E471 (6.25%) (e471-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: E471 (6.25%) (e471-il) Reynolds number: 100,000 Max Cl/Cd: 71.98 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e471-il-100000-n5.txt Download as CSV file: xf-e471-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3792 0.11129 0.10670 -0.0297 1.0000 0.0381
-7.750 -0.3881 0.10993 0.10543 -0.0281 1.0000 0.0382
-7.500 -0.3949 0.10823 0.10381 -0.0273 1.0000 0.0383
-7.250 -0.3978 0.10533 0.10101 -0.0270 1.0000 0.0384
-7.000 -0.3882 0.09909 0.09473 -0.0220 1.0000 0.0401
-6.750 -0.3908 0.09684 0.09247 -0.0199 1.0000 0.0409
-6.500 -0.3865 0.09408 0.08974 -0.0203 0.9987 0.0422
-6.250 -0.3674 0.09011 0.08577 -0.0252 0.9943 0.0442
-6.000 -0.3481 0.08608 0.08173 -0.0309 0.9888 0.0464
-5.750 -0.2997 0.08063 0.07619 -0.0534 0.9810 0.0513
-5.500 -0.2901 0.07567 0.07128 -0.0535 0.9767 0.0529
-5.250 -0.2766 0.07266 0.06827 -0.0522 0.9732 0.0558
-5.000 -0.2456 0.06807 0.06362 -0.0596 0.9697 0.0584
-4.750 -0.2177 0.06351 0.05898 -0.0667 0.9637 0.0604
-4.500 -0.1481 0.05173 0.04675 -0.0880 0.9603 0.0393
-4.250 -0.1198 0.04825 0.04319 -0.0910 0.9577 0.0341
-4.000 -0.0690 0.04125 0.03579 -0.1013 0.9556 0.0306
-3.750 -0.0082 0.03328 0.02685 -0.1121 0.9548 0.0276
-3.500 0.0329 0.02980 0.02275 -0.1164 0.9523 0.0274
-3.250 0.0671 0.02805 0.02083 -0.1194 0.9494 0.0310
-3.000 0.1074 0.02583 0.01806 -0.1226 0.9475 0.0329
-2.750 0.1475 0.02374 0.01537 -0.1252 0.9459 0.0325
-2.500 0.1856 0.02224 0.01347 -0.1273 0.9443 0.0324
-2.250 0.2159 0.02120 0.01223 -0.1279 0.9402 0.0326
-2.000 0.2487 0.02035 0.01122 -0.1290 0.9366 0.0331
-1.750 0.2839 0.01967 0.01040 -0.1305 0.9337 0.0342
-1.500 0.3206 0.01914 0.00967 -0.1324 0.9313 0.0361
-1.250 0.3488 0.01880 0.00921 -0.1326 0.9258 0.0401
-1.000 0.3829 0.01834 0.00879 -0.1339 0.9220 0.0641
-0.750 0.4207 0.01730 0.00883 -0.1368 0.9198 0.3629
-0.500 0.4400 0.01607 0.00896 -0.1344 0.9160 0.8147
-0.250 0.4656 0.01595 0.00874 -0.1338 0.9088 1.0000
0.000 0.5023 0.01598 0.00857 -0.1355 0.9054 1.0000
0.250 0.5298 0.01612 0.00857 -0.1355 0.8982 1.0000
0.500 0.5648 0.01613 0.00845 -0.1369 0.8937 1.0000
0.750 0.5970 0.01617 0.00839 -0.1377 0.8881 1.0000
1.000 0.6286 0.01620 0.00835 -0.1384 0.8817 1.0000
1.250 0.6675 0.01606 0.00817 -0.1404 0.8781 1.0000
1.500 0.6944 0.01614 0.00825 -0.1401 0.8690 1.0000
1.750 0.7340 0.01596 0.00806 -0.1421 0.8646 1.0000
2.000 0.7616 0.01599 0.00811 -0.1419 0.8547 1.0000
2.250 0.7940 0.01589 0.00805 -0.1424 0.8463 1.0000
2.500 0.8301 0.01567 0.00793 -0.1435 0.8383 1.0000
2.750 0.8596 0.01560 0.00792 -0.1435 0.8267 1.0000
3.000 0.8904 0.01548 0.00788 -0.1436 0.8142 1.0000
3.250 0.9215 0.01534 0.00783 -0.1436 0.8003 1.0000
3.500 0.9531 0.01519 0.00784 -0.1438 0.7847 1.0000
3.750 0.9811 0.01515 0.00790 -0.1433 0.7651 1.0000
4.000 1.0121 0.01503 0.00787 -0.1432 0.7428 1.0000
4.250 1.0395 0.01502 0.00795 -0.1425 0.7140 1.0000
4.500 1.0672 0.01505 0.00801 -0.1418 0.6767 1.0000
4.750 1.0941 0.01520 0.00811 -0.1408 0.6253 1.0000
5.000 1.1184 0.01560 0.00837 -0.1395 0.5542 1.0000
5.250 1.1373 0.01641 0.00879 -0.1373 0.4708 1.0000
5.500 1.1519 0.01754 0.00947 -0.1348 0.3832 1.0000
5.750 1.1621 0.01912 0.01036 -0.1319 0.2750 1.0000
6.000 1.1743 0.02073 0.01136 -0.1297 0.1824 1.0000
6.250 1.1887 0.02227 0.01242 -0.1279 0.1103 1.0000
6.500 1.2028 0.02395 0.01369 -0.1259 0.0526 1.0000
6.750 1.2171 0.02576 0.01537 -0.1236 0.0280 1.0000
7.000 1.2318 0.02747 0.01717 -0.1214 0.0210 1.0000
7.250 1.2480 0.02887 0.01887 -0.1195 0.0172 1.0000
7.500 1.2636 0.03032 0.02049 -0.1176 0.0149 1.0000
7.750 1.2765 0.03211 0.02246 -0.1154 0.0139 1.0000
8.000 1.2877 0.03433 0.02484 -0.1129 0.0133 1.0000
8.250 1.3026 0.03645 0.02718 -0.1110 0.0129 1.0000
8.500 1.3196 0.03887 0.02986 -0.1093 0.0126 1.0000
8.750 1.3377 0.04164 0.03294 -0.1078 0.0123 1.0000
9.000 1.3545 0.04477 0.03645 -0.1063 0.0121 1.0000
9.250 1.3674 0.04823 0.04034 -0.1043 0.0119 1.0000
9.500 1.3746 0.05182 0.04438 -0.1017 0.0118 1.0000
9.750 1.3750 0.05548 0.04848 -0.0985 0.0118 1.0000
10.000 1.3695 0.05910 0.05251 -0.0948 0.0118 1.0000
10.250 1.3600 0.06280 0.05658 -0.0912 0.0118 1.0000
10.500 1.3473 0.06673 0.06085 -0.0880 0.0118 1.0000
10.750 1.3323 0.07095 0.06540 -0.0854 0.0118 1.0000
11.000 1.3155 0.07554 0.07029 -0.0837 0.0118 1.0000
11.250 1.2968 0.08067 0.07569 -0.0830 0.0118 1.0000
11.500 1.2775 0.08626 0.08153 -0.0834 0.0118 1.0000
11.750 1.2579 0.09243 0.08794 -0.0851 0.0119 1.0000
12.000 1.2382 0.09929 0.09499 -0.0880 0.0121 1.0000
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Polar data table (+)
Polar graphs
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