E214 (11.1%) (e214-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E214 (11.1%) (e214-il) Reynolds number: 200,000 Max Cl/Cd: 84.86 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e214-il-200000-n5.txt Download as CSV file: xf-e214-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3444 0.08673 0.08335 -0.0501 0.9908 0.0187
-8.250 -0.3408 0.08018 0.07683 -0.0563 0.9861 0.0181
-7.750 -0.3621 0.04901 0.04536 -0.0909 0.9628 0.0163
-7.500 -0.3536 0.04082 0.03660 -0.0993 0.9545 0.0164
-7.250 -0.3358 0.03477 0.03001 -0.1044 0.9487 0.0168
-7.000 -0.3060 0.03250 0.02754 -0.1077 0.9462 0.0177
-6.750 -0.2851 0.03094 0.02581 -0.1081 0.9395 0.0188
-6.500 -0.2557 0.02783 0.02221 -0.1106 0.9358 0.0198
-6.250 -0.2227 0.02486 0.01870 -0.1132 0.9334 0.0203
-6.000 -0.1955 0.02288 0.01633 -0.1138 0.9284 0.0209
-5.750 -0.1659 0.02127 0.01440 -0.1147 0.9239 0.0215
-5.500 -0.1323 0.02000 0.01284 -0.1161 0.9211 0.0227
-5.250 -0.0981 0.01855 0.01130 -0.1179 0.9190 0.0241
-5.000 -0.0720 0.01764 0.01029 -0.1178 0.9127 0.0248
-4.750 -0.0400 0.01673 0.00929 -0.1188 0.9086 0.0257
-4.500 -0.0044 0.01588 0.00834 -0.1205 0.9058 0.0269
-4.250 0.0267 0.01521 0.00759 -0.1213 0.9007 0.0282
-4.000 0.0581 0.01468 0.00696 -0.1221 0.8949 0.0300
-3.750 0.0954 0.01399 0.00624 -0.1243 0.8914 0.0337
-3.500 0.1260 0.01356 0.00572 -0.1249 0.8847 0.0373
-3.250 0.1603 0.01305 0.00519 -0.1263 0.8789 0.0462
-3.000 0.1950 0.01251 0.00474 -0.1279 0.8731 0.0797
-2.750 0.2267 0.01203 0.00443 -0.1289 0.8653 0.1358
-2.500 0.2609 0.01137 0.00417 -0.1307 0.8584 0.2441
-2.250 0.2932 0.01074 0.00401 -0.1321 0.8501 0.3827
-2.000 0.3240 0.01043 0.00401 -0.1328 0.8410 0.4979
-1.750 0.3578 0.01029 0.00389 -0.1338 0.8328 0.5502
-1.500 0.3870 0.01023 0.00383 -0.1339 0.8219 0.5829
-1.000 0.4479 0.01014 0.00366 -0.1346 0.8007 0.6280
-0.500 0.5069 0.01011 0.00354 -0.1349 0.7780 0.6661
-0.250 0.5350 0.01012 0.00352 -0.1348 0.7662 0.6831
0.000 0.5630 0.01014 0.00351 -0.1347 0.7546 0.6995
0.250 0.5907 0.01017 0.00351 -0.1345 0.7432 0.7159
0.500 0.6181 0.01021 0.00351 -0.1342 0.7319 0.7325
0.750 0.6442 0.01026 0.00355 -0.1337 0.7201 0.7487
1.000 0.6702 0.01031 0.00359 -0.1332 0.7086 0.7646
1.250 0.6960 0.01037 0.00365 -0.1327 0.6974 0.7810
1.500 0.7215 0.01044 0.00370 -0.1321 0.6865 0.7989
1.750 0.7458 0.01050 0.00377 -0.1312 0.6752 0.8187
2.250 0.7917 0.01059 0.00392 -0.1288 0.6530 0.8741
2.500 0.8146 0.01059 0.00395 -0.1275 0.6423 0.9257
2.750 0.8445 0.01068 0.00400 -0.1280 0.6307 1.0000
3.000 0.8712 0.01085 0.00415 -0.1278 0.6185 1.0000
3.250 0.8975 0.01104 0.00429 -0.1276 0.6061 1.0000
3.500 0.9235 0.01123 0.00445 -0.1273 0.5934 1.0000
3.750 0.9491 0.01143 0.00462 -0.1269 0.5804 1.0000
4.000 0.9744 0.01164 0.00482 -0.1265 0.5671 1.0000
4.250 0.9993 0.01187 0.00501 -0.1259 0.5529 1.0000
