E210 (13.64%) (e210-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E210 (13.64%) (e210-il) Reynolds number: 500,000 Max Cl/Cd: 109.02 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e210-il-500000-n5.txt Download as CSV file: xf-e210-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6800 0.04928 0.04638 -0.0791 0.9967 0.0089
-11.750 -0.6848 0.04187 0.03873 -0.0892 0.9931 0.0089
-11.500 -0.6854 0.03670 0.03333 -0.0965 0.9877 0.0090
-11.250 -0.6718 0.03299 0.02938 -0.1034 0.9836 0.0092
-11.000 -0.6630 0.03056 0.02675 -0.1046 0.9771 0.0094
-10.750 -0.6420 0.02835 0.02430 -0.1072 0.9737 0.0097
-10.500 -0.6163 0.02635 0.02204 -0.1099 0.9716 0.0101
-10.250 -0.6042 0.02488 0.02039 -0.1088 0.9647 0.0104
-10.000 -0.5783 0.02354 0.01883 -0.1101 0.9614 0.0108
-9.500 -0.5343 0.02116 0.01618 -0.1106 0.9515 0.0115
-9.250 -0.5061 0.02043 0.01539 -0.1115 0.9477 0.0119
-9.000 -0.4823 0.01964 0.01451 -0.1115 0.9419 0.0123
-8.750 -0.4586 0.01886 0.01364 -0.1113 0.9351 0.0128
-8.500 -0.4331 0.01802 0.01268 -0.1114 0.9290 0.0132
-8.250 -0.4070 0.01721 0.01175 -0.1116 0.9216 0.0137
-8.000 -0.3755 0.01642 0.01083 -0.1128 0.9159 0.0142
-7.750 -0.3424 0.01584 0.01014 -0.1142 0.9085 0.0146
-7.500 -0.3031 0.01471 0.00894 -0.1174 0.9022 0.0155
-7.250 -0.2623 0.01405 0.00821 -0.1205 0.8928 0.0162
-7.000 -0.2216 0.01340 0.00745 -0.1236 0.8805 0.0170
-6.750 -0.1839 0.01285 0.00677 -0.1259 0.8635 0.0176
-6.500 -0.1514 0.01246 0.00622 -0.1271 0.8433 0.0183
-6.250 -0.1230 0.01217 0.00577 -0.1273 0.8218 0.0189
-6.000 -0.0974 0.01173 0.00519 -0.1272 0.8006 0.0199
-5.750 -0.0719 0.01147 0.00480 -0.1268 0.7803 0.0207
-5.500 -0.0466 0.01125 0.00445 -0.1264 0.7612 0.0216
-5.250 -0.0213 0.01107 0.00414 -0.1259 0.7437 0.0226
-5.000 0.0042 0.01091 0.00386 -0.1255 0.7269 0.0236
-4.750 0.0297 0.01073 0.00358 -0.1251 0.7114 0.0257
-4.500 0.0555 0.01057 0.00334 -0.1247 0.6972 0.0288
-4.250 0.0815 0.01039 0.00312 -0.1244 0.6839 0.0359
-4.000 0.1074 0.01019 0.00292 -0.1241 0.6713 0.0533
-3.750 0.1335 0.01003 0.00275 -0.1239 0.6597 0.0723
-3.500 0.1599 0.00987 0.00261 -0.1237 0.6485 0.0938
-3.250 0.1865 0.00968 0.00247 -0.1236 0.6382 0.1244
-3.000 0.2129 0.00948 0.00235 -0.1235 0.6284 0.1641
-2.750 0.2395 0.00926 0.00224 -0.1235 0.6191 0.2112
-2.500 0.2664 0.00909 0.00214 -0.1234 0.6104 0.2557
-2.250 0.2929 0.00887 0.00207 -0.1234 0.6017 0.3160
-2.000 0.3199 0.00868 0.00205 -0.1234 0.5941 0.3862
-1.750 0.3469 0.00863 0.00206 -0.1233 0.5863 0.4300
-1.500 0.3743 0.00862 0.00208 -0.1232 0.5792 0.4575
-1.250 0.4015 0.00865 0.00208 -0.1230 0.5720 0.4760
-1.000 0.4290 0.00868 0.00209 -0.1229 0.5658 0.4894
-0.750 0.4564 0.00872 0.00210 -0.1228 0.5590 0.5014
-0.500 0.4836 0.00877 0.00212 -0.1227 0.5529 0.5130
-0.250 0.5113 0.00880 0.00214 -0.1226 0.5468 0.5242
0.000 0.5384 0.00885 0.00218 -0.1225 0.5408 0.5352
0.250 0.5658 0.00889 0.00222 -0.1224 0.5352 0.5463
0.500 0.5932 0.00894 0.00226 -0.1223 0.5293 0.5567
0.750 0.6201 0.00901 0.00231 -0.1221 0.5240 0.5667
1.000 0.6476 0.00904 0.00237 -0.1220 0.5187 0.5779
1.500 0.7015 0.00917 0.00250 -0.1217 0.5078 0.6000
1.750 0.7289 0.00921 0.00257 -0.1216 0.5026 0.6101
2.250 0.7824 0.00936 0.00274 -0.1212 0.4920 0.6324
