E210 (13.64%) (e210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E210 (13.64%) (e210-il) Reynolds number: 1,000,000 Max Cl/Cd: 140.31 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e210-il-1000000.txt Download as CSV file: xf-e210-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.2499 0.11898 0.11743 -0.0471 0.9965 0.0141
-12.250 -0.7329 0.05010 0.04789 -0.0711 1.0000 0.0089
-12.000 -0.7375 0.04227 0.03985 -0.0820 0.9972 0.0090
-11.750 -0.7306 0.03647 0.03382 -0.0923 0.9941 0.0091
-11.500 -0.7173 0.03438 0.03166 -0.0962 0.9894 0.0093
-11.250 -0.6985 0.03064 0.02766 -0.1027 0.9856 0.0094
-11.000 -0.6680 0.02926 0.02618 -0.1062 0.9843 0.0098
-10.750 -0.6533 0.02708 0.02379 -0.1072 0.9797 0.0100
-10.500 -0.6295 0.02528 0.02179 -0.1090 0.9765 0.0103
-10.250 -0.6012 0.02368 0.01998 -0.1113 0.9746 0.0106
-10.000 -0.5693 0.02259 0.01873 -0.1135 0.9733 0.0108
-9.750 -0.5423 0.01978 0.01565 -0.1162 0.9720 0.0114
-9.500 -0.5247 0.01889 0.01470 -0.1150 0.9662 0.0116
-9.250 -0.4944 0.01817 0.01393 -0.1162 0.9637 0.0120
-9.000 -0.4617 0.01739 0.01306 -0.1179 0.9619 0.0124
-8.750 -0.4277 0.01664 0.01224 -0.1198 0.9606 0.0130
-8.500 -0.3928 0.01580 0.01130 -0.1218 0.9595 0.0134
-8.250 -0.3728 0.01524 0.01067 -0.1204 0.9528 0.0138
-8.000 -0.3408 0.01495 0.01032 -0.1214 0.9494 0.0141
-7.750 -0.3112 0.01329 0.00856 -0.1228 0.9467 0.0151
-7.500 -0.2900 0.01277 0.00802 -0.1216 0.9381 0.0156
-7.250 -0.2561 0.01217 0.00738 -0.1231 0.9331 0.0163
-7.000 -0.2241 0.01166 0.00681 -0.1242 0.9250 0.0169
-6.750 -0.1837 0.01111 0.00619 -0.1270 0.9178 0.0176
-6.500 -0.1453 0.01079 0.00579 -0.1293 0.9048 0.0181
-6.250 -0.1122 0.00988 0.00473 -0.1309 0.8865 0.0194
-6.000 -0.0825 0.00957 0.00429 -0.1314 0.8631 0.0203
-5.750 -0.0558 0.00936 0.00395 -0.1312 0.8391 0.0212
-5.500 -0.0305 0.00920 0.00365 -0.1307 0.8156 0.0220
-5.250 -0.0054 0.00910 0.00342 -0.1301 0.7938 0.0228
-5.000 0.0193 0.00884 0.00302 -0.1295 0.7728 0.0247
-4.750 0.0442 0.00870 0.00279 -0.1289 0.7531 0.0266
-4.500 0.0698 0.00861 0.00259 -0.1284 0.7353 0.0284
-4.250 0.0955 0.00844 0.00237 -0.1280 0.7185 0.0357
-4.000 0.1210 0.00816 0.00216 -0.1277 0.7026 0.0686
-3.750 0.1469 0.00796 0.00202 -0.1274 0.6882 0.1006
-3.500 0.1730 0.00780 0.00191 -0.1272 0.6747 0.1335
-3.250 0.1996 0.00764 0.00180 -0.1271 0.6619 0.1690
-3.000 0.2263 0.00745 0.00171 -0.1270 0.6502 0.2147
