EPPLER 417 AIRFOIL (e417-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 417 AIRFOIL (e417-il) Reynolds number: 100,000 Max Cl/Cd: 46 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e417-il-100000-n5.txt Download as CSV file: xf-e417-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 417 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5487 0.10526 0.10029 -0.0481 1.0000 0.0232
-11.250 -0.5602 0.09966 0.09469 -0.0500 1.0000 0.0229
-11.000 -0.5786 0.09319 0.08822 -0.0525 1.0000 0.0227
-10.750 -0.5993 0.08736 0.08235 -0.0546 1.0000 0.0225
-10.500 -0.6238 0.08189 0.07682 -0.0561 1.0000 0.0224
-10.250 -0.6459 0.07755 0.07243 -0.0564 1.0000 0.0223
-10.000 -0.6686 0.07371 0.06851 -0.0560 1.0000 0.0221
-9.750 -0.6927 0.07032 0.06504 -0.0547 1.0000 0.0220
-9.500 -0.7166 0.06760 0.06223 -0.0524 1.0000 0.0219
-9.250 -0.7429 0.06496 0.05948 -0.0498 0.9994 0.0219
-9.000 -0.7496 0.06077 0.05501 -0.0519 0.9957 0.0217
-8.750 -0.7497 0.05664 0.05052 -0.0533 0.9919 0.0216
-8.500 -0.7446 0.05277 0.04626 -0.0542 0.9887 0.0214
-8.250 -0.7325 0.04912 0.04218 -0.0554 0.9861 0.0214
-8.000 -0.7188 0.04580 0.03843 -0.0558 0.9832 0.0215
-7.750 -0.7018 0.04305 0.03528 -0.0561 0.9805 0.0218
-7.500 -0.6811 0.04065 0.03241 -0.0565 0.9783 0.0227
-7.250 -0.6566 0.03864 0.02997 -0.0570 0.9763 0.0232
-7.000 -0.6312 0.03667 0.02781 -0.0576 0.9747 0.0237
-6.750 -0.6095 0.03507 0.02606 -0.0571 0.9725 0.0241
-6.500 -0.5878 0.03370 0.02459 -0.0565 0.9700 0.0245
-6.250 -0.5640 0.03251 0.02332 -0.0562 0.9676 0.0251
-6.000 -0.5387 0.03146 0.02219 -0.0563 0.9654 0.0257
-5.750 -0.5120 0.03050 0.02116 -0.0568 0.9635 0.0267
-5.500 -0.4865 0.02959 0.02015 -0.0571 0.9611 0.0277
-5.250 -0.4634 0.02876 0.01920 -0.0571 0.9577 0.0294
-5.000 -0.4366 0.02790 0.01832 -0.0581 0.9550 0.0323
-4.750 -0.4063 0.02723 0.01755 -0.0595 0.9526 0.0358
-4.500 -0.3733 0.02649 0.01670 -0.0615 0.9507 0.0411
-4.250 -0.3421 0.02570 0.01595 -0.0632 0.9483 0.0579
-4.000 -0.2999 0.02269 0.01467 -0.0706 0.9479 0.3571
-3.750 -0.2818 0.02339 0.01624 -0.0677 0.9432 0.5527
-3.250 -0.2328 0.02627 0.01902 -0.0631 0.9361 0.6268
-3.000 -0.2195 0.02679 0.01949 -0.0594 0.9300 0.6360
-2.750 -0.1885 0.02683 0.01933 -0.0604 0.9266 0.6435
-2.500 -0.1574 0.02697 0.01932 -0.0611 0.9238 0.6476
-2.250 -0.1264 0.02691 0.01910 -0.0624 0.9204 0.6529
-2.000 -0.0983 0.02674 0.01878 -0.0634 0.9154 0.6579
-1.750 -0.0686 0.02677 0.01871 -0.0639 0.9117 0.6607
-1.500 -0.0340 0.02677 0.01861 -0.0656 0.9091 0.6641
-1.250 -0.0077 0.02666 0.01840 -0.0661 0.9036 0.6684
-1.000 0.0256 0.02653 0.01815 -0.0681 0.8992 0.6728
-0.750 0.0582 0.02653 0.01810 -0.0692 0.8959 0.6752
-0.500 0.0850 0.02650 0.01803 -0.0694 0.8906 0.6780
-0.250 0.1142 0.02643 0.01793 -0.0702 0.8851 0.6814
0.000 0.1519 0.02631 0.01774 -0.0727 0.8819 0.6854
0.250 0.1805 0.02624 0.01763 -0.0735 0.8758 0.6886
0.500 0.2092 0.02617 0.01757 -0.0738 0.8701 0.6909
0.750 0.2454 0.02603 0.01744 -0.0756 0.8668 0.6936
1.000 0.2687 0.02600 0.01742 -0.0753 0.8582 0.6969
1.250 0.3061 0.02579 0.01721 -0.0775 0.8539 0.7003
