E210 (13.64%) (e210-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E210 (13.64%) (e210-il) Reynolds number: 200,000 Max Cl/Cd: 79.58 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e210-il-200000-n5.txt Download as CSV file: xf-e210-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4058 0.08754 0.08416 -0.0478 1.0000 0.0182
-9.750 -0.4254 0.08144 0.07813 -0.0491 1.0000 0.0180
-9.500 -0.4930 0.05531 0.05180 -0.0734 0.9914 0.0171
-9.250 -0.5112 0.04491 0.04091 -0.0885 0.9772 0.0170
-9.000 -0.5069 0.03873 0.03417 -0.0942 0.9679 0.0173
-8.750 -0.4925 0.03421 0.02908 -0.0974 0.9603 0.0178
-8.500 -0.4761 0.03101 0.02536 -0.0984 0.9521 0.0184
-8.250 -0.4503 0.02849 0.02244 -0.1003 0.9468 0.0192
-8.000 -0.4281 0.02710 0.02097 -0.1006 0.9389 0.0200
-7.750 -0.3988 0.02568 0.01936 -0.1020 0.9336 0.0209
-7.500 -0.3748 0.02421 0.01767 -0.1021 0.9255 0.0216
-7.250 -0.3451 0.02272 0.01595 -0.1031 0.9198 0.0224
-7.000 -0.3194 0.02149 0.01453 -0.1031 0.9114 0.0232
-6.750 -0.2883 0.02032 0.01319 -0.1041 0.9054 0.0243
-6.500 -0.2604 0.01928 0.01211 -0.1047 0.8967 0.0256
-6.250 -0.2259 0.01832 0.01107 -0.1063 0.8904 0.0269
-6.000 -0.1944 0.01745 0.01011 -0.1073 0.8813 0.0280
-5.750 -0.1553 0.01658 0.00910 -0.1098 0.8746 0.0294
-5.500 -0.1200 0.01579 0.00822 -0.1117 0.8640 0.0314
-5.250 -0.0821 0.01513 0.00750 -0.1140 0.8533 0.0345
-5.000 -0.0430 0.01454 0.00676 -0.1164 0.8415 0.0378
-4.750 -0.0056 0.01393 0.00608 -0.1185 0.8279 0.0438
-4.500 0.0291 0.01343 0.00552 -0.1201 0.8128 0.0569
-4.250 0.0612 0.01297 0.00508 -0.1212 0.7969 0.0842
-4.000 0.0915 0.01259 0.00472 -0.1219 0.7808 0.1170
-3.750 0.1206 0.01229 0.00444 -0.1224 0.7652 0.1537
-3.500 0.1485 0.01191 0.00419 -0.1227 0.7501 0.2113
-3.250 0.1754 0.01149 0.00399 -0.1229 0.7357 0.2947
-3.000 0.2021 0.01122 0.00393 -0.1229 0.7223 0.3762
-2.750 0.2291 0.01118 0.00390 -0.1227 0.7091 0.4247
-2.500 0.2561 0.01120 0.00385 -0.1224 0.6967 0.4573
-2.250 0.2832 0.01123 0.00382 -0.1221 0.6853 0.4837
-2.000 0.3102 0.01129 0.00379 -0.1219 0.6746 0.5055
-1.750 0.3371 0.01134 0.00376 -0.1216 0.6640 0.5231
-1.500 0.3640 0.01138 0.00375 -0.1213 0.6542 0.5386
-1.250 0.3910 0.01145 0.00373 -0.1211 0.6453 0.5529
-1.000 0.4177 0.01149 0.00373 -0.1208 0.6360 0.5665
-0.750 0.4446 0.01155 0.00374 -0.1205 0.6278 0.5800
-0.500 0.4714 0.01161 0.00376 -0.1203 0.6194 0.5931
-0.250 0.4984 0.01168 0.00378 -0.1201 0.6118 0.6057
0.000 0.5250 0.01173 0.00381 -0.1198 0.6041 0.6178
0.250 0.5517 0.01180 0.00386 -0.1195 0.5971 0.6302
0.500 0.5783 0.01186 0.00391 -0.1192 0.5899 0.6427
0.750 0.6050 0.01194 0.00396 -0.1190 0.5834 0.6550
1.000 0.6316 0.01200 0.00404 -0.1187 0.5765 0.6677
1.250 0.6581 0.01208 0.00411 -0.1184 0.5705 0.6808
1.500 0.6843 0.01214 0.00421 -0.1181 0.5640 0.6948
1.750 0.7103 0.01222 0.00431 -0.1177 0.5577 0.7105
2.000 0.7362 0.01230 0.00442 -0.1173 0.5522 0.7281
2.250 0.7615 0.01236 0.00455 -0.1167 0.5459 0.7473
2.500 0.7864 0.01245 0.00467 -0.1160 0.5403 0.7700
2.750 0.8105 0.01250 0.00482 -0.1152 0.5345 0.7969
3.000 0.8339 0.01255 0.00495 -0.1142 0.5287 0.8295
3.500 0.8852 0.01258 0.00516 -0.1129 0.5174 0.9560
3.750 0.9135 0.01274 0.00529 -0.1132 0.5117 1.0000
