E210 (13.64%) (e210-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E210 (13.64%) (e210-il) Reynolds number: 500,000 Max Cl/Cd: 112.97 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e210-il-500000.txt Download as CSV file: xf-e210-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3615 0.10405 0.10189 -0.0392 1.0000 0.0244
-10.000 -0.3632 0.10130 0.09917 -0.0390 1.0000 0.0249
-9.250 -0.5023 0.04090 0.03799 -0.0951 0.9785 0.0175
-9.000 -0.4908 0.03399 0.03051 -0.1020 0.9729 0.0173
-8.750 -0.4760 0.02999 0.02604 -0.1039 0.9659 0.0176
-8.500 -0.4495 0.02703 0.02266 -0.1063 0.9619 0.0178
-8.250 -0.4202 0.02362 0.01878 -0.1092 0.9596 0.0185
-8.000 -0.3978 0.02204 0.01715 -0.1093 0.9532 0.0193
-7.750 -0.3662 0.02092 0.01593 -0.1107 0.9494 0.0202
-7.500 -0.3317 0.01948 0.01431 -0.1127 0.9470 0.0209
-7.250 -0.3019 0.01818 0.01285 -0.1135 0.9425 0.0216
-7.000 -0.2736 0.01719 0.01172 -0.1138 0.9363 0.0223
-6.750 -0.2386 0.01630 0.01069 -0.1153 0.9333 0.0229
-6.500 -0.2147 0.01470 0.00904 -0.1151 0.9255 0.0242
-6.250 -0.1814 0.01388 0.00819 -0.1164 0.9200 0.0255
-6.000 -0.1485 0.01314 0.00739 -0.1175 0.9126 0.0265
-5.750 -0.1093 0.01242 0.00659 -0.1200 0.9058 0.0278
-5.500 -0.0715 0.01171 0.00580 -0.1223 0.8960 0.0293
-5.250 -0.0318 0.01098 0.00500 -0.1250 0.8846 0.0319
-5.000 0.0055 0.01054 0.00446 -0.1270 0.8688 0.0344
-4.750 0.0387 0.01012 0.00392 -0.1282 0.8496 0.0383
-4.500 0.0690 0.00981 0.00352 -0.1287 0.8294 0.0473
-4.250 0.0957 0.00933 0.00315 -0.1287 0.8087 0.0900
-4.000 0.1219 0.00906 0.00292 -0.1285 0.7885 0.1315
-3.750 0.1478 0.00884 0.00274 -0.1282 0.7695 0.1738
-3.250 0.1989 0.00833 0.00244 -0.1277 0.7354 0.2936
-3.000 0.2243 0.00808 0.00237 -0.1274 0.7199 0.3750
-2.750 0.2505 0.00804 0.00237 -0.1271 0.7056 0.4291
-2.500 0.2770 0.00806 0.00237 -0.1268 0.6922 0.4625
-2.250 0.3036 0.00810 0.00238 -0.1264 0.6796 0.4882
-2.000 0.3305 0.00816 0.00238 -0.1262 0.6682 0.5047
-1.750 0.3574 0.00823 0.00237 -0.1259 0.6578 0.5188
-1.500 0.3843 0.00828 0.00239 -0.1256 0.6475 0.5345
-1.250 0.4114 0.00833 0.00240 -0.1254 0.6381 0.5474
-1.000 0.4384 0.00842 0.00240 -0.1252 0.6294 0.5587
-0.750 0.4658 0.00846 0.00243 -0.1251 0.6208 0.5701
-0.500 0.4927 0.00853 0.00245 -0.1248 0.6130 0.5805
-0.250 0.5200 0.00856 0.00248 -0.1247 0.6050 0.5914
0.250 0.5744 0.00867 0.00256 -0.1244 0.5907 0.6143
0.500 0.6014 0.00875 0.00260 -0.1242 0.5838 0.6254
0.750 0.6287 0.00879 0.00266 -0.1241 0.5773 0.6373
1.000 0.6558 0.00885 0.00272 -0.1239 0.5708 0.6506
1.250 0.6828 0.00892 0.00279 -0.1238 0.5647 0.6646
1.500 0.7097 0.00895 0.00286 -0.1236 0.5583 0.6791
1.750 0.7366 0.00903 0.00295 -0.1234 0.5525 0.6948
2.000 0.7634 0.00906 0.00304 -0.1232 0.5466 0.7127
2.250 0.7898 0.00910 0.00314 -0.1229 0.5405 0.7327
2.500 0.8161 0.00918 0.00325 -0.1225 0.5351 0.7571
2.750 0.8417 0.00917 0.00337 -0.1220 0.5292 0.7859
3.000 0.8663 0.00920 0.00348 -0.1213 0.5236 0.8209