2.500 0.8095 0.00941 0.00284 -0.1211 0.4868 0.6448
2.750 0.8360 0.00948 0.00294 -0.1208 0.4813 0.6590
3.000 0.8625 0.00956 0.00305 -0.1206 0.4764 0.6741
3.250 0.8891 0.00961 0.00317 -0.1204 0.4709 0.6905
3.500 0.9151 0.00969 0.00330 -0.1200 0.4655 0.7097
3.750 0.9410 0.00976 0.00344 -0.1197 0.4603 0.7319
4.000 0.9667 0.00981 0.00358 -0.1193 0.4543 0.7573
4.250 0.9910 0.00990 0.00373 -0.1186 0.4482 0.7859
4.500 1.0155 0.00993 0.00388 -0.1179 0.4415 0.8208
4.750 1.0363 0.00997 0.00403 -0.1163 0.4341 0.8689
5.000 1.0613 0.00992 0.00413 -0.1156 0.4262 1.0000
5.500 1.1119 0.01027 0.00445 -0.1149 0.4103 1.0000
5.750 1.1362 0.01047 0.00463 -0.1143 0.4020 1.0000
6.000 1.1610 0.01066 0.00483 -0.1138 0.3925 1.0000
6.250 1.1850 0.01087 0.00503 -0.1132 0.3827 1.0000
6.500 1.2082 0.01112 0.00525 -0.1125 0.3721 1.0000
6.750 1.2311 0.01137 0.00549 -0.1117 0.3600 1.0000
7.000 1.2538 0.01164 0.00574 -0.1108 0.3477 1.0000
7.250 1.2756 0.01193 0.00601 -0.1098 0.3346 1.0000
7.500 1.2955 0.01227 0.00631 -0.1085 0.3188 1.0000
7.750 1.3139 0.01266 0.00664 -0.1069 0.3016 1.0000
8.000 1.3309 0.01311 0.00703 -0.1051 0.2816 1.0000
8.250 1.3452 0.01370 0.00750 -0.1029 0.2564 1.0000
8.500 1.3582 0.01436 0.00805 -0.1005 0.2296 1.0000
8.750 1.3695 0.01512 0.00866 -0.0979 0.2027 1.0000
9.000 1.3817 0.01583 0.00929 -0.0955 0.1821 1.0000
9.250 1.3925 0.01660 0.00998 -0.0930 0.1614 1.0000
9.500 1.4017 0.01747 0.01074 -0.0902 0.1409 1.0000
9.750 1.4107 0.01834 0.01154 -0.0876 0.1222 1.0000
10.000 1.4181 0.01932 0.01243 -0.0848 0.1051 1.0000
10.500 1.4333 0.02131 0.01433 -0.0796 0.0792 1.0000
10.750 1.4400 0.02241 0.01541 -0.0771 0.0684 1.0000
11.000 1.4472 0.02353 0.01652 -0.0749 0.0599 1.0000
11.250 1.4530 0.02478 0.01777 -0.0726 0.0521 1.0000
11.500 1.4575 0.02619 0.01918 -0.0704 0.0453 1.0000
11.750 1.4645 0.02750 0.02053 -0.0686 0.0405 1.0000
12.000 1.4685 0.02911 0.02216 -0.0668 0.0356 1.0000
12.250 1.4731 0.03076 0.02384 -0.0652 0.0313 1.0000
12.500 1.4768 0.03257 0.02569 -0.0637 0.0279 1.0000
12.750 1.4799 0.03453 0.02770 -0.0624 0.0243 1.0000
13.000 1.4829 0.03659 0.02981 -0.0613 0.0219 1.0000
13.250 1.4857 0.03877 0.03205 -0.0603 0.0193 1.0000
13.500 1.4867 0.04121 0.03455 -0.0595 0.0170 1.0000
13.750 1.4877 0.04375 0.03716 -0.0588 0.0145 1.0000
14.000 1.4877 0.04650 0.03996 -0.0583 0.0125 1.0000
14.250 1.4869 0.04941 0.04294 -0.0580 0.0107 1.0000
14.500 1.4860 0.05242 0.04603 -0.0578 0.0093 1.0000
14.750 1.4851 0.05554 0.04922 -0.0577 0.0083 1.0000
15.000 1.4830 0.05887 0.05263 -0.0578 0.0074 1.0000
15.250 1.4817 0.06220 0.05605 -0.0580 0.0067 1.0000
15.500 1.4794 0.06573 0.05968 -0.0584 0.0062 1.0000
15.750 1.4763 0.06947 0.06351 -0.0589 0.0058 1.0000
16.000 1.4739 0.07319 0.06734 -0.0595 0.0054 1.0000
16.250 1.4723 0.07686 0.07111 -0.0602 0.0052 1.0000
16.500 1.4702 0.08071 0.07507 -0.0611 0.0050 1.0000
16.750 1.4668 0.08480 0.07925 -0.0621 0.0047 1.0000
17.000 1.4632 0.08901 0.08357 -0.0633 0.0045 1.0000
17.250 1.4591 0.09337 0.08803 -0.0646 0.0044 1.0000
17.500 1.4538 0.09799 0.09276 -0.0661 0.0042 1.0000
17.750 1.4487 0.10269 0.09756 -0.0677 0.0041 1.0000
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Polar data table (+)
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