EPPLER 657 AIRFOIL (e657-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: EPPLER 657 AIRFOIL (e657-il) Reynolds number: 200,000 Max Cl/Cd: 72.02 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e657-il-200000.txt Download as CSV file: xf-e657-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 657 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0263 0.09848 0.09438 -0.1282 0.8896 0.0499
-11.000 -0.0436 0.09411 0.09006 -0.1332 0.8844 0.0516
-10.750 -0.0425 0.08989 0.08585 -0.1346 0.8810 0.0523
-10.500 -0.0254 0.08782 0.08374 -0.1337 0.8785 0.0532
-10.250 -0.0147 0.08560 0.08150 -0.1341 0.8758 0.0545
-10.000 -0.0115 0.08290 0.07882 -0.1349 0.8723 0.0561
-9.750 -0.0134 0.07960 0.07555 -0.1365 0.8684 0.0579
-9.500 -0.0642 0.07074 0.06674 -0.1479 0.8624 0.0604
-9.250 -0.0967 0.06706 0.06296 -0.1500 0.8582 0.0605
-9.000 -0.0406 0.06620 0.06225 -0.1452 0.8584 0.0624
-8.750 -0.0447 0.06294 0.05903 -0.1468 0.8550 0.0632
-8.500 -0.0559 0.05969 0.05577 -0.1480 0.8511 0.0642
-8.250 -0.0758 0.05690 0.05294 -0.1474 0.8469 0.0648
-8.000 -0.0906 0.05437 0.05029 -0.1465 0.8438 0.0664
-7.750 -0.1391 0.05436 0.04965 -0.1426 0.8386 0.0706
-7.500 -0.1685 0.03839 0.03291 -0.1386 0.8347 0.0333
-7.250 -0.1716 0.03367 0.02725 -0.1346 0.8314 0.0272
-7.000 -0.1557 0.03148 0.02482 -0.1335 0.8292 0.0267
-6.750 -0.1378 0.02949 0.02249 -0.1323 0.8275 0.0265
-6.500 -0.1177 0.02792 0.02061 -0.1313 0.8259 0.0264
-6.250 -0.1086 0.02721 0.01971 -0.1286 0.8219 0.0267
-6.000 -0.0929 0.02646 0.01873 -0.1267 0.8185 0.0272
-5.750 -0.0739 0.02546 0.01772 -0.1256 0.8161 0.0283
-5.500 -0.0518 0.02497 0.01718 -0.1249 0.8141 0.0310
-5.250 -0.0274 0.02421 0.01639 -0.1245 0.8124 0.0343
-5.000 -0.0009 0.02352 0.01559 -0.1242 0.8109 0.0379
-4.750 0.0240 0.02274 0.01484 -0.1238 0.8094 0.0439
-4.500 0.0083 0.02375 0.01596 -0.1176 0.8022 0.0461
-4.250 0.0259 0.02346 0.01572 -0.1162 0.7990 0.0589
-4.000 0.0496 0.02275 0.01517 -0.1159 0.7969 0.0878
-3.750 0.0762 0.02211 0.01477 -0.1162 0.7954 0.1403
-3.500 0.1049 0.02130 0.01443 -0.1171 0.7942 0.2412
-3.250 0.0884 0.02259 0.01590 -0.1108 0.7860 0.2753
-3.000 0.1049 0.02232 0.01613 -0.1098 0.7824 0.3969
-2.750 0.1304 0.02168 0.01615 -0.1096 0.7804 0.5638
-2.500 0.1550 0.02152 0.01639 -0.1081 0.7788 0.6862
-2.250 0.1818 0.02164 0.01657 -0.1068 0.7776 0.7478
-2.000 0.1441 0.02366 0.01870 -0.0969 0.7660 0.7594
-1.750 0.1685 0.02398 0.01896 -0.0953 0.7637 0.7965
-1.500 0.1975 0.02415 0.01903 -0.0946 0.7622 0.8251
-1.250 0.2251 0.02419 0.01899 -0.0932 0.7610 0.8443
-1.000 0.1886 0.02604 0.02091 -0.0836 0.7488 0.8582
-0.750 0.2087 0.02605 0.02086 -0.0811 0.7465 0.8757
-0.500 0.2320 0.02589 0.02063 -0.0790 0.7449 0.8925
-0.250 0.2570 0.02559 0.02026 -0.0770 0.7438 0.9090
0.000 0.2854 0.02521 0.01980 -0.0758 0.7430 0.9243
0.250 0.2493 0.02677 0.02142 -0.0666 0.7292 0.9446
0.500 0.2861 0.02647 0.02104 -0.0674 0.7281 0.9597
0.750 0.3384 0.02627 0.02075 -0.0714 0.7275 0.9715
1.000 0.4044 0.02607 0.02046 -0.0781 0.7273 0.9792
1.250 0.4715 0.02581 0.02012 -0.0852 0.7272 0.9838
1.500 0.5372 0.02545 0.01968 -0.0921 0.7271 0.9862
