E71 (5.15%) (e71-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E71 (5.15%) (e71-il) Reynolds number: 200,000 Max Cl/Cd: 108.42 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e71-il-200000.txt Download as CSV file: xf-e71-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E71 (5.15%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3796 0.10200 0.09866 -0.0201 1.0000 0.0245
-7.250 -0.3888 0.10111 0.09784 -0.0189 1.0000 0.0248
-7.000 -0.3978 0.10004 0.09685 -0.0176 1.0000 0.0250
-6.750 -0.3982 0.09794 0.09479 -0.0179 1.0000 0.0251
-6.500 -0.3961 0.09567 0.09256 -0.0196 1.0000 0.0253
-6.250 -0.3913 0.09296 0.08989 -0.0217 1.0000 0.0254
-6.000 -0.3858 0.08954 0.08653 -0.0238 1.0000 0.0255
-5.750 -0.3963 0.08481 0.08183 -0.0165 1.0000 0.0273
-5.500 -0.3928 0.08251 0.07955 -0.0155 1.0000 0.0292
-5.250 -0.3863 0.07979 0.07685 -0.0169 1.0000 0.0313
-5.000 -0.3754 0.07662 0.07370 -0.0201 1.0000 0.0332
-4.750 -0.3381 0.07226 0.06928 -0.0334 1.0000 0.0364
-4.500 -0.2943 0.06747 0.06432 -0.0459 1.0000 0.0371
-4.250 -0.2772 0.06066 0.05753 -0.0498 0.9988 0.0384
-4.000 -0.2549 0.05765 0.05452 -0.0511 0.9957 0.0407
-3.750 -0.2086 0.05304 0.04979 -0.0604 0.9929 0.0453
-3.500 -0.1305 0.04462 0.04099 -0.0793 0.9919 0.0521
-3.250 -0.0976 0.04194 0.03828 -0.0828 0.9890 0.0566
-3.000 -0.0394 0.03694 0.03295 -0.0930 0.9881 0.0679
-2.750 0.0134 0.03315 0.02878 -0.1008 0.9872 0.0808
-2.500 0.0624 0.03020 0.02552 -0.1069 0.9860 0.0941
-2.250 0.1075 0.02792 0.02302 -0.1117 0.9847 0.1089
-2.000 0.1781 0.02050 0.01402 -0.1178 0.9885 0.0415
-1.750 0.2199 0.01950 0.01256 -0.1199 0.9864 0.0375
-1.500 0.2608 0.01832 0.01112 -0.1225 0.9848 0.0373
-1.250 0.3020 0.01706 0.00983 -0.1254 0.9836 0.0430
-1.000 0.3397 0.01645 0.00918 -0.1275 0.9798 0.0446
-0.750 0.3787 0.01605 0.00870 -0.1298 0.9755 0.0483
-0.500 0.4223 0.01529 0.00833 -0.1333 0.9731 0.1697
-0.250 0.4639 0.01418 0.00865 -0.1367 0.9715 0.6391
0.000 0.4870 0.01354 0.00850 -0.1351 0.9634 1.0000
0.250 0.5284 0.01361 0.00843 -0.1379 0.9590 1.0000
0.500 0.5628 0.01361 0.00834 -0.1393 0.9515 1.0000
0.750 0.6047 0.01354 0.00819 -0.1420 0.9466 1.0000
1.000 0.6397 0.01344 0.00805 -0.1434 0.9385 1.0000
1.250 0.6828 0.01321 0.00780 -0.1462 0.9335 1.0000
1.500 0.7177 0.01302 0.00764 -0.1474 0.9248 1.0000
1.750 0.7631 0.01259 0.00724 -0.1504 0.9199 1.0000
2.000 0.7985 0.01226 0.00694 -0.1515 0.9102 1.0000
2.250 0.8456 0.01163 0.00639 -0.1547 0.9059 1.0000
2.500 0.8815 0.01123 0.00611 -0.1557 0.8949 1.0000
2.750 0.9196 0.01077 0.00574 -0.1570 0.8826 1.0000
3.000 0.9588 0.01032 0.00539 -0.1585 0.8675 1.0000
3.250 0.9945 0.01002 0.00517 -0.1593 0.8450 1.0000
3.500 1.0306 0.00981 0.00504 -0.1602 0.8147 1.0000
3.750 1.0625 0.00980 0.00499 -0.1602 0.7723 1.0000
4.000 1.0893 0.01006 0.00504 -0.1591 0.7038 1.0000
4.250 1.1052 0.01097 0.00524 -0.1558 0.5715 1.0000
4.500 1.1134 0.01252 0.00584 -0.1519 0.4137 1.0000
4.750 1.1285 0.01376 0.00653 -0.1496 0.3076 1.0000
5.000 1.1433 0.01530 0.00742 -0.1476 0.1877 1.0000
5.250 1.1541 0.01787 0.00891 -0.1450 0.0398 1.0000
5.500 1.1735 0.01936 0.01041 -0.1431 0.0237 1.0000
5.750 1.1937 0.02060 0.01179 -0.1414 0.0203 1.0000
6.000 1.2110 0.02239 0.01370 -0.1393 0.0186 1.0000
6.250 1.2285 0.02480 0.01624 -0.1372 0.0179 1.0000
6.500 1.2508 0.02761 0.01919 -0.1359 0.0177 1.0000
6.750 1.2759 0.03020 0.02197 -0.1350 0.0178 1.0000
7.000 1.3006 0.03243 0.02449 -0.1339 0.0182 1.0000
7.250 1.3246 0.03450 0.02688 -0.1325 0.0189 1.0000
7.500 1.3468 0.03949 0.03270 -0.1298 0.0219 1.0000
7.750 1.3588 0.04577 0.03962 -0.1266 0.0252 1.0000
15.750 0.9677 0.22979 0.22760 -0.1588 0.0301 1.0000
16.000 0.9713 0.23374 0.23156 -0.1602 0.0295 1.0000
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Polar data table (+)
Polar graphs
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