4.500 1.0237 0.01210 0.00522 -0.1253 0.5379 1.0000
4.750 1.0475 0.01235 0.00544 -0.1246 0.5217 1.0000
5.000 1.0709 0.01262 0.00570 -0.1238 0.5045 1.0000
5.250 1.0938 0.01291 0.00595 -0.1229 0.4872 1.0000
5.500 1.1163 0.01321 0.00623 -0.1219 0.4693 1.0000
5.750 1.1382 0.01354 0.00654 -0.1209 0.4492 1.0000
6.000 1.1587 0.01392 0.00688 -0.1195 0.4272 1.0000
6.250 1.1789 0.01432 0.00724 -0.1182 0.4035 1.0000
6.500 1.1980 0.01477 0.00763 -0.1167 0.3788 1.0000
6.750 1.2161 0.01528 0.00806 -0.1150 0.3528 1.0000
7.000 1.2327 0.01585 0.00854 -0.1132 0.3238 1.0000
7.250 1.2481 0.01649 0.00910 -0.1111 0.2931 1.0000
7.500 1.2613 0.01719 0.00968 -0.1087 0.2619 1.0000
7.750 1.2733 0.01797 0.01033 -0.1062 0.2310 1.0000
8.000 1.2849 0.01881 0.01105 -0.1037 0.2018 1.0000
8.250 1.2968 0.01966 0.01180 -0.1013 0.1762 1.0000
8.500 1.3084 0.02055 0.01261 -0.0989 0.1538 1.0000
8.750 1.3202 0.02144 0.01348 -0.0966 0.1340 1.0000
9.000 1.3308 0.02242 0.01441 -0.0943 0.1165 1.0000
9.250 1.3415 0.02342 0.01538 -0.0920 0.1006 1.0000
9.500 1.3514 0.02447 0.01641 -0.0897 0.0859 1.0000
9.750 1.3604 0.02562 0.01752 -0.0874 0.0719 1.0000
10.000 1.3685 0.02685 0.01871 -0.0851 0.0591 1.0000
10.250 1.3764 0.02812 0.01997 -0.0829 0.0485 1.0000
10.500 1.3841 0.02945 0.02132 -0.0808 0.0410 1.0000
10.750 1.3911 0.03087 0.02278 -0.0787 0.0340 1.0000
11.000 1.3988 0.03229 0.02428 -0.0768 0.0287 1.0000
11.250 1.4036 0.03399 0.02602 -0.0748 0.0242 1.0000
11.500 1.4091 0.03569 0.02782 -0.0730 0.0204 1.0000
11.750 1.4113 0.03776 0.02996 -0.0712 0.0174 1.0000
12.000 1.4145 0.03983 0.03217 -0.0696 0.0151 1.0000
12.250 1.4150 0.04223 0.03465 -0.0680 0.0136 1.0000
12.500 1.4157 0.04471 0.03726 -0.0667 0.0123 1.0000
12.750 1.4168 0.04723 0.03994 -0.0657 0.0113 1.0000
13.000 1.4178 0.04986 0.04269 -0.0648 0.0105 1.0000
13.250 1.4162 0.05289 0.04583 -0.0642 0.0098 1.0000
13.500 1.4129 0.05625 0.04935 -0.0638 0.0093 1.0000
13.750 1.4114 0.05953 0.05280 -0.0636 0.0089 1.0000
14.000 1.4084 0.06312 0.05657 -0.0636 0.0085 1.0000
14.250 1.4046 0.06696 0.06057 -0.0638 0.0083 1.0000
14.500 1.4003 0.07100 0.06478 -0.0643 0.0080 1.0000
14.750 1.3956 0.07525 0.06918 -0.0651 0.0078 1.0000
15.000 1.3901 0.07974 0.07383 -0.0661 0.0076 1.0000
15.250 1.3842 0.08443 0.07868 -0.0673 0.0075 1.0000
15.500 1.3780 0.08933 0.08373 -0.0689 0.0073 1.0000
15.750 1.3710 0.09448 0.08904 -0.0706 0.0072 1.0000
16.000 1.3638 0.09980 0.09451 -0.0726 0.0071 1.0000
16.250 1.3560 0.10535 0.10020 -0.0749 0.0070 1.0000
16.500 1.3482 0.11103 0.10604 -0.0774 0.0069 1.0000
16.750 1.3403 0.11685 0.11200 -0.0801 0.0068 1.0000
17.000 1.3323 0.12276 0.11805 -0.0830 0.0067 1.0000
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Polar data table (+)
Polar graphs
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