EPPLER 557 AIRFOIL (e557-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 557 AIRFOIL (e557-il) Reynolds number: 100,000 Max Cl/Cd: 53.73 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e557-il-100000.txt Download as CSV file: xf-e557-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 557 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5304 0.08136 0.07627 -0.0715 1.0000 0.0534
-11.000 -0.5397 0.07719 0.07213 -0.0717 1.0000 0.0526
-10.750 -0.5637 0.07257 0.06750 -0.0725 1.0000 0.0521
-10.500 -0.5898 0.06873 0.06364 -0.0725 1.0000 0.0516
-10.250 -0.6152 0.06554 0.06043 -0.0714 1.0000 0.0507
-10.000 -0.6472 0.06317 0.05804 -0.0690 1.0000 0.0502
-9.750 -0.6788 0.06100 0.05585 -0.0664 1.0000 0.0497
-9.500 -0.7042 0.05788 0.05256 -0.0653 1.0000 0.0489
-9.250 -0.7218 0.05466 0.04912 -0.0642 1.0000 0.0486
-9.000 -0.7332 0.05099 0.04509 -0.0636 1.0000 0.0478
-8.750 -0.7317 0.04857 0.04246 -0.0628 1.0000 0.0490
-8.500 -0.7273 0.04585 0.03943 -0.0625 1.0000 0.0502
-8.250 -0.7186 0.04301 0.03620 -0.0624 1.0000 0.0512
-8.000 -0.7056 0.04031 0.03309 -0.0623 1.0000 0.0521
-7.750 -0.6893 0.03790 0.03024 -0.0621 1.0000 0.0532
-7.500 -0.6728 0.03546 0.02768 -0.0614 1.0000 0.0550
-7.250 -0.6560 0.03416 0.02641 -0.0608 1.0000 0.0587
-7.000 -0.6196 0.03238 0.02438 -0.0632 0.9956 0.0648
-6.750 -0.5815 0.03105 0.02299 -0.0659 0.9899 0.0734
-6.500 -0.5435 0.02965 0.02169 -0.0686 0.9845 0.0854
-6.250 -0.5099 0.02820 0.02044 -0.0705 0.9780 0.1020
-6.000 -0.4684 0.02664 0.01918 -0.0746 0.9729 0.1330
-5.750 -0.4238 0.02320 0.01724 -0.0823 0.9676 0.3045
-5.500 -0.3828 0.02540 0.01947 -0.0834 0.9597 0.4139
-5.250 -0.3510 0.02698 0.02093 -0.0830 0.9503 0.4424
-5.000 -0.3227 0.02852 0.02247 -0.0815 0.9413 0.4603
-4.750 -0.2880 0.02997 0.02386 -0.0810 0.9341 0.4772
-4.500 -0.2618 0.03074 0.02453 -0.0801 0.9245 0.4919
-4.250 -0.2260 0.03182 0.02558 -0.0797 0.9185 0.5050
-4.000 -0.2076 0.03260 0.02636 -0.0766 0.9080 0.5137
-3.750 -0.1693 0.03319 0.02685 -0.0771 0.9028 0.5284
-3.500 -0.1461 0.03331 0.02685 -0.0767 0.8923 0.5421
-3.250 -0.1127 0.03384 0.02738 -0.0754 0.8871 0.5500
-3.000 -0.0846 0.03323 0.02660 -0.0773 0.8770 0.5598
-2.750 -0.0465 0.03304 0.02634 -0.0783 0.8719 0.5653
-2.500 -0.0139 0.03238 0.02550 -0.0812 0.8625 0.5731
-2.250 0.0265 0.03180 0.02482 -0.0836 0.8570 0.5781
-2.000 0.0569 0.03150 0.02444 -0.0844 0.8490 0.5825
-1.750 0.0999 0.03075 0.02354 -0.0884 0.8424 0.5891
-1.500 0.1515 0.02983 0.02250 -0.0930 0.8393 0.5938
-1.250 0.1715 0.02979 0.02243 -0.0920 0.8282 0.5975
-1.000 0.2219 0.02899 0.02153 -0.0963 0.8246 0.6033
-0.750 0.2834 0.02791 0.02029 -0.1032 0.8222 0.6090
-0.500 0.2998 0.02796 0.02036 -0.1013 0.8104 0.6123
-0.250 0.3520 0.02722 0.01957 -0.1054 0.8070 0.6177
0.000 0.3829 0.02699 0.01925 -0.1071 0.7969 0.6233
0.250 0.4291 0.02630 0.01853 -0.1102 0.7919 0.6275
0.500 0.4581 0.02615 0.01838 -0.1104 0.7830 0.6318
0.750 0.5009 0.02564 0.01783 -0.1133 0.7762 0.6381
1.000 0.5395 0.02526 0.01741 -0.1155 0.7687 0.6433
1.250 0.5707 0.02503 0.01720 -0.1159 0.7600 0.6475
1.500 0.6056 0.02481 0.01697 -0.1174 0.7517 0.6533
1.750 0.6422 0.02451 0.01664 -0.1192 0.7431 0.6595
2.000 0.6683 0.02451 0.01668 -0.1187 0.7336 0.6644
2.250 0.7075 0.02417 0.01632 -0.1207 0.7257 0.6710
2.500 0.7332 0.02425 0.01642 -0.1207 0.7151 0.6764
2.750 0.7719 0.02388 0.01606 -0.1222 0.7080 0.6826
3.000 0.7957 0.02409 0.01630 -0.1219 0.6965 0.6900
