E210 (13.64%) (e210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E210 (13.64%) (e210-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.52 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e210-il-1000000-n5.txt Download as CSV file: xf-e210-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.8459 0.06567 0.06318 -0.0694 1.0000 0.0059
-14.750 -0.8897 0.05545 0.05279 -0.0750 1.0000 0.0058
-14.500 -0.9204 0.04711 0.04427 -0.0809 0.9996 0.0059
-14.250 -0.9307 0.04055 0.03753 -0.0879 0.9981 0.0058
-14.000 -0.9329 0.03505 0.03186 -0.0948 0.9959 0.0059
-13.750 -0.9210 0.03141 0.02809 -0.1008 0.9941 0.0061
-13.500 -0.9139 0.02810 0.02461 -0.1056 0.9891 0.0061
-13.250 -0.8854 0.02633 0.02275 -0.1099 0.9861 0.0064
-13.000 -0.8512 0.02491 0.02124 -0.1139 0.9844 0.0066
-12.750 -0.8306 0.02362 0.01985 -0.1150 0.9813 0.0067
-12.500 -0.8102 0.02272 0.01889 -0.1153 0.9780 0.0069
-12.250 -0.7861 0.02169 0.01775 -0.1164 0.9758 0.0071
-12.000 -0.7586 0.02089 0.01688 -0.1177 0.9743 0.0074
-11.750 -0.7297 0.02002 0.01591 -0.1192 0.9731 0.0076
-11.500 -0.7000 0.01918 0.01498 -0.1208 0.9721 0.0078
-11.250 -0.6842 0.01858 0.01431 -0.1192 0.9678 0.0080
-11.000 -0.6615 0.01787 0.01352 -0.1191 0.9642 0.0081
-10.750 -0.6349 0.01696 0.01252 -0.1200 0.9618 0.0085
-10.500 -0.6048 0.01635 0.01186 -0.1211 0.9602 0.0088
-10.250 -0.5730 0.01582 0.01130 -0.1225 0.9588 0.0090
-10.000 -0.5608 0.01546 0.01090 -0.1196 0.9502 0.0093
-9.750 -0.5328 0.01493 0.01032 -0.1202 0.9466 0.0096
-9.500 -0.5116 0.01448 0.00982 -0.1191 0.9389 0.0099
-9.250 -0.4803 0.01398 0.00926 -0.1202 0.9338 0.0102
-9.000 -0.4462 0.01349 0.00870 -0.1219 0.9278 0.0106
-8.750 -0.4060 0.01307 0.00821 -0.1248 0.9204 0.0109
-8.500 -0.3657 0.01239 0.00742 -0.1280 0.9082 0.0114
-8.250 -0.3291 0.01189 0.00681 -0.1302 0.8896 0.0119
-8.000 -0.2997 0.01159 0.00638 -0.1307 0.8640 0.0123
-7.750 -0.2743 0.01139 0.00602 -0.1304 0.8373 0.0126
-7.500 -0.2503 0.01120 0.00569 -0.1297 0.8128 0.0130
-7.250 -0.2261 0.01103 0.00540 -0.1291 0.7904 0.0135
-7.000 -0.2021 0.01087 0.00510 -0.1284 0.7687 0.0140
-6.750 -0.1774 0.01072 0.00484 -0.1279 0.7491 0.0143
-6.500 -0.1524 0.01056 0.00457 -0.1274 0.7310 0.0145
-6.250 -0.1276 0.01028 0.00417 -0.1269 0.7143 0.0151
-6.000 -0.1024 0.01006 0.00386 -0.1265 0.6982 0.0157
-5.750 -0.0765 0.00989 0.00361 -0.1262 0.6839 0.0164
-5.500 -0.0503 0.00975 0.00339 -0.1259 0.6709 0.0171
-5.250 -0.0240 0.00961 0.00318 -0.1257 0.6581 0.0176
-5.000 0.0025 0.00950 0.00298 -0.1254 0.6460 0.0182
