EPPLER 417 AIRFOIL (e417-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 417 AIRFOIL (e417-il) Reynolds number: 100,000 Max Cl/Cd: 46.76 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e417-il-100000.txt Download as CSV file: xf-e417-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6012 0.10688 0.10249 -0.0406 1.0000 0.1495
-9.250 -0.5292 0.10650 0.10196 -0.0316 1.0000 0.1545
-7.000 -0.7326 0.05327 0.04730 -0.0439 1.0000 0.0880
-6.750 -0.7109 0.04543 0.03831 -0.0443 1.0000 0.0618
-6.500 -0.6902 0.04132 0.03373 -0.0443 1.0000 0.0574
-6.250 -0.6649 0.03827 0.02986 -0.0442 1.0000 0.0538
-6.000 -0.6431 0.03588 0.02729 -0.0439 1.0000 0.0551
-5.750 -0.6205 0.03406 0.02526 -0.0434 1.0000 0.0559
-5.500 -0.5977 0.03238 0.02338 -0.0425 1.0000 0.0558
-5.250 -0.5755 0.03089 0.02176 -0.0413 1.0000 0.0561
-5.000 -0.5539 0.02966 0.02047 -0.0400 1.0000 0.0569
-4.750 -0.5325 0.02859 0.01940 -0.0388 1.0000 0.0585
-4.500 -0.5108 0.02768 0.01848 -0.0378 1.0000 0.0610
-4.250 -0.4878 0.02695 0.01769 -0.0371 1.0000 0.0648
-4.000 -0.4622 0.02588 0.01675 -0.0378 1.0000 0.0742
-3.750 -0.4308 0.02471 0.01567 -0.0396 1.0000 0.0955
-3.500 -0.4001 0.02398 0.01765 -0.0402 1.0000 0.5991
-3.250 -0.3961 0.02582 0.01949 -0.0333 1.0000 0.6295
-3.000 -0.3973 0.02766 0.02139 -0.0249 1.0000 0.6539
-2.750 -0.4027 0.02940 0.02321 -0.0153 1.0000 0.6773
-2.500 -0.4021 0.03075 0.02455 -0.0077 1.0000 0.7034
-2.250 -0.4048 0.03156 0.02538 0.0005 1.0000 0.7209
-2.000 -0.4001 0.03197 0.02575 0.0060 1.0000 0.7372
-1.750 -0.3859 0.03204 0.02569 0.0084 1.0000 0.7505
-1.500 -0.3688 0.03196 0.02549 0.0097 1.0000 0.7587
-1.250 -0.3470 0.03179 0.02519 0.0094 1.0000 0.7656
-1.000 -0.3280 0.03168 0.02498 0.0100 1.0000 0.7715
-0.750 -0.2972 0.03167 0.02480 0.0070 1.0000 0.7777
-0.500 -0.2815 0.03154 0.02461 0.0084 1.0000 0.7817
-0.250 -0.2596 0.03155 0.02454 0.0079 1.0000 0.7863
0.000 -0.2312 0.03168 0.02456 0.0056 1.0000 0.7910
0.250 -0.1450 0.03353 0.02620 -0.0063 0.9681 0.7948
0.500 -0.1043 0.03385 0.02644 -0.0097 0.9548 0.7987
0.750 -0.0622 0.03414 0.02664 -0.0136 0.9435 0.8024
1.000 -0.0115 0.03464 0.02706 -0.0195 0.9349 0.8065
1.250 0.0194 0.03453 0.02693 -0.0210 0.9233 0.8096
1.500 0.0518 0.03454 0.02692 -0.0227 0.9123 0.8129
1.750 0.0904 0.03467 0.02703 -0.0257 0.9026 0.8168
2.000 0.1368 0.03484 0.02719 -0.0302 0.8942 0.8203
2.250 0.1691 0.03474 0.02711 -0.0320 0.8828 0.8235
2.500 0.2012 0.03467 0.02708 -0.0334 0.8724 0.8269
2.750 0.2474 0.03466 0.02710 -0.0372 0.8656 0.8306
