0.1186 0.6253 0.8350
2.000 0.7372 0.01255 0.00571 -0.1170 0.6181 0.8662
2.250 0.7594 0.01255 0.00574 -0.1155 0.6121 0.9104
2.500 0.7978 0.01253 0.00577 -0.1178 0.6041 1.0000
2.750 0.8300 0.01278 0.00588 -0.1191 0.5981 1.0000
3.000 0.8569 0.01298 0.00609 -0.1193 0.5906 1.0000
3.250 0.8860 0.01320 0.00622 -0.1197 0.5843 1.0000
3.500 0.9128 0.01344 0.00647 -0.1197 0.5777 1.0000
3.750 0.9402 0.01366 0.00665 -0.1198 0.5710 1.0000
4.000 0.9682 0.01393 0.00687 -0.1199 0.5651 1.0000
4.250 0.9937 0.01415 0.00714 -0.1196 0.5581 1.0000
4.500 1.0226 0.01441 0.00732 -0.1199 0.5523 1.0000
4.750 1.0468 0.01465 0.00764 -0.1194 0.5451 1.0000
5.000 1.0741 0.01487 0.00784 -0.1193 0.5386 1.0000
5.250 1.0991 0.01513 0.00814 -0.1189 0.5316 1.0000
5.500 1.1250 0.01533 0.00835 -0.1186 0.5243 1.0000
5.750 1.1501 0.01557 0.00862 -0.1181 0.5170 1.0000
6.000 1.1750 0.01576 0.00884 -0.1176 0.5091 1.0000
6.250 1.1995 0.01599 0.00911 -0.1171 0.5016 1.0000
6.500 1.2239 0.01617 0.00932 -0.1165 0.4935 1.0000
6.750 1.2473 0.01639 0.00962 -0.1157 0.4854 1.0000
7.000 1.2715 0.01656 0.00979 -0.1150 0.4769 1.0000
7.250 1.2928 0.01676 0.01009 -0.1139 0.4677 1.0000
7.500 1.3169 0.01695 0.01026 -0.1132 0.4591 1.0000
7.750 1.3364 0.01712 0.01056 -0.1117 0.4488 1.0000
8.000 1.3568 0.01733 0.01084 -0.1103 0.4388 1.0000
8.250 1.3777 0.01753 0.01105 -0.1091 0.4285 1.0000
8.500 1.3952 0.01773 0.01134 -0.1072 0.4167 1.0000
8.750 1.4120 0.01797 0.01168 -0.1052 0.4043 1.0000
9.000 1.4277 0.01823 0.01201 -0.1031 0.3908 1.0000
9.250 1.4417 0.01853 0.01236 -0.1007 0.3761 1.0000
9.500 1.4529 0.01888 0.01275 -0.0978 0.3605 1.0000
9.750 1.4615 0.01931 0.01320 -0.0945 0.3435 1.0000
10.000 1.4683 0.01988 0.01375 -0.0910 0.3252 1.0000
10.250 1.4741 0.02055 0.01445 -0.0875 0.3029 1.0000
10.500 1.4765 0.02145 0.01529 -0.0838 0.2794 1.0000
10.750 1.4761 0.02260 0.01635 -0.0799 0.2536 1.0000
11.000 1.4738 0.02399 0.01766 -0.0761 0.2278 1.0000
11.250 1.4693 0.02565 0.01922 -0.0724 0.2043 1.0000
11.500 1.4632 0.02759 0.02107 -0.0690 0.1830 1.0000
11.750 1.4573 0.02972 0.02313 -0.0660 0.1642 1.0000
12.000 1.4516 0.03202 0.02539 -0.0634 0.1467 1.0000
12.250 1.4456 0.03455 0.02788 -0.0613 0.1316 1.0000
12.500 1.4397 0.03726 0.03057 -0.0595 0.1184 1.0000
12.750 1.4340 0.04013 0.03345 -0.0581 0.1068 1.0000
13.000 1.4274 0.04326 0.03657 -0.0570 0.0973 1.0000
13.250 1.4217 0.04647 0.03979 -0.0562 0.0882 1.0000
13.500 1.4185 0.04956 0.04294 -0.0556 0.0800 1.0000
13.750 1.4101 0.05331 0.04668 -0.0553 0.0738 1.0000
14.000 1.4079 0.05654 0.05000 -0.0551 0.0669 1.0000
14.250 1.4005 0.06043 0.05392 -0.0551 0.0615 1.0000
14.500 1.3973 0.06398 0.05755 -0.0553 0.0558 1.0000
14.750 1.3888 0.06826 0.06184 -0.0556 0.0513 1.0000
15.000 1.3860 0.07196 0.06566 -0.0561 0.0461 1.0000
15.250 1.3760 0.07664 0.07032 -0.0568 0.0423 1.0000
15.500 1.3733 0.08055 0.07437 -0.0574 0.0381 1.0000
15.750 1.3648 0.08524 0.07906 -0.0584 0.0350 1.0000
16.000 1.3609 0.08936 0.08330 -0.0591 0.0319 1.0000
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Polar data table (+)
Polar graphs
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