EPPLER 855 AIRFOIL (e855-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER 855 AIRFOIL (e855-il) Reynolds number: 50,000 Max Cl/Cd: 5.67 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e855-il-50000.txt Download as CSV file: xf-e855-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 855 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3183 0.11854 0.11219 -0.0329 1.0000 0.2944
-9.250 -0.2916 0.11292 0.10656 -0.0317 1.0000 0.3018
-9.000 -0.3203 0.11296 0.10678 -0.0304 1.0000 0.3094
-8.750 -0.3001 0.10794 0.10178 -0.0292 1.0000 0.3146
-8.500 -0.3050 0.10545 0.09939 -0.0278 1.0000 0.3179
-8.250 -0.5001 0.08451 0.07909 -0.0477 1.0000 0.1304
-8.000 -0.5165 0.08129 0.07595 -0.0464 1.0000 0.1264
-7.750 -0.5865 0.07404 0.06849 -0.0502 1.0000 0.1138
-7.500 -0.5958 0.07062 0.06506 -0.0491 1.0000 0.1129
-7.250 -0.6066 0.06677 0.06109 -0.0487 1.0000 0.1119
-7.000 -0.6130 0.06283 0.05696 -0.0487 1.0000 0.1105
-6.750 -0.6156 0.05851 0.05231 -0.0493 1.0000 0.1097
-6.500 -0.6119 0.05428 0.04763 -0.0500 1.0000 0.1093
-6.250 -0.6021 0.05040 0.04325 -0.0506 1.0000 0.1095
-6.000 -0.5883 0.04707 0.03930 -0.0512 1.0000 0.1122
-5.750 -0.5726 0.04417 0.03600 -0.0513 1.0000 0.1170
-5.500 -0.5560 0.04218 0.03387 -0.0508 1.0000 0.1229
-5.250 -0.5373 0.04003 0.03130 -0.0507 1.0000 0.1317
-5.000 -0.4957 0.03811 0.02924 -0.0540 0.9920 0.1492
-4.750 -0.4531 0.03647 0.02749 -0.0572 0.9834 0.1766
-4.500 -0.4172 0.03495 0.02619 -0.0593 0.9743 0.2152
-4.250 -0.3834 0.03350 0.02537 -0.0612 0.9654 0.2838
-4.000 -0.3556 0.03422 0.02718 -0.0601 0.9558 0.4252
-3.750 -0.3337 0.03671 0.02981 -0.0561 0.9458 0.5130
-3.500 -0.3161 0.03838 0.03147 -0.0519 0.9361 0.5609
-3.250 -0.3017 0.03947 0.03249 -0.0479 0.9268 0.5963
-3.000 -0.2785 0.04039 0.03323 -0.0457 0.9186 0.6332
-2.750 -0.2682 0.04088 0.03368 -0.0415 0.9099 0.6577
-2.500 -0.2501 0.04132 0.03396 -0.0390 0.9023 0.6854
-2.250 -0.2349 0.04153 0.03402 -0.0368 0.8945 0.7118
-2.000 -0.2206 0.04178 0.03418 -0.0336 0.8874 0.7341
-1.750 -0.2065 0.04184 0.03410 -0.0317 0.8800 0.7558
-1.500 -0.1844 0.04195 0.03405 -0.0310 0.8737 0.7759
-1.250 -0.1737 0.04194 0.03392 -0.0291 0.8667 0.7917
-1.000 -0.1440 0.04209 0.03390 -0.0301 0.8605 0.8087
-0.750 -0.1345 0.04217 0.03387 -0.0288 0.8545 0.8221
-0.500 -0.1124 0.04235 0.03390 -0.0292 0.8486 0.8367
-0.250 -0.0879 0.04263 0.03404 -0.0300 0.8428 0.8512
0.000 -0.0759 0.04289 0.03422 -0.0292 0.8378 0.8654
0.250 -0.0515 0.04326 0.03450 -0.0301 0.8326 0.8812
0.500 -0.0268 0.04373 0.03488 -0.0311 0.8276 0.8986
0.750 -0.0085 0.04426 0.03538 -0.0318 0.8231 0.9172
1.000 0.0322 0.04512 0.03618 -0.0364 0.8178 0.9402
1.250 0.0866 0.04635 0.03731 -0.0440 0.8114 0.9665
1.500 0.1131 0.04727 0.03817 -0.0480 0.8075 1.0000
1.750 0.1302 0.04824 0.03901 -0.0503 0.8055 1.0000
2.000 0.1605 0.04949 0.04012 -0.0544 0.8021 1.0000
2.250 0.1952 0.05095 0.04143 -0.0589 0.7978 1.0000
2.500 0.2160 0.05254 0.04289 -0.0616 0.7976 1.0000
2.750 0.2383 0.05428 0.04450 -0.0643 0.7982 1.0000
3.000 0.1006 0.05553 0.04599 -0.0488 0.9456 1.0000
3.250 0.1301 0.05727 0.04758 -0.0521 0.9366 1.0000
3.500 0.1539 0.05892 0.04910 -0.0542 0.9297 1.0000
3.750 0.1869 0.06128 0.05131 -0.0577 0.9211 1.0000
4.000 0.2045 0.06249 0.05244 -0.0586 0.9117 1.0000
4.250 0.2387 0.06539 0.05522 -0.0621 0.9046 1.0000
4.500 0.2569 0.06656 0.05634 -0.0629 0.8930 1.0000
4.750 0.2750 0.06815 0.05787 -0.0636 0.8833 1.0000
5.000 0.3117 0.07144 0.06108 -0.0673 0.8751 1.0000
5.250 0.3250 0.07239 0.06202 -0.0672 0.8627 1.0000
5.500 0.3409 0.07398 0.06359 -0.0676 0.8518 1.0000
5.750 0.3681 0.07667 0.06625 -0.0697 0.8431 1.0000
6.000 0.3921 0.07879 0.06838 -0.0712 0.8309 1.0000
6.250 0.4050 0.08023 0.06983 -0.0711 0.8185 1.0000
6.500 0.4213 0.08220 0.07181 -0.0716 0.8074 1.0000
6.750 0.4509 0.08531 0.07493 -0.0739 0.7980 1.0000
7.000 0.4716 0.08742 0.07709 -0.0749 0.7847 1.0000
7.250 0.4827 0.08900 0.07871 -0.0746 0.7715 1.0000
7.500 0.4960 0.09098 0.08073 -0.0748 0.7589 1.0000
7.750 0.5125 0.09335 0.08315 -0.0754 0.7475 1.0000
8.000 0.5393 0.09652 0.08639 -0.0772 0.7364 1.0000
8.250 0.5628 0.09926 0.08921 -0.0784 0.7228 1.0000
8.500 0.5729 0.10110 0.09112 -0.0783 0.7085 1.0000
8.750 0.5834 0.10318 0.09329 -0.0782 0.6946 1.0000
9.000 0.5956 0.10552 0.09571 -0.0784 0.6806 1.0000
9.250 0.6084 0.10799 0.09826 -0.0787 0.6668 1.0000
9.500 0.6219 0.11060 0.10096 -0.0791 0.6527 1.0000
9.750 0.6357 0.11329 0.10375 -0.0796 0.6386 1.0000
10.000 0.6496 0.11604 0.10662 -0.0800 0.6242 1.0000
10.250 0.6632 0.11878 0.10945 -0.0805 0.6089 1.0000
10.500 0.6762 0.12158 0.11236 -0.0809 0.5937 1.0000
10.750 0.6891 0.12427 0.11516 -0.0812 0.5770 1.0000
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Polar data table (+)
Polar graphs
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