3.250 0.8889 0.00921 0.00360 -0.1201 0.5183 0.8657
3.500 0.9093 0.00909 0.00366 -0.1182 0.5127 0.9452
3.750 0.9413 0.00923 0.00374 -0.1192 0.5068 1.0000
4.000 0.9684 0.00934 0.00387 -0.1192 0.5009 1.0000
4.250 0.9951 0.00947 0.00399 -0.1190 0.4947 1.0000
4.500 1.0215 0.00965 0.00412 -0.1189 0.4884 1.0000
4.750 1.0475 0.00975 0.00425 -0.1186 0.4813 1.0000
5.000 1.0732 0.00995 0.00439 -0.1183 0.4747 1.0000
5.250 1.0991 0.01004 0.00454 -0.1179 0.4676 1.0000
5.500 1.1242 0.01023 0.00469 -0.1175 0.4607 1.0000
5.750 1.1497 0.01035 0.00485 -0.1171 0.4534 1.0000
6.000 1.1741 0.01055 0.00502 -0.1166 0.4458 1.0000
6.250 1.1991 0.01068 0.00521 -0.1161 0.4379 1.0000
6.750 1.2472 0.01104 0.00559 -0.1148 0.4211 1.0000
7.000 1.2704 0.01125 0.00580 -0.1140 0.4124 1.0000
7.250 1.2935 0.01145 0.00601 -0.1132 0.4027 1.0000
7.500 1.3164 0.01166 0.00625 -0.1124 0.3928 1.0000
7.750 1.3379 0.01191 0.00650 -0.1113 0.3817 1.0000
8.000 1.3583 0.01219 0.00677 -0.1100 0.3694 1.0000
8.250 1.3777 0.01247 0.00705 -0.1086 0.3558 1.0000
8.500 1.3955 0.01281 0.00737 -0.1068 0.3403 1.0000
8.750 1.4129 0.01318 0.00773 -0.1050 0.3235 1.0000
9.000 1.4290 0.01362 0.00813 -0.1031 0.3037 1.0000
9.250 1.4415 0.01422 0.00863 -0.1006 0.2799 1.0000
9.500 1.4518 0.01496 0.00924 -0.0978 0.2516 1.0000
9.750 1.4588 0.01587 0.00999 -0.0946 0.2199 1.0000
10.000 1.4638 0.01692 0.01086 -0.0912 0.1896 1.0000
10.250 1.4683 0.01801 0.01182 -0.0879 0.1635 1.0000
10.500 1.4724 0.01914 0.01283 -0.0846 0.1408 1.0000
10.750 1.4777 0.02025 0.01386 -0.0817 0.1229 1.0000
11.000 1.4832 0.02138 0.01494 -0.0789 0.1082 1.0000
11.250 1.4882 0.02259 0.01612 -0.0763 0.0956 1.0000
11.500 1.4921 0.02392 0.01742 -0.0737 0.0845 1.0000
11.750 1.4950 0.02540 0.01888 -0.0713 0.0746 1.0000
12.000 1.4994 0.02686 0.02036 -0.0692 0.0664 1.0000
12.250 1.5023 0.02850 0.02202 -0.0671 0.0586 1.0000
12.500 1.5032 0.03042 0.02394 -0.0652 0.0523 1.0000
12.750 1.5069 0.03221 0.02578 -0.0637 0.0469 1.0000
13.000 1.5071 0.03440 0.02799 -0.0622 0.0415 1.0000
13.250 1.5081 0.03665 0.03027 -0.0610 0.0368 1.0000
13.500 1.5081 0.03910 0.03277 -0.0599 0.0326 1.0000
13.750 1.5063 0.04183 0.03553 -0.0591 0.0285 1.0000
14.000 1.5046 0.04469 0.03846 -0.0584 0.0245 1.0000
14.250 1.4988 0.04811 0.04191 -0.0579 0.0207 1.0000
14.500 1.4948 0.05144 0.04532 -0.0576 0.0180 1.0000
14.750 1.4879 0.05527 0.04922 -0.0575 0.0160 1.0000
15.000 1.4845 0.05878 0.05281 -0.0575 0.0144 1.0000
15.250 1.4759 0.06306 0.05717 -0.0578 0.0131 1.0000
15.500 1.4701 0.06713 0.06135 -0.0583 0.0124 1.0000
15.750 1.4668 0.07096 0.06528 -0.0589 0.0117 1.0000
16.000 1.4626 0.07498 0.06941 -0.0596 0.0111 1.0000
16.250 1.4576 0.07922 0.07374 -0.0605 0.0106 1.0000
16.500 1.4495 0.08404 0.07865 -0.0617 0.0102 1.0000
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Polar data table (+)
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