-4.750 0.0295 0.00939 0.00280 -0.1253 0.6350 0.0188
-4.500 0.0564 0.00926 0.00261 -0.1251 0.6249 0.0198
-4.250 0.0832 0.00915 0.00244 -0.1250 0.6148 0.0216
-4.000 0.1106 0.00904 0.00230 -0.1249 0.6055 0.0238
-3.750 0.1376 0.00889 0.00216 -0.1248 0.5972 0.0331
-3.500 0.1647 0.00872 0.00202 -0.1248 0.5885 0.0526
-3.250 0.1921 0.00859 0.00192 -0.1247 0.5809 0.0689
-3.000 0.2194 0.00846 0.00182 -0.1247 0.5733 0.0894
-2.750 0.2468 0.00833 0.00174 -0.1247 0.5666 0.1162
-2.500 0.2743 0.00818 0.00166 -0.1248 0.5594 0.1484
-2.250 0.3016 0.00802 0.00159 -0.1248 0.5532 0.1887
-2.000 0.3293 0.00784 0.00154 -0.1249 0.5473 0.2342
-1.750 0.3568 0.00773 0.00149 -0.1249 0.5408 0.2733
-1.500 0.3844 0.00759 0.00146 -0.1250 0.5353 0.3168
-1.250 0.4119 0.00738 0.00145 -0.1251 0.5296 0.3935
-0.750 0.4674 0.00734 0.00149 -0.1251 0.5187 0.4515
-0.500 0.4952 0.00737 0.00151 -0.1251 0.5130 0.4641
-0.250 0.5227 0.00740 0.00153 -0.1250 0.5081 0.4757
0.000 0.5508 0.00742 0.00156 -0.1251 0.5032 0.4862
0.500 0.6059 0.00751 0.00163 -0.1249 0.4925 0.5065
0.750 0.6338 0.00753 0.00167 -0.1249 0.4880 0.5165
1.000 0.6614 0.00758 0.00171 -0.1249 0.4827 0.5259
1.250 0.6887 0.00764 0.00177 -0.1248 0.4775 0.5343
1.500 0.7164 0.00768 0.00182 -0.1248 0.4729 0.5442
1.750 0.7438 0.00772 0.00188 -0.1247 0.4677 0.5555
2.000 0.7709 0.00779 0.00195 -0.1246 0.4624 0.5653
2.500 0.8256 0.00790 0.00210 -0.1244 0.4524 0.5833
2.750 0.8525 0.00798 0.00218 -0.1243 0.4471 0.5924
3.000 0.8798 0.00804 0.00226 -0.1242 0.4418 0.6025
3.250 0.9066 0.00812 0.00236 -0.1240 0.4358 0.6137
3.500 0.9333 0.00819 0.00246 -0.1238 0.4299 0.6261
3.750 0.9599 0.00828 0.00256 -0.1236 0.4224 0.6389
4.000 0.9861 0.00838 0.00268 -0.1234 0.4146 0.6528
4.250 1.0122 0.00849 0.00281 -0.1231 0.4059 0.6686
4.500 1.0382 0.00858 0.00294 -0.1228 0.3984 0.6874
4.750 1.0638 0.00870 0.00308 -0.1224 0.3895 0.7087
5.000 1.0895 0.00879 0.00324 -0.1221 0.3811 0.7315
5.250 1.1144 0.00892 0.00340 -0.1216 0.3721 0.7572
5.500 1.1390 0.00904 0.00358 -0.1210 0.3611 0.7878
5.750 1.1627 0.00915 0.00377 -0.1203 0.3504 0.8266
6.000 1.1837 0.00924 0.00397 -0.1189 0.3390 0.8814
6.250 1.2058 0.00931 0.00414 -0.1178 0.3261 1.0000
6.500 1.2294 0.00958 0.00435 -0.1171 0.3126 1.0000
6.750 1.2520 0.00990 0.00460 -0.1163 0.2948 1.0000
7.000 1.2735 0.01027 0.00489 -0.1153 0.2745 1.0000
7.250 1.2937 0.01071 0.00521 -0.1140 0.2525 1.0000
7.500 1.3114 0.01126 0.00562 -0.1124 0.2248 1.0000
7.750 1.3267 0.01185 0.00606 -0.1102 0.1974 1.0000