3.250 0.8308 0.02384 0.01607 -0.1228 0.6888 0.6961
3.500 0.8554 0.02394 0.01623 -0.1223 0.6778 0.7030
3.750 0.8820 0.02403 0.01637 -0.1222 0.6676 0.7099
4.000 0.9168 0.02381 0.01615 -0.1231 0.6590 0.7179
4.250 0.9383 0.02405 0.01648 -0.1221 0.6474 0.7259
4.500 0.9682 0.02399 0.01646 -0.1222 0.6380 0.7343
4.750 0.9974 0.02396 0.01647 -0.1223 0.6274 0.7431
5.000 1.0191 0.02416 0.01676 -0.1213 0.6159 0.7526
5.250 1.0497 0.02405 0.01669 -0.1214 0.6062 0.7627
5.500 1.0759 0.02408 0.01679 -0.1210 0.5947 0.7743
5.750 1.0967 0.02427 0.01708 -0.1196 0.5829 0.7859
6.000 1.1231 0.02424 0.01710 -0.1190 0.5721 0.7985
6.250 1.1500 0.02415 0.01706 -0.1185 0.5609 0.8132
6.500 1.1672 0.02433 0.01737 -0.1164 0.5484 0.8294
6.750 1.1875 0.02438 0.01752 -0.1148 0.5366 0.8487
7.000 1.2108 0.02419 0.01737 -0.1134 0.5255 0.8723
7.250 1.2220 0.02409 0.01742 -0.1100 0.5134 0.9069
7.500 1.2460 0.02405 0.01752 -0.1095 0.4993 1.0000
7.750 1.2813 0.02434 0.01778 -0.1116 0.4833 1.0000
8.000 1.3108 0.02464 0.01806 -0.1124 0.4674 1.0000
8.250 1.3359 0.02495 0.01835 -0.1122 0.4512 1.0000
8.500 1.3580 0.02528 0.01867 -0.1114 0.4348 1.0000
8.750 1.3776 0.02564 0.01900 -0.1100 0.4179 1.0000
9.000 1.3950 0.02604 0.01938 -0.1083 0.4006 1.0000
9.250 1.4105 0.02649 0.01980 -0.1063 0.3830 1.0000
9.500 1.4226 0.02704 0.02031 -0.1038 0.3649 1.0000
9.750 1.4290 0.02770 0.02099 -0.1004 0.3470 1.0000
10.000 1.4332 0.02844 0.02174 -0.0968 0.3291 1.0000
10.250 1.4367 0.02931 0.02259 -0.0932 0.3113 1.0000
10.500 1.4393 0.03030 0.02356 -0.0897 0.2937 1.0000
10.750 1.4413 0.03144 0.02467 -0.0864 0.2765 1.0000
11.000 1.4427 0.03274 0.02592 -0.0832 0.2599 1.0000
11.250 1.4437 0.03420 0.02733 -0.0803 0.2438 1.0000
11.500 1.4444 0.03581 0.02890 -0.0776 0.2285 1.0000
11.750 1.4448 0.03758 0.03064 -0.0750 0.2138 1.0000
12.000 1.4452 0.03948 0.03252 -0.0728 0.2000 1.0000
12.250 1.4459 0.04151 0.03454 -0.0707 0.1870 1.0000
12.500 1.4472 0.04362 0.03663 -0.0689 0.1750 1.0000
12.750 1.4502 0.04574 0.03867 -0.0674 0.1635 1.0000
13.000 1.4494 0.04808 0.04107 -0.0658 0.1532 1.0000
13.250 1.4494 0.05061 0.04368 -0.0644 0.1434 1.0000
13.500 1.4532 0.05297 0.04598 -0.0634 0.1341 1.0000
13.750 1.4520 0.05562 0.04871 -0.0623 0.1259 1.0000
14.000 1.4529 0.05841 0.05158 -0.0614 0.1182 1.0000
14.250 1.4571 0.06083 0.05395 -0.0607 0.1107 1.0000
14.500 1.4542 0.06412 0.05745 -0.0601 0.1045 1.0000
14.750 1.4584 0.06665 0.05994 -0.0596 0.0981 1.0000
15.000 1.4570 0.07010 0.06358 -0.0592 0.0930 1.0000
15.250 1.4543 0.07345 0.06706 -0.0591 0.0881 1.0000
15.500 1.4637 0.07606 0.06962 -0.0588 0.0828 1.0000
15.750 1.4526 0.08054 0.07442 -0.0591 0.0797 1.0000
16.000 1.4506 0.08405 0.07804 -0.0595 0.0760 1.0000
16.250 1.4593 0.08690 0.08084 -0.0594 0.0717 1.0000
16.500 1.4435 0.09228 0.08657 -0.0606 0.0700 1.0000
16.750 1.4302 0.09760 0.09217 -0.0621 0.0680 1.0000
17.000 1.4198 0.10258 0.09733 -0.0637 0.0659 1.0000
17.250 1.4363 0.10433 0.09892 -0.0634 0.0619 1.0000
17.500 1.4130 0.11124 0.10617 -0.0664 0.0613 1.0000
17.750 1.3886 0.11880 0.11405 -0.0702 0.0609 1.0000
18.000 1.3619 0.12721 0.12276 -0.0750 0.0607 1.0000
18.250 1.3325 0.13670 0.13250 -0.0808 0.0609 1.0000
18.500 1.2994 0.14758 0.14361 -0.0880 0.0614 1.0000
18.750 1.2642 0.15986 0.15608 -0.0963 0.0621 1.0000
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Polar data table (+)
Polar graphs
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