-2.750 0.2530 0.00725 0.00163 -0.1269 0.6394 0.2676
-2.500 0.2793 0.00699 0.00156 -0.1268 0.6290 0.3445
-2.250 0.3066 0.00685 0.00154 -0.1268 0.6192 0.4019
-2.000 0.3339 0.00684 0.00154 -0.1267 0.6104 0.4333
-1.750 0.3614 0.00684 0.00155 -0.1266 0.6017 0.4603
-1.500 0.3890 0.00686 0.00156 -0.1265 0.5938 0.4783
-1.250 0.4165 0.00690 0.00157 -0.1264 0.5857 0.4910
-1.000 0.4442 0.00693 0.00159 -0.1264 0.5788 0.5060
-0.750 0.4718 0.00696 0.00160 -0.1263 0.5716 0.5164
-0.500 0.4994 0.00701 0.00162 -0.1262 0.5650 0.5257
-0.250 0.5272 0.00704 0.00165 -0.1262 0.5584 0.5357
0.000 0.5544 0.00710 0.00168 -0.1260 0.5521 0.5448
0.250 0.5825 0.00713 0.00171 -0.1260 0.5463 0.5546
0.500 0.6099 0.00717 0.00175 -0.1260 0.5401 0.5645
0.750 0.6373 0.00723 0.00179 -0.1259 0.5345 0.5748
1.000 0.6651 0.00725 0.00184 -0.1259 0.5289 0.5856
1.250 0.6923 0.00731 0.00189 -0.1257 0.5231 0.5963
1.500 0.7198 0.00735 0.00195 -0.1257 0.5178 0.6082
1.750 0.7474 0.00739 0.00201 -0.1256 0.5123 0.6219
2.000 0.7742 0.00746 0.00208 -0.1254 0.5067 0.6361
2.250 0.8018 0.00749 0.00215 -0.1254 0.5016 0.6507
2.500 0.8290 0.00753 0.00223 -0.1253 0.4961 0.6669
2.750 0.8554 0.00761 0.00233 -0.1250 0.4904 0.6849
3.000 0.8829 0.00762 0.00241 -0.1250 0.4853 0.7055
3.250 0.9096 0.00766 0.00251 -0.1248 0.4796 0.7293
3.500 0.9357 0.00772 0.00263 -0.1244 0.4738 0.7565
3.750 0.9622 0.00773 0.00273 -0.1242 0.4675 0.7872
4.000 0.9868 0.00778 0.00285 -0.1235 0.4606 0.8241
4.250 1.0108 0.00775 0.00297 -0.1227 0.4543 0.8724
4.500 1.0347 0.00767 0.00304 -0.1217 0.4476 0.9918
4.750 1.0612 0.00779 0.00315 -0.1215 0.4411 1.0000
5.000 1.0877 0.00792 0.00326 -0.1213 0.4339 1.0000
5.250 1.1138 0.00806 0.00339 -0.1210 0.4267 1.0000
5.500 1.1398 0.00820 0.00351 -0.1208 0.4188 1.0000
5.750 1.1656 0.00835 0.00365 -0.1205 0.4111 1.0000
6.000 1.1909 0.00852 0.00380 -0.1201 0.4023 1.0000
6.250 1.2165 0.00867 0.00395 -0.1197 0.3939 1.0000
6.500 1.2408 0.00889 0.00413 -0.1192 0.3842 1.0000
6.750 1.2657 0.00906 0.00430 -0.1187 0.3738 1.0000
7.000 1.2901 0.00927 0.00449 -0.1181 0.3633 1.0000
7.250 1.3135 0.00951 0.00470 -0.1174 0.3512 1.0000
7.500 1.3362 0.00979 0.00494 -0.1166 0.3362 1.0000
7.750 1.3582 0.01010 0.00520 -0.1157 0.3200 1.0000
8.000 1.3790 0.01045 0.00548 -0.1145 0.3017 1.0000
8.250 1.3970 0.01090 0.00583 -0.1128 0.2790 1.0000
8.500 1.4111 0.01151 0.00627 -0.1105 0.2470 1.0000