8.000 1.3404 0.01247 0.00654 -0.1078 0.1710 1.0000
8.250 1.3548 0.01304 0.00700 -0.1056 0.1496 1.0000
8.500 1.3679 0.01367 0.00752 -0.1031 0.1288 1.0000
8.750 1.3817 0.01424 0.00801 -0.1009 0.1119 1.0000
9.000 1.3948 0.01487 0.00855 -0.0985 0.0957 1.0000
9.250 1.4079 0.01547 0.00910 -0.0962 0.0830 1.0000
9.500 1.4205 0.01611 0.00969 -0.0939 0.0712 1.0000
9.750 1.4317 0.01682 0.01034 -0.0914 0.0597 1.0000
10.000 1.4434 0.01751 0.01099 -0.0890 0.0506 1.0000
10.250 1.4541 0.01826 0.01171 -0.0866 0.0431 1.0000
10.750 1.4758 0.01979 0.01324 -0.0822 0.0322 1.0000
11.000 1.4854 0.02066 0.01412 -0.0799 0.0278 1.0000
11.250 1.4945 0.02160 0.01506 -0.0777 0.0240 1.0000
11.500 1.5038 0.02255 0.01603 -0.0756 0.0211 1.0000
11.750 1.5114 0.02366 0.01716 -0.0735 0.0183 1.0000
12.000 1.5184 0.02486 0.01839 -0.0715 0.0152 1.0000
12.250 1.5238 0.02624 0.01979 -0.0694 0.0125 1.0000
12.500 1.5279 0.02779 0.02137 -0.0675 0.0098 1.0000
12.750 1.5315 0.02948 0.02309 -0.0657 0.0075 1.0000
13.000 1.5345 0.03130 0.02496 -0.0642 0.0059 1.0000
13.250 1.5389 0.03310 0.02682 -0.0628 0.0051 1.0000
13.500 1.5432 0.03501 0.02879 -0.0617 0.0046 1.0000
13.750 1.5460 0.03714 0.03098 -0.0607 0.0041 1.0000
14.000 1.5496 0.03928 0.03319 -0.0599 0.0038 1.0000
14.250 1.5531 0.04151 0.03550 -0.0592 0.0037 1.0000
14.500 1.5555 0.04393 0.03799 -0.0587 0.0035 1.0000
14.750 1.5578 0.04645 0.04059 -0.0583 0.0033 1.0000
15.000 1.5586 0.04919 0.04341 -0.0580 0.0032 1.0000
15.250 1.5587 0.05210 0.04640 -0.0578 0.0030 1.0000
15.500 1.5580 0.05519 0.04957 -0.0578 0.0029 1.0000
15.750 1.5578 0.05830 0.05276 -0.0579 0.0028 1.0000
16.000 1.5551 0.06181 0.05636 -0.0582 0.0027 1.0000
16.250 1.5548 0.06508 0.05972 -0.0585 0.0027 1.0000
16.500 1.5541 0.06848 0.06320 -0.0590 0.0026 1.0000
16.750 1.5525 0.07207 0.06688 -0.0596 0.0025 1.0000
17.000 1.5504 0.07579 0.07070 -0.0604 0.0025 1.0000
17.250 1.5482 0.07962 0.07461 -0.0612 0.0024 1.0000
17.500 1.5456 0.08358 0.07867 -0.0622 0.0024 1.0000
17.750 1.5418 0.08779 0.08299 -0.0634 0.0024 1.0000
18.000 1.5382 0.09203 0.08731 -0.0647 0.0023 1.0000
18.250 1.5339 0.09646 0.09184 -0.0661 0.0023 1.0000
18.500 1.5293 0.10099 0.09647 -0.0677 0.0022 1.0000
18.750 1.5249 0.10556 0.10113 -0.0693 0.0022 1.0000
19.000 1.5193 0.11037 0.10604 -0.0712 0.0022 1.0000
19.250 1.5141 0.11515 0.11092 -0.0732 0.0021 1.0000
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Polar data table (+)
Polar graphs
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