EPPLER 417 AIRFOIL (e417-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 417 AIRFOIL (e417-il) Reynolds number: 200,000 Max Cl/Cd: 65.62 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e417-il-200000.txt Download as CSV file: xf-e417-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4932 0.10137 0.09836 -0.0444 1.0000 0.0647
-10.250 -0.5181 0.09517 0.09214 -0.0468 1.0000 0.0647
-10.000 -0.5462 0.08960 0.08655 -0.0483 1.0000 0.0647
-9.750 -0.5749 0.08472 0.08162 -0.0490 1.0000 0.0647
-9.500 -0.5990 0.08038 0.07726 -0.0486 1.0000 0.0647
-9.250 -0.6285 0.07671 0.07354 -0.0473 1.0000 0.0646
-9.000 -0.6579 0.07365 0.07045 -0.0448 1.0000 0.0645
-8.750 -0.6862 0.07057 0.06728 -0.0431 1.0000 0.0645
-8.500 -0.7093 0.06763 0.06418 -0.0418 1.0000 0.0647
-8.250 -0.7285 0.06506 0.06134 -0.0406 1.0000 0.0649
-8.000 -0.7762 0.06896 0.06467 -0.0420 1.0000 0.0649
-7.750 -0.7757 0.05985 0.05574 -0.0426 1.0000 0.0671
-6.500 -0.6978 0.03708 0.03074 -0.0422 1.0000 0.0397
-6.250 -0.6713 0.03277 0.02562 -0.0418 1.0000 0.0327
-6.000 -0.6484 0.03159 0.02426 -0.0412 1.0000 0.0319
-5.750 -0.6263 0.02927 0.02180 -0.0406 1.0000 0.0314
-5.500 -0.6040 0.02772 0.02011 -0.0399 1.0000 0.0311
-5.250 -0.5815 0.02653 0.01880 -0.0391 1.0000 0.0312
-5.000 -0.5564 0.02561 0.01780 -0.0389 0.9995 0.0315
-4.750 -0.4909 0.02479 0.01700 -0.0466 0.9875 0.0343
-4.500 -0.4448 0.02410 0.01630 -0.0510 0.9795 0.0365
-4.250 -0.4031 0.02352 0.01565 -0.0547 0.9757 0.0393
-4.000 -0.3593 0.02284 0.01487 -0.0588 0.9712 0.0451
-3.750 -0.2939 0.01975 0.01423 -0.0706 0.9735 0.5284
-3.500 -0.2688 0.02011 0.01458 -0.0698 0.9660 0.5783
-3.250 -0.2349 0.02137 0.01581 -0.0702 0.9620 0.6071
-3.000 -0.2121 0.02209 0.01648 -0.0687 0.9547 0.6266
-2.750 -0.1920 0.02394 0.01849 -0.0646 0.9494 0.6462
-2.500 -0.1757 0.02480 0.01938 -0.0611 0.9419 0.6600
-2.250 -0.1490 0.02547 0.02003 -0.0600 0.9373 0.6673
-2.000 -0.1059 0.02563 0.02003 -0.0637 0.9350 0.6742
-1.750 -0.0883 0.02556 0.01993 -0.0617 0.9269 0.6770
-1.500 -0.0525 0.02566 0.01997 -0.0635 0.9233 0.6808
-1.250 -0.0074 0.02567 0.01984 -0.0678 0.9213 0.6861
-1.000 0.0151 0.02544 0.01955 -0.0674 0.9131 0.6895
-0.750 0.0502 0.02547 0.01956 -0.0689 0.9094 0.6919
-0.500 0.0914 0.02549 0.01954 -0.0716 0.9072 0.6948
-0.250 0.1141 0.02531 0.01933 -0.0714 0.8984 0.6987
0.000 0.1595 0.02509 0.01902 -0.0757 0.8955 0.7032
0.250 0.1993 0.02498 0.01891 -0.0779 0.8933 0.7052
0.500 0.2186 0.02488 0.01883 -0.0765 0.8838 0.7077
0.750 0.2595 0.02464 0.01860 -0.0791 0.8808 0.7105
1.000 0.2897 0.02445 0.01840 -0.0801 0.8734 0.7139
1.250 0.3326 0.02410 0.01802 -0.0836 0.8690 0.7181
1.500 0.3725 0.02372 0.01769 -0.0857 0.8663 0.7201