1.500 0.3346 0.02571 0.01714 -0.0781 0.8464 0.7036
1.750 0.3659 0.02551 0.01701 -0.0788 0.8404 0.7059
2.000 0.3940 0.02536 0.01692 -0.0790 0.8327 0.7085
2.250 0.4270 0.02511 0.01673 -0.0801 0.8260 0.7114
2.500 0.4571 0.02495 0.01664 -0.0808 0.8180 0.7148
2.750 0.4920 0.02467 0.01642 -0.0824 0.8114 0.7183
3.000 0.5176 0.02452 0.01638 -0.0819 0.8023 0.7206
3.250 0.5519 0.02407 0.01605 -0.0828 0.7957 0.7231
3.500 0.5783 0.02381 0.01590 -0.0825 0.7841 0.7259
3.750 0.6088 0.02342 0.01561 -0.0828 0.7732 0.7293
4.000 0.6476 0.02280 0.01511 -0.0845 0.7648 0.7330
4.250 0.6738 0.02251 0.01496 -0.0839 0.7508 0.7353
4.500 0.7037 0.02212 0.01471 -0.0839 0.7359 0.7379
4.750 0.7364 0.02167 0.01440 -0.0843 0.7186 0.7407
5.000 0.7697 0.02127 0.01410 -0.0850 0.6966 0.7441
5.250 0.8122 0.02066 0.01355 -0.0871 0.6700 0.7478
5.500 0.8527 0.02015 0.01309 -0.0886 0.6341 0.7503
5.750 0.8918 0.01992 0.01278 -0.0901 0.5868 0.7529
6.000 0.9232 0.02010 0.01280 -0.0905 0.5337 0.7558
6.250 0.9467 0.02058 0.01312 -0.0897 0.4796 0.7592
6.500 0.9658 0.02128 0.01359 -0.0884 0.4235 0.7630
6.750 0.9766 0.02215 0.01418 -0.0856 0.3624 0.7658
7.000 0.9856 0.02321 0.01489 -0.0827 0.2955 0.7690
7.250 0.9953 0.02440 0.01570 -0.0803 0.2319 0.7724
7.500 1.0077 0.02564 0.01661 -0.0786 0.1734 0.7759
7.750 1.0206 0.02690 0.01756 -0.0769 0.1217 0.7793
8.000 1.0328 0.02811 0.01859 -0.0750 0.0840 0.7825
8.250 1.0437 0.02958 0.01984 -0.0729 0.0521 0.7862
8.500 1.0560 0.03102 0.02124 -0.0711 0.0374 0.7901
8.750 1.0678 0.03248 0.02272 -0.0692 0.0318 0.7938
9.000 1.0792 0.03373 0.02419 -0.0671 0.0289 0.7971
9.250 1.0900 0.03509 0.02570 -0.0651 0.0269 0.8008
9.500 1.0992 0.03667 0.02739 -0.0631 0.0255 0.8050
9.750 1.1083 0.03828 0.02916 -0.0611 0.0246 0.8091
10.000 1.1176 0.03981 0.03089 -0.0591 0.0235 0.8131
10.250 1.1278 0.04142 0.03266 -0.0574 0.0223 0.8176
10.500 1.1385 0.04311 0.03447 -0.0560 0.0212 0.8223
10.750 1.1464 0.04483 0.03633 -0.0543 0.0203 0.8264
11.000 1.1552 0.04683 0.03843 -0.0527 0.0196 0.8311
11.250 1.1677 0.04884 0.04067 -0.0515 0.0192 0.8364
11.500 1.1787 0.05095 0.04302 -0.0501 0.0188 0.8414
11.750 1.1891 0.05326 0.04560 -0.0487 0.0185 0.8472
12.000 1.1977 0.05582 0.04844 -0.0474 0.0182 0.8531
12.250 1.2022 0.05854 0.05147 -0.0458 0.0179 0.8592
12.500 1.2041 0.06160 0.05483 -0.0444 0.0178 0.8659
12.750 1.2012 0.06482 0.05841 -0.0427 0.0176 0.8730
13.250 1.1852 0.07224 0.06648 -0.0400 0.0175 0.8916
13.500 1.1719 0.07637 0.07094 -0.0391 0.0175 0.9056
13.750 1.1550 0.08067 0.07554 -0.0384 0.0175 0.9346
14.000 1.1376 0.08596 0.08113 -0.0394 0.0175 1.0000
14.250 1.1199 0.09236 0.08781 -0.0419 0.0176 1.0000
14.500 1.1003 0.09958 0.09530 -0.0455 0.0177 1.0000
14.750 1.0788 0.10780 0.10375 -0.0504 0.0178 1.0000
15.000 1.0555 0.11723 0.11342 -0.0566 0.0180 1.0000
15.250 1.0301 0.12833 0.12468 -0.0645 0.0182 1.0000
15.500 1.0024 0.14153 0.13803 -0.0739 0.0186 1.0000
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Polar data table (+)
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