E214 (11.1%) (e214-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E214 (11.1%) (e214-il) Reynolds number: 200,000 Max Cl/Cd: 87.57 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e214-il-200000.txt Download as CSV file: xf-e214-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E214 (11.1%)
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3994 0.09492 0.09184 -0.0316 1.0000 0.0491
-7.750 -0.4037 0.09317 0.09013 -0.0295 1.0000 0.0500
-7.500 -0.4127 0.09147 0.08848 -0.0274 1.0000 0.0510
-7.250 -0.4115 0.08859 0.08564 -0.0289 0.9977 0.0524
-7.000 -0.3994 0.08393 0.08098 -0.0358 0.9912 0.0550
-6.750 -0.3698 0.06968 0.06637 -0.0707 0.9760 0.0592
-6.500 -0.3546 0.06277 0.05957 -0.0733 0.9730 0.0609
-6.250 -0.3342 0.06055 0.05739 -0.0736 0.9677 0.0628
-6.000 -0.3073 0.05609 0.05281 -0.0794 0.9619 0.0667
-5.750 -0.2779 0.04767 0.04382 -0.0911 0.9543 0.0747
-5.500 -0.2493 0.04490 0.04104 -0.0933 0.9497 0.0779
-5.250 -0.2106 0.04042 0.03616 -0.0999 0.9466 0.0898
-5.000 -0.1599 0.02772 0.02173 -0.1059 0.9458 0.0441
-4.750 -0.1320 0.02493 0.01849 -0.1064 0.9386 0.0426
-4.500 -0.0927 0.02279 0.01595 -0.1087 0.9355 0.0430
-4.250 -0.0513 0.02146 0.01433 -0.1113 0.9333 0.0453
-4.000 -0.0208 0.02029 0.01297 -0.1117 0.9268 0.0461
-3.750 0.0159 0.01888 0.01145 -0.1133 0.9229 0.0477
-3.500 0.0560 0.01758 0.01019 -0.1158 0.9203 0.0513
-3.250 0.0990 0.01684 0.00939 -0.1187 0.9183 0.0589
-3.000 0.1271 0.01601 0.00859 -0.1189 0.9098 0.0705
-2.750 0.1697 0.01435 0.00767 -0.1226 0.9073 0.2290
-2.500 0.2120 0.01324 0.00739 -0.1261 0.9053 0.4535
-2.250 0.2422 0.01301 0.00737 -0.1262 0.8981 0.5578
-2.000 0.2801 0.01276 0.00720 -0.1277 0.8939 0.6212
-1.750 0.3216 0.01247 0.00691 -0.1299 0.8912 0.6561
-1.500 0.3512 0.01233 0.00677 -0.1298 0.8831 0.6832
-1.250 0.3887 0.01207 0.00648 -0.1313 0.8783 0.7092
-1.000 0.4216 0.01186 0.00626 -0.1318 0.8715 0.7293
-0.750 0.4547 0.01164 0.00603 -0.1324 0.8641 0.7492
-0.500 0.4860 0.01147 0.00585 -0.1328 0.8559 0.7691
-0.250 0.5189 0.01124 0.00561 -0.1333 0.8483 0.7872
0.000 0.5455 0.01112 0.00550 -0.1326 0.8378 0.8055
0.250 0.5754 0.01096 0.00534 -0.1326 0.8288 0.8250
0.500 0.6037 0.01080 0.00517 -0.1323 0.8191 0.8451
0.750 0.6264 0.01070 0.00509 -0.1308 0.8075 0.8674
1.000 0.6489 0.01058 0.00498 -0.1292 0.7964 0.8935
1.500 0.7144 0.01027 0.00462 -0.1307 0.7752 1.0000
1.750 0.7470 0.01037 0.00464 -0.1321 0.7629 1.0000
2.000 0.7782 0.01050 0.00468 -0.1331 0.7508 1.0000
2.250 0.8084 0.01064 0.00474 -0.1336 0.7390 1.0000
2.500 0.8381 0.01078 0.00480 -0.1341 0.7274 1.0000
2.750 0.8676 0.01094 0.00487 -0.1344 0.7158 1.0000
3.000 0.8944 0.01111 0.00502 -0.1342 0.7031 1.0000
3.250 0.9209 0.01129 0.00516 -0.1339 0.6901 1.0000
3.500 0.9473 0.01147 0.00531 -0.1336 0.6772 1.0000
3.750 0.9736 0.01167 0.00547 -0.1333 0.6642 1.0000
4.000 0.9995 0.01186 0.00565 -0.1329 0.6511 1.0000
4.250 1.0251 0.01206 0.00583 -0.1324 0.6376 1.0000
4.500 1.0502 0.01225 0.00601 -0.1318 0.6234 1.0000