1.750 0.3960 0.02359 0.01761 -0.0850 0.8576 0.7223
2.000 0.4343 0.02322 0.01729 -0.0869 0.8539 0.7251
2.250 0.4787 0.02269 0.01682 -0.0900 0.8517 0.7284
2.500 0.5089 0.02235 0.01651 -0.0908 0.8420 0.7320
2.750 0.5535 0.02155 0.01577 -0.0936 0.8387 0.7344
3.000 0.5976 0.02072 0.01505 -0.0961 0.8367 0.7366
3.250 0.6209 0.02040 0.01482 -0.0951 0.8257 0.7394
3.500 0.6667 0.01939 0.01391 -0.0979 0.8232 0.7425
3.750 0.6968 0.01885 0.01346 -0.0981 0.8126 0.7458
4.000 0.7453 0.01769 0.01240 -0.1015 0.8086 0.7486
4.250 0.7726 0.01713 0.01195 -0.1008 0.7958 0.7510
4.500 0.8050 0.01648 0.01143 -0.1010 0.7818 0.7538
4.750 0.8471 0.01568 0.01072 -0.1031 0.7646 0.7568
5.000 0.8866 0.01514 0.01022 -0.1050 0.7375 0.7600
5.250 0.9340 0.01467 0.00968 -0.1084 0.6949 0.7630
5.500 0.9666 0.01473 0.00942 -0.1087 0.6234 0.7654
5.750 0.9799 0.01531 0.00964 -0.1057 0.5535 0.7683
6.000 0.9880 0.01603 0.01005 -0.1020 0.4888 0.7715
6.250 0.9961 0.01684 0.01055 -0.0986 0.4268 0.7748
6.500 1.0042 0.01777 0.01114 -0.0955 0.3623 0.7780
6.750 1.0106 0.01868 0.01176 -0.0920 0.3015 0.7806
7.000 1.0191 0.01967 0.01245 -0.0891 0.2426 0.7837
7.250 1.0307 0.02068 0.01320 -0.0868 0.1899 0.7873
7.500 1.0419 0.02199 0.01413 -0.0848 0.1232 0.7909
7.750 1.0436 0.02424 0.01574 -0.0812 0.0479 0.7935
8.000 1.0546 0.02545 0.01696 -0.0787 0.0377 0.7963
8.250 1.0664 0.02664 0.01823 -0.0764 0.0334 0.7994
8.500 1.0803 0.02774 0.01943 -0.0746 0.0307 0.8032
8.750 1.0934 0.02910 0.02083 -0.0729 0.0288 0.8071
9.000 1.1011 0.03080 0.02262 -0.0703 0.0276 0.8099
9.250 1.1160 0.03222 0.02414 -0.0686 0.0268 0.8132
9.500 1.1349 0.03364 0.02568 -0.0675 0.0262 0.8168
9.750 1.1583 0.03524 0.02739 -0.0672 0.0256 0.8205
10.000 1.1836 0.03695 0.02925 -0.0670 0.0251 0.8239
10.250 1.2072 0.03868 0.03116 -0.0665 0.0244 0.8277
10.500 1.2275 0.04033 0.03299 -0.0659 0.0234 0.8321
10.750 1.2473 0.04225 0.03507 -0.0654 0.0227 0.8365
11.000 1.2663 0.04468 0.03778 -0.0645 0.0226 0.8401
11.250 1.2816 0.04757 0.04101 -0.0631 0.0226 0.8441
11.500 1.2865 0.05112 0.04502 -0.0607 0.0230 0.8482
11.750 1.2813 0.05515 0.04953 -0.0573 0.0236 0.8520
12.000 1.2703 0.05928 0.05409 -0.0537 0.0243 0.8557
12.250 1.2565 0.06357 0.05875 -0.0505 0.0249 0.8598
12.500 1.2405 0.06805 0.06354 -0.0479 0.0254 0.8640
12.750 1.2225 0.07265 0.06841 -0.0458 0.0258 0.8677
13.000 1.2033 0.07756 0.07357 -0.0443 0.0262 0.8716
13.250 1.1836 0.08312 0.07934 -0.0438 0.0267 0.8756
14.500 0.8888 0.11575 0.11329 -0.0536 0.0268 0.8442
14.750 0.8707 0.12286 0.12049 -0.0577 0.0275 0.8449
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Polar data table (+)
Polar graphs
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