E471 (6.25%) (e471-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E471 (6.25%) (e471-il) Reynolds number: 50,000 Max Cl/Cd: 46.81 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e471-il-50000-n5.txt Download as CSV file: xf-e471-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E471 (6.25%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3608 0.11157 0.10497 -0.0295 1.0000 0.0903
-7.750 -0.3734 0.11116 0.10470 -0.0288 1.0000 0.0913
-7.500 -0.3875 0.11080 0.10449 -0.0279 1.0000 0.0917
-7.250 -0.3905 0.10824 0.10205 -0.0275 1.0000 0.0923
-7.000 -0.3760 0.10277 0.09646 -0.0241 1.0000 0.0953
-6.750 -0.3776 0.10048 0.09424 -0.0226 1.0000 0.0977
-6.500 -0.3806 0.09839 0.09223 -0.0220 1.0000 0.1004
-6.250 -0.3860 0.09683 0.09077 -0.0236 1.0000 0.1041
-6.000 -0.3872 0.09545 0.08948 -0.0304 1.0000 0.1056
-5.750 -0.3842 0.09125 0.08534 -0.0260 1.0000 0.1071
-5.500 -0.3802 0.08816 0.08230 -0.0241 1.0000 0.1095
-5.250 -0.3752 0.08535 0.07951 -0.0245 1.0000 0.1128
-4.750 -0.3537 0.07864 0.07283 -0.0329 1.0000 0.1213
-4.500 -0.3436 0.07537 0.06957 -0.0332 1.0000 0.1234
-4.250 -0.2977 0.06645 0.06031 -0.0469 1.0000 0.0628
-4.000 -0.2570 0.05950 0.05310 -0.0572 1.0000 0.0531
-3.750 -0.2173 0.05427 0.04754 -0.0648 1.0000 0.0507
-3.500 -0.1872 0.05026 0.04338 -0.0695 1.0000 0.0538
-3.250 -0.1268 0.04404 0.03634 -0.0806 1.0000 0.0519
-3.000 -0.0880 0.04029 0.03217 -0.0852 1.0000 0.0507
-2.750 -0.0463 0.03674 0.02810 -0.0899 1.0000 0.0500
-2.500 -0.0054 0.03379 0.02454 -0.0938 1.0000 0.0496
-2.250 0.0384 0.03132 0.02134 -0.0976 0.9979 0.0496
-2.000 0.0782 0.02952 0.01898 -0.1002 0.9954 0.0500
-1.750 0.1154 0.02822 0.01720 -0.1021 0.9925 0.0511
-1.500 0.1507 0.02715 0.01587 -0.1037 0.9891 0.0530
-1.250 0.1867 0.02646 0.01494 -0.1055 0.9855 0.0573
-1.000 0.2246 0.02602 0.01430 -0.1078 0.9823 0.0706
-0.750 0.2606 0.02539 0.01366 -0.1098 0.9779 0.1078
-0.500 0.2954 0.02326 0.01381 -0.1119 0.9766 0.6238
-0.250 0.3173 0.02286 0.01355 -0.1103 0.9684 1.0000
0.000 0.3496 0.02326 0.01351 -0.1116 0.9615 1.0000
0.250 0.3862 0.02373 0.01359 -0.1137 0.9561 1.0000
0.500 0.4169 0.02411 0.01371 -0.1148 0.9483 1.0000
0.750 0.4516 0.02455 0.01392 -0.1166 0.9418 1.0000
1.000 0.4837 0.02494 0.01415 -0.1178 0.9340 1.0000
1.250 0.5156 0.02533 0.01441 -0.1191 0.9262 1.0000
1.500 0.5512 0.02571 0.01468 -0.1209 0.9190 1.0000
1.750 0.5809 0.02607 0.01499 -0.1216 0.9096 1.0000
2.000 0.6149 0.02641 0.01529 -0.1230 0.9014 1.0000
2.250 0.6496 0.02669 0.01560 -0.1245 0.8926 1.0000
2.500 0.6796 0.02699 0.01593 -0.1251 0.8819 1.0000
2.750 0.7116 0.02724 0.01624 -0.1260 0.8715 1.0000
3.000 0.7466 0.02738 0.01649 -0.1272 0.8615 1.0000
3.250 0.7839 0.02740 0.01669 -0.1286 0.8513 1.0000
3.500 0.8161 0.02744 0.01688 -0.1291 0.8385 1.0000
3.750 0.8497 0.02736 0.01699 -0.1297 0.8253 1.0000
4.000 0.8845 0.02713 0.01697 -0.1302 0.8115 1.0000
4.250 0.9195 0.02679 0.01697 -0.1304 0.7961 1.0000
4.500 0.9482 0.02660 0.01701 -0.1297 0.7766 1.0000
4.750 0.9857 0.02597 0.01668 -0.1299 0.7576 1.0000
5.000 1.0146 0.02559 0.01659 -0.1287 0.7328 1.0000
5.250 1.0459 0.02503 0.01631 -0.1276 0.7033 1.0000
5.500 1.0736 0.02465 0.01631 -0.1259 0.6641 1.0000
5.750 1.1028 0.02426 0.01608 -0.1243 0.6103 1.0000
6.000 1.1319 0.02418 0.01589 -0.1225 0.5303 1.0000
6.250 1.1516 0.02499 0.01627 -0.1198 0.4358 1.0000
6.500 1.1623 0.02649 0.01731 -0.1167 0.3488 1.0000
6.750 1.1700 0.02831 0.01871 -0.1136 0.2696 1.0000
7.000 1.1776 0.03039 0.02037 -0.1108 0.1991 1.0000
7.250 1.1848 0.03286 0.02236 -0.1083 0.1322 1.0000
7.500 1.1936 0.03553 0.02442 -0.1063 0.0696 1.0000
7.750 1.2062 0.03804 0.02682 -0.1044 0.0462 1.0000
8.000 1.2200 0.04053 0.02964 -0.1022 0.0384 1.0000
8.250 1.2364 0.04300 0.03233 -0.1005 0.0340 1.0000
8.500 1.2558 0.04612 0.03555 -0.0993 0.0311 1.0000
8.750 1.2851 0.04949 0.03942 -0.0988 0.0293 1.0000
9.000 1.3074 0.05318 0.04363 -0.0978 0.0278 1.0000
9.250 1.3205 0.05682 0.04778 -0.0960 0.0261 1.0000
9.500 1.3269 0.06035 0.05174 -0.0938 0.0247 1.0000
9.750 1.3267 0.06373 0.05550 -0.0911 0.0236 1.0000
10.000 1.3221 0.06720 0.05931 -0.0882 0.0228 1.0000
10.250 1.3140 0.07084 0.06328 -0.0855 0.0223 1.0000
10.500 1.3028 0.07484 0.06761 -0.0831 0.0221 1.0000
10.750 1.2888 0.07921 0.07229 -0.0813 0.0220 1.0000
11.000 1.2723 0.08406 0.07745 -0.0802 0.0220 1.0000
11.250 1.2535 0.08951 0.08319 -0.0803 0.0221 1.0000
11.500 1.2327 0.09575 0.08971 -0.0816 0.0224 1.0000
11.750 1.2096 0.10317 0.09739 -0.0846 0.0229 1.0000
12.000 1.1819 0.11279 0.10724 -0.0902 0.0241 1.0000
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Polar data table (+)
Polar graphs
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