E214 (11.1%) (e214-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E214 (11.1%) (e214-il) Reynolds number: 100,000 Max Cl/Cd: 63.16 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e214-il-100000-n5.txt Download as CSV file: xf-e214-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3558 0.10660 0.10174 -0.0391 1.0000 0.0376
-9.000 -0.3573 0.10369 0.09888 -0.0383 1.0000 0.0356
-8.750 -0.3631 0.10055 0.09581 -0.0379 1.0000 0.0345
-8.500 -0.3704 0.09757 0.09290 -0.0374 1.0000 0.0341
-8.000 -0.4125 0.08838 0.08393 -0.0387 1.0000 0.0299
-7.750 -0.4240 0.08523 0.08086 -0.0387 0.9989 0.0300
-7.500 -0.4138 0.07847 0.07410 -0.0471 0.9923 0.0300
-7.250 -0.3982 0.06911 0.06467 -0.0603 0.9846 0.0299
-7.000 -0.3854 0.06131 0.05667 -0.0697 0.9761 0.0297
-6.750 -0.3683 0.05413 0.04919 -0.0779 0.9693 0.0294
-6.500 -0.3487 0.04759 0.04222 -0.0844 0.9621 0.0293
-6.250 -0.3227 0.04184 0.03591 -0.0898 0.9566 0.0293
-6.000 -0.2954 0.03717 0.03058 -0.0934 0.9506 0.0295
-5.750 -0.2615 0.03335 0.02614 -0.0972 0.9470 0.0307
-5.500 -0.2342 0.03158 0.02421 -0.0986 0.9410 0.0327
-5.250 -0.2015 0.02932 0.02152 -0.1006 0.9363 0.0339
-5.000 -0.1650 0.02716 0.01894 -0.1028 0.9332 0.0348
-4.750 -0.1363 0.02559 0.01707 -0.1033 0.9269 0.0358
-4.500 -0.1030 0.02418 0.01541 -0.1045 0.9222 0.0372
-4.250 -0.0663 0.02305 0.01406 -0.1063 0.9190 0.0402
-4.000 -0.0394 0.02209 0.01309 -0.1065 0.9117 0.0434
-3.750 -0.0049 0.02117 0.01209 -0.1079 0.9071 0.0463
-3.500 0.0333 0.02030 0.01106 -0.1100 0.9041 0.0508
-3.250 0.0599 0.01961 0.01037 -0.1100 0.8956 0.0576
-3.000 0.0972 0.01875 0.00957 -0.1120 0.8917 0.0827
-2.750 0.1283 0.01797 0.00906 -0.1131 0.8851 0.1504
-2.500 0.1621 0.01689 0.00872 -0.1151 0.8798 0.3153
-2.250 0.1980 0.01622 0.00868 -0.1167 0.8762 0.5031
-2.000 0.2237 0.01613 0.00864 -0.1160 0.8670 0.5662
-1.750 0.2593 0.01593 0.00843 -0.1170 0.8624 0.6149
-1.500 0.2854 0.01587 0.00833 -0.1163 0.8533 0.6486
-1.250 0.3206 0.01568 0.00809 -0.1172 0.8482 0.6799
-1.000 0.3462 0.01561 0.00800 -0.1164 0.8387 0.7053
-0.750 0.3807 0.01539 0.00773 -0.1172 0.8332 0.7313
-0.500 0.4061 0.01534 0.00765 -0.1164 0.8232 0.7551
-0.250 0.4361 0.01516 0.00745 -0.1163 0.8158 0.7778
0.000 0.4643 0.01502 0.00729 -0.1160 0.8070 0.8011
0.250 0.4904 0.01489 0.00716 -0.1153 0.7976 0.8247
0.500 0.5215 0.01467 0.00692 -0.1154 0.7903 0.8498
0.750 0.5454 0.01456 0.00682 -0.1143 0.7796 0.8801
1.000 0.5761 0.01438 0.00664 -0.1145 0.7703 0.9242
1.250 0.6174 0.01422 0.00641 -0.1172 0.7617 1.0000
1.500 0.6489 0.01432 0.00643 -0.1182 0.7506 1.0000
1.750 0.6813 0.01441 0.00642 -0.1192 0.7402 1.0000
2.000 0.7149 0.01447 0.00640 -0.1204 0.7305 1.0000
2.250 0.7456 0.01460 0.00647 -0.1210 0.7195 1.0000
2.500 0.7746 0.01475 0.00659 -0.1213 0.7080 1.0000
2.750 0.8042 0.01491 0.00670 -0.1216 0.6968 1.0000
3.000 0.8341 0.01507 0.00680 -0.1220 0.6859 1.0000
3.250 0.8632 0.01524 0.00696 -0.1223 0.6746 1.0000
3.500 0.8899 0.01545 0.00717 -0.1221 0.6623 1.0000
3.750 0.9167 0.01567 0.00739 -0.1219 0.6500 1.0000
4.000 0.9434 0.01589 0.00763 -0.1217 0.6374 1.0000