3.000 0.2809 0.03458 0.02707 -0.0393 0.8540 0.8339
3.250 0.3170 0.03450 0.02705 -0.0416 0.8433 0.8373
3.500 0.3617 0.03408 0.02673 -0.0444 0.8370 0.8408
3.750 0.3940 0.03375 0.02647 -0.0456 0.8245 0.8444
4.000 0.4312 0.03336 0.02618 -0.0476 0.8124 0.8478
4.250 0.4727 0.03286 0.02581 -0.0502 0.8015 0.8514
4.500 0.5173 0.03186 0.02495 -0.0522 0.7944 0.8551
4.750 0.5512 0.03120 0.02441 -0.0530 0.7817 0.8590
5.000 0.5904 0.03039 0.02377 -0.0547 0.7695 0.8626
5.250 0.6462 0.02867 0.02225 -0.0581 0.7635 0.8664
5.500 0.6818 0.02732 0.02110 -0.0581 0.7510 0.8705
5.750 0.7215 0.02588 0.01985 -0.0588 0.7377 0.8748
6.000 0.7699 0.02418 0.01837 -0.0609 0.7229 0.8788
6.250 0.8180 0.02238 0.01677 -0.0625 0.7030 0.8825
6.500 0.8601 0.02111 0.01564 -0.0635 0.6717 0.8870
6.750 0.9041 0.02027 0.01483 -0.0651 0.6257 0.8917
7.000 0.9367 0.02007 0.01449 -0.0652 0.5678 0.8960
7.250 0.9529 0.02038 0.01457 -0.0628 0.5056 0.9007
7.500 0.9622 0.02111 0.01495 -0.0597 0.4369 0.9060
7.750 0.9658 0.02200 0.01547 -0.0558 0.3704 0.9116
8.000 0.9689 0.02303 0.01619 -0.0523 0.3052 0.9181
8.250 0.9736 0.02420 0.01704 -0.0493 0.2448 0.9246
8.500 0.9767 0.02564 0.01811 -0.0462 0.1802 0.9317
8.750 0.9722 0.02804 0.01985 -0.0424 0.1069 0.9388
9.000 0.9729 0.03026 0.02182 -0.0389 0.0745 0.9478
9.250 0.9810 0.03201 0.02355 -0.0366 0.0641 0.9596
9.500 0.9962 0.03348 0.02503 -0.0354 0.0579 0.9926
9.750 1.0321 0.03583 0.02741 -0.0371 0.0529 1.0000
10.000 1.0664 0.03783 0.02952 -0.0388 0.0483 1.0000
10.250 1.1237 0.04174 0.03340 -0.0438 0.0446 1.0000
10.500 1.1601 0.04504 0.03711 -0.0457 0.0438 1.0000
10.750 1.1860 0.04875 0.04127 -0.0464 0.0435 1.0000
11.000 1.2020 0.05269 0.04569 -0.0459 0.0436 1.0000
11.250 1.2103 0.05684 0.05025 -0.0446 0.0439 1.0000
11.500 1.2140 0.06137 0.05513 -0.0432 0.0443 1.0000
11.750 1.2204 0.06690 0.06098 -0.0426 0.0450 1.0000
12.000 1.2116 0.06909 0.06353 -0.0396 0.0456 1.0000
12.250 1.1848 0.07230 0.06725 -0.0356 0.0467 1.0000
12.500 1.1402 0.07778 0.07329 -0.0324 0.0482 1.0000
12.750 1.1065 0.08396 0.07984 -0.0319 0.0493 1.0000
13.000 1.0757 0.09062 0.08677 -0.0331 0.0502 1.0000
13.250 1.0448 0.09809 0.09444 -0.0362 0.0510 1.0000
13.500 1.0136 0.10673 0.10326 -0.0411 0.0518 1.0000
13.750 0.9829 0.11695 0.11361 -0.0481 0.0527 1.0000
14.000 0.9630 0.12691 0.12363 -0.0547 0.0541 1.0000
14.250 0.9108 0.15153 0.14823 -0.0706 0.0660 1.0000
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Polar data table (+)
Polar graphs
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