8.750 1.4220 0.01226 0.00682 -0.1076 0.2126 1.0000
9.000 1.4332 0.01299 0.00739 -0.1049 0.1840 1.0000
9.250 1.4443 0.01369 0.00797 -0.1021 0.1596 1.0000
9.500 1.4545 0.01445 0.00860 -0.0993 0.1367 1.0000
9.750 1.4650 0.01518 0.00923 -0.0966 0.1176 1.0000
10.000 1.4749 0.01595 0.00991 -0.0939 0.1010 1.0000
10.250 1.4849 0.01671 0.01060 -0.0912 0.0874 1.0000
10.500 1.4950 0.01748 0.01132 -0.0886 0.0759 1.0000
10.750 1.5056 0.01823 0.01205 -0.0863 0.0670 1.0000
11.000 1.5153 0.01904 0.01285 -0.0838 0.0590 1.0000
11.250 1.5233 0.01997 0.01376 -0.0813 0.0513 1.0000
11.500 1.5313 0.02094 0.01472 -0.0789 0.0452 1.0000
11.750 1.5397 0.02193 0.01572 -0.0766 0.0399 1.0000
12.000 1.5450 0.02315 0.01693 -0.0742 0.0346 1.0000
12.250 1.5520 0.02432 0.01813 -0.0721 0.0304 1.0000
12.500 1.5568 0.02571 0.01954 -0.0700 0.0265 1.0000
12.750 1.5613 0.02720 0.02105 -0.0680 0.0230 1.0000
13.000 1.5644 0.02889 0.02276 -0.0662 0.0193 1.0000
13.250 1.5646 0.03091 0.02479 -0.0643 0.0153 1.0000
13.500 1.5641 0.03312 0.02703 -0.0627 0.0121 1.0000
13.750 1.5629 0.03553 0.02948 -0.0613 0.0100 1.0000
14.000 1.5644 0.03780 0.03182 -0.0603 0.0087 1.0000
14.250 1.5606 0.04072 0.03480 -0.0592 0.0074 1.0000
14.500 1.5627 0.04314 0.03731 -0.0586 0.0071 1.0000
14.750 1.5646 0.04569 0.03994 -0.0582 0.0068 1.0000
15.000 1.5646 0.04850 0.04283 -0.0578 0.0064 1.0000
15.250 1.5626 0.05164 0.04605 -0.0576 0.0060 1.0000
15.500 1.5604 0.05492 0.04941 -0.0576 0.0058 1.0000
15.750 1.5530 0.05894 0.05354 -0.0577 0.0054 1.0000
16.000 1.5505 0.06244 0.05713 -0.0580 0.0053 1.0000
16.250 1.5497 0.06582 0.06060 -0.0584 0.0052 1.0000
16.500 1.5469 0.06954 0.06442 -0.0590 0.0051 1.0000
16.750 1.5437 0.07340 0.06838 -0.0597 0.0050 1.0000
17.000 1.5406 0.07731 0.07239 -0.0605 0.0049 1.0000
17.250 1.5358 0.08158 0.07675 -0.0615 0.0047 1.0000
17.500 1.5310 0.08594 0.08121 -0.0627 0.0046 1.0000
17.750 1.5264 0.09033 0.08570 -0.0640 0.0045 1.0000
18.000 1.5214 0.09486 0.09033 -0.0654 0.0044 1.0000
18.250 1.5143 0.09983 0.09540 -0.0671 0.0044 1.0000
18.500 1.5074 0.10485 0.10051 -0.0690 0.0043 1.0000
18.750 1.5007 0.10988 0.10565 -0.0709 0.0043 1.0000
19.000 1.4924 0.11527 0.11114 -0.0731 0.0042 1.0000
19.250 1.4840 0.12076 0.11673 -0.0755 0.0041 1.0000
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Polar data table (+)
Polar graphs
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