4.750 1.0747 0.01246 0.00620 -0.1310 0.6086 1.0000
5.000 1.0987 0.01266 0.00642 -0.1302 0.5935 1.0000
5.250 1.1224 0.01288 0.00664 -0.1294 0.5780 1.0000
5.500 1.1456 0.01310 0.00687 -0.1284 0.5618 1.0000
5.750 1.1682 0.01334 0.00710 -0.1273 0.5447 1.0000
6.000 1.1903 0.01361 0.00736 -0.1261 0.5267 1.0000
6.250 1.2114 0.01388 0.00764 -0.1248 0.5073 1.0000
6.500 1.2317 0.01418 0.00794 -0.1233 0.4866 1.0000
6.750 1.2513 0.01452 0.00827 -0.1218 0.4650 1.0000
7.000 1.2695 0.01490 0.00864 -0.1199 0.4406 1.0000
7.250 1.2866 0.01533 0.00904 -0.1179 0.4139 1.0000
7.500 1.3018 0.01584 0.00948 -0.1157 0.3844 1.0000
7.750 1.3152 0.01645 0.00999 -0.1132 0.3525 1.0000
8.000 1.3268 0.01714 0.01058 -0.1104 0.3183 1.0000
8.250 1.3353 0.01793 0.01125 -0.1071 0.2831 1.0000
8.500 1.3421 0.01888 0.01203 -0.1037 0.2478 1.0000
8.750 1.3486 0.01992 0.01293 -0.1004 0.2132 1.0000
9.000 1.3538 0.02111 0.01395 -0.0970 0.1814 1.0000
9.250 1.3587 0.02239 0.01508 -0.0938 0.1532 1.0000
9.500 1.3638 0.02372 0.01629 -0.0907 0.1285 1.0000
9.750 1.3683 0.02513 0.01760 -0.0878 0.1079 1.0000
10.000 1.3736 0.02654 0.01895 -0.0851 0.0904 1.0000
10.250 1.3781 0.02805 0.02045 -0.0824 0.0766 1.0000
10.500 1.3823 0.02966 0.02206 -0.0799 0.0654 1.0000
10.750 1.3848 0.03147 0.02390 -0.0773 0.0561 1.0000
11.000 1.3845 0.03357 0.02600 -0.0747 0.0477 1.0000
11.250 1.3835 0.03585 0.02828 -0.0724 0.0400 1.0000
11.500 1.3857 0.03799 0.03055 -0.0704 0.0340 1.0000
11.750 1.3785 0.04111 0.03367 -0.0681 0.0305 1.0000
12.000 1.3803 0.04357 0.03629 -0.0664 0.0277 1.0000
12.250 1.3820 0.04609 0.03891 -0.0650 0.0255 1.0000
12.500 1.3820 0.04888 0.04176 -0.0638 0.0240 1.0000
12.750 1.3810 0.05228 0.04520 -0.0622 0.0225 1.0000
13.000 1.3863 0.05467 0.04782 -0.0614 0.0214 1.0000
13.250 1.3902 0.05728 0.05059 -0.0607 0.0201 1.0000
13.500 1.3931 0.06005 0.05349 -0.0601 0.0191 1.0000
13.750 1.3956 0.06296 0.05651 -0.0597 0.0183 1.0000
14.000 1.3984 0.06602 0.05967 -0.0592 0.0177 1.0000
14.250 1.4017 0.06937 0.06314 -0.0586 0.0172 1.0000
14.500 1.4033 0.07362 0.06761 -0.0579 0.0168 1.0000
14.750 1.3989 0.07814 0.07238 -0.0580 0.0166 1.0000
15.000 1.3915 0.08274 0.07724 -0.0586 0.0165 1.0000
15.250 1.3821 0.08776 0.08252 -0.0596 0.0164 1.0000
15.500 1.3710 0.09322 0.08824 -0.0610 0.0164 1.0000
15.750 1.3580 0.09915 0.09441 -0.0631 0.0163 1.0000
16.000 1.3436 0.10551 0.10101 -0.0657 0.0163 1.0000
16.250 1.3284 0.11227 0.10800 -0.0688 0.0164 1.0000
16.500 1.3122 0.11950 0.11545 -0.0726 0.0164 1.0000
16.750 1.2953 0.12719 0.12335 -0.0770 0.0165 1.0000
17.000 1.2781 0.13531 0.13165 -0.0819 0.0166 1.0000
17.250 1.2635 0.14323 0.13977 -0.0871 0.0167 1.0000
17.500 1.2498 0.15138 0.14809 -0.0929 0.0168 1.0000
17.750 1.2329 0.16116 0.15807 -0.1002 0.0171 1.0000
18.000 1.1171 0.21498 0.21208 -0.1328 0.0242 1.0000
18.250 1.1274 0.21543 0.21257 -0.1333 0.0233 1.0000
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Polar data table (+)
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