4.000 0.9403 0.01293 0.00546 -0.1131 0.5062 1.0000
4.250 0.9666 0.01311 0.00567 -0.1130 0.5000 1.0000
4.500 0.9929 0.01332 0.00585 -0.1128 0.4946 1.0000
4.750 1.0188 0.01352 0.00607 -0.1126 0.4884 1.0000
5.000 1.0444 0.01372 0.00628 -0.1123 0.4821 1.0000
5.250 1.0699 0.01394 0.00652 -0.1119 0.4760 1.0000
5.500 1.0946 0.01413 0.00676 -0.1115 0.4685 1.0000
5.750 1.1191 0.01436 0.00697 -0.1109 0.4614 1.0000
6.000 1.1430 0.01456 0.00724 -0.1103 0.4529 1.0000
6.250 1.1668 0.01480 0.00749 -0.1096 0.4452 1.0000
6.500 1.1900 0.01503 0.00776 -0.1089 0.4366 1.0000
6.750 1.2128 0.01527 0.00805 -0.1081 0.4279 1.0000
7.000 1.2348 0.01553 0.00833 -0.1071 0.4188 1.0000
7.250 1.2565 0.01579 0.00866 -0.1061 0.4085 1.0000
7.500 1.2774 0.01607 0.00898 -0.1049 0.3981 1.0000
7.750 1.2971 0.01638 0.00931 -0.1036 0.3870 1.0000
8.000 1.3160 0.01671 0.00968 -0.1021 0.3745 1.0000
8.250 1.3341 0.01706 0.01007 -0.1005 0.3613 1.0000
8.500 1.3497 0.01745 0.01048 -0.0984 0.3468 1.0000
8.750 1.3636 0.01789 0.01093 -0.0961 0.3311 1.0000
9.000 1.3760 0.01842 0.01144 -0.0936 0.3137 1.0000
9.250 1.3873 0.01902 0.01204 -0.0910 0.2932 1.0000
9.500 1.3953 0.01979 0.01275 -0.0880 0.2712 1.0000
9.750 1.4019 0.02067 0.01356 -0.0850 0.2470 1.0000
10.000 1.4061 0.02173 0.01454 -0.0817 0.2236 1.0000
10.250 1.4089 0.02294 0.01566 -0.0786 0.2015 1.0000
10.500 1.4115 0.02423 0.01690 -0.0756 0.1822 1.0000
10.750 1.4141 0.02561 0.01825 -0.0728 0.1649 1.0000
11.000 1.4160 0.02713 0.01976 -0.0702 0.1493 1.0000
11.250 1.4174 0.02877 0.02139 -0.0677 0.1354 1.0000
11.500 1.4185 0.03053 0.02316 -0.0656 0.1230 1.0000
11.750 1.4189 0.03248 0.02512 -0.0636 0.1117 1.0000
12.000 1.4182 0.03462 0.02727 -0.0619 0.1011 1.0000
12.250 1.4167 0.03697 0.02963 -0.0603 0.0911 1.0000
12.500 1.4162 0.03936 0.03205 -0.0591 0.0814 1.0000
12.750 1.4144 0.04200 0.03470 -0.0581 0.0722 1.0000
13.000 1.4118 0.04482 0.03754 -0.0573 0.0645 1.0000
13.250 1.4098 0.04771 0.04046 -0.0567 0.0574 1.0000
13.500 1.4088 0.05061 0.04343 -0.0563 0.0515 1.0000
13.750 1.4059 0.05380 0.04665 -0.0561 0.0463 1.0000
14.000 1.4058 0.05678 0.04973 -0.0560 0.0423 1.0000
14.250 1.4035 0.06008 0.05309 -0.0560 0.0384 1.0000
14.500 1.4015 0.06345 0.05655 -0.0562 0.0352 1.0000
14.750 1.4003 0.06681 0.06001 -0.0565 0.0322 1.0000
15.000 1.3963 0.07061 0.06387 -0.0570 0.0293 1.0000
15.250 1.3945 0.07421 0.06758 -0.0575 0.0267 1.0000
15.500 1.3911 0.07812 0.07158 -0.0583 0.0241 1.0000
15.750 1.3861 0.08235 0.07589 -0.0592 0.0220 1.0000
16.000 1.3831 0.08638 0.08003 -0.0601 0.0197 1.0000
16.250 1.3777 0.09084 0.08458 -0.0614 0.0181 1.0000
16.500 1.3728 0.09533 0.08918 -0.0627 0.0166 1.0000
16.750 1.3685 0.09980 0.09379 -0.0641 0.0151 1.0000
17.000 1.3625 0.10462 0.09870 -0.0658 0.0140 1.0000
17.250 1.3560 0.10960 0.10378 -0.0677 0.0132 1.0000
17.500 1.3512 0.11438 0.10870 -0.0695 0.0124 1.0000
17.750 1.3460 0.11930 0.11375 -0.0716 0.0118 1.0000
18.000 1.3405 0.12432 0.11890 -0.0738 0.0113 1.0000
18.250 1.3345 0.12947 0.12416 -0.0762 0.0109 1.0000
18.500 1.3276 0.13488 0.12968 -0.0789 0.0105 1.0000
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Polar data table (+)
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