4.250 0.9698 0.01611 0.00786 -0.1214 0.6245 1.0000
4.500 0.9958 0.01635 0.00810 -0.1209 0.6111 1.0000
4.750 1.0211 0.01660 0.00837 -0.1204 0.5972 1.0000
5.000 1.0458 0.01686 0.00868 -0.1198 0.5827 1.0000
5.250 1.0698 0.01713 0.00898 -0.1190 0.5673 1.0000
5.500 1.0930 0.01741 0.00929 -0.1181 0.5509 1.0000
5.750 1.1158 0.01770 0.00961 -0.1171 0.5336 1.0000
6.000 1.1381 0.01802 0.00994 -0.1160 0.5157 1.0000
6.250 1.1593 0.01836 0.01035 -0.1148 0.4968 1.0000
6.500 1.1796 0.01874 0.01076 -0.1134 0.4764 1.0000
6.750 1.1991 0.01915 0.01117 -0.1118 0.4549 1.0000
7.000 1.2171 0.01960 0.01164 -0.1101 0.4308 1.0000
7.250 1.2341 0.02012 0.01215 -0.1082 0.4054 1.0000
7.500 1.2496 0.02070 0.01274 -0.1061 0.3782 1.0000
7.750 1.2636 0.02136 0.01335 -0.1038 0.3494 1.0000
8.000 1.2754 0.02211 0.01404 -0.1012 0.3189 1.0000
8.250 1.2847 0.02296 0.01480 -0.0982 0.2882 1.0000
8.500 1.2926 0.02394 0.01567 -0.0952 0.2575 1.0000
8.750 1.2995 0.02504 0.01667 -0.0922 0.2277 1.0000
9.000 1.3062 0.02622 0.01780 -0.0893 0.2005 1.0000
9.250 1.3122 0.02751 0.01901 -0.0865 0.1752 1.0000
9.500 1.3177 0.02888 0.02033 -0.0838 0.1538 1.0000
9.750 1.3233 0.03031 0.02174 -0.0812 0.1346 1.0000
10.000 1.3277 0.03187 0.02328 -0.0787 0.1185 1.0000
10.250 1.3319 0.03352 0.02494 -0.0763 0.1049 1.0000
10.500 1.3357 0.03526 0.02671 -0.0740 0.0926 1.0000
10.750 1.3390 0.03710 0.02861 -0.0719 0.0819 1.0000
11.000 1.3412 0.03912 0.03068 -0.0699 0.0728 1.0000
11.250 1.3414 0.04138 0.03297 -0.0680 0.0645 1.0000
11.500 1.3441 0.04353 0.03522 -0.0665 0.0558 1.0000
11.750 1.3456 0.04587 0.03765 -0.0651 0.0481 1.0000
12.000 1.3434 0.04865 0.04043 -0.0639 0.0424 1.0000
12.250 1.3449 0.05121 0.04318 -0.0629 0.0370 1.0000
12.500 1.3403 0.05450 0.04652 -0.0620 0.0335 1.0000
12.750 1.3384 0.05766 0.04987 -0.0613 0.0303 1.0000
13.000 1.3359 0.06100 0.05335 -0.0609 0.0274 1.0000
13.250 1.3302 0.06481 0.05726 -0.0608 0.0254 1.0000
13.500 1.3260 0.06863 0.06124 -0.0608 0.0235 1.0000
13.750 1.3231 0.07242 0.06522 -0.0610 0.0217 1.0000
14.000 1.3192 0.07645 0.06941 -0.0615 0.0203 1.0000
14.250 1.3142 0.08074 0.07385 -0.0623 0.0194 1.0000
14.500 1.3082 0.08530 0.07854 -0.0633 0.0187 1.0000
14.750 1.3016 0.09004 0.08338 -0.0643 0.0181 1.0000
15.000 1.2983 0.09448 0.08808 -0.0653 0.0175 1.0000
15.250 1.2942 0.09918 0.09301 -0.0666 0.0170 1.0000
15.500 1.2891 0.10417 0.09823 -0.0682 0.0166 1.0000
15.750 1.2828 0.10951 0.10379 -0.0702 0.0162 1.0000
16.000 1.2753 0.11520 0.10970 -0.0727 0.0159 1.0000
16.250 1.2666 0.12132 0.11604 -0.0757 0.0157 1.0000
16.500 1.2567 0.12790 0.12283 -0.0792 0.0155 1.0000
16.750 1.2454 0.13503 0.13017 -0.0833 0.0154 1.0000
17.000 1.2327 0.14286 0.13821 -0.0881 0.0153 1.0000
17.250 1.2178 0.15159 0.14714 -0.0938 0.0154 1.0000
17.500 1.2001 0.16168 0.15742 -0.1004 0.0156 1.0000
17.750 1.1781 0.17398 0.16986 -0.1087 0.0160 1.0000
18.000 1.1508 0.18956 0.18555 -0.1186 0.0165 1.0000
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Polar data table (+)
Polar graphs
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