1.750 0.5938 0.02499 0.01915 -0.0973 0.7267 0.9884
2.000 0.5191 0.02778 0.02203 -0.0838 0.7056 1.0000
2.250 0.5770 0.02687 0.02106 -0.0881 0.7074 1.0000
2.500 0.6314 0.02607 0.02022 -0.0922 0.7081 1.0000
2.750 0.6911 0.02526 0.01936 -0.0973 0.7089 1.0000
3.000 0.7505 0.02427 0.01834 -0.1023 0.7098 1.0000
3.250 0.6225 0.02779 0.02189 -0.0796 0.6821 1.0000
3.500 0.6634 0.02715 0.02125 -0.0813 0.6811 1.0000
3.750 0.7063 0.02638 0.02046 -0.0832 0.6805 1.0000
4.000 0.7514 0.02549 0.01956 -0.0855 0.6802 1.0000
4.250 0.7973 0.02463 0.01871 -0.0880 0.6797 1.0000
4.500 0.8455 0.02374 0.01783 -0.0909 0.6791 1.0000
4.750 0.8962 0.02282 0.01692 -0.0944 0.6785 1.0000
5.000 0.8827 0.02396 0.01811 -0.0887 0.6655 1.0000
5.250 0.9325 0.02285 0.01702 -0.0918 0.6648 1.0000
5.500 0.9850 0.02175 0.01595 -0.0954 0.6639 1.0000
5.750 1.0375 0.02068 0.01490 -0.0991 0.6628 1.0000
6.000 1.0291 0.02144 0.01573 -0.0937 0.6508 1.0000
6.250 1.0822 0.02026 0.01459 -0.0974 0.6490 1.0000
6.500 1.0853 0.02067 0.01506 -0.0938 0.6387 1.0000
6.750 1.1325 0.01959 0.01402 -0.0965 0.6351 1.0000
7.000 1.1543 0.01936 0.01386 -0.0956 0.6270 1.0000
7.250 1.1872 0.01875 0.01328 -0.0962 0.6196 1.0000
7.500 1.2007 0.01883 0.01343 -0.0941 0.6086 1.0000
7.750 1.2364 0.01818 0.01280 -0.0951 0.5997 1.0000
8.000 1.2598 0.01799 0.01263 -0.0944 0.5872 1.0000
8.250 1.2780 0.01805 0.01271 -0.0930 0.5722 1.0000
8.500 1.3000 0.01805 0.01269 -0.0921 0.5557 1.0000
8.750 1.3122 0.01849 0.01312 -0.0900 0.5366 1.0000
9.000 1.3259 0.01896 0.01354 -0.0882 0.5161 1.0000
9.250 1.3406 0.01946 0.01394 -0.0865 0.4946 1.0000
9.500 1.3491 0.02029 0.01469 -0.0842 0.4726 1.0000
9.750 1.3560 0.02125 0.01558 -0.0818 0.4507 1.0000
10.000 1.3626 0.02229 0.01650 -0.0794 0.4295 1.0000
10.250 1.3662 0.02354 0.01770 -0.0769 0.4082 1.0000
10.500 1.3695 0.02486 0.01896 -0.0744 0.3874 1.0000
10.750 1.3725 0.02626 0.02028 -0.0721 0.3674 1.0000
11.000 1.3750 0.02774 0.02168 -0.0698 0.3479 1.0000
11.250 1.3776 0.02928 0.02319 -0.0677 0.3288 1.0000
11.500 1.3802 0.03089 0.02476 -0.0657 0.3101 1.0000
11.750 1.3825 0.03258 0.02640 -0.0638 0.2921 1.0000
12.000 1.3848 0.03434 0.02812 -0.0619 0.2746 1.0000
12.250 1.3871 0.03618 0.02990 -0.0603 0.2576 1.0000
12.500 1.3891 0.03810 0.03178 -0.0587 0.2412 1.0000
12.750 1.3916 0.04006 0.03371 -0.0572 0.2257 1.0000
13.000 1.3941 0.04210 0.03574 -0.0559 0.2106 1.0000
13.250 1.3964 0.04422 0.03784 -0.0547 0.1961 1.0000
13.500 1.3990 0.04638 0.03999 -0.0536 0.1822 1.0000
13.750 1.4010 0.04867 0.04228 -0.0526 0.1689 1.0000
14.000 1.4031 0.05102 0.04463 -0.0517 0.1566 1.0000
14.250 1.4043 0.05352 0.04711 -0.0508 0.1452 1.0000
14.500 1.4038 0.05624 0.04979 -0.0500 0.1349 1.0000
14.750 1.4066 0.05873 0.05236 -0.0495 0.1243 1.0000
15.000 1.4081 0.06143 0.05510 -0.0490 0.1147 1.0000
15.250 1.4071 0.06443 0.05808 -0.0485 0.1064 1.0000
15.500 1.4076 0.06737 0.06106 -0.0483 0.0981 1.0000
15.750 1.4081 0.07039 0.06414 -0.0481 0.0905 1.0000
16.000 1.4048 0.07386 0.06754 -0.0480 0.0840 1.0000
16.250 1.4066 0.07690 0.07076 -0.0481 0.0774 1.0000
16.500 1.4036 0.08046 0.07429 -0.0482 0.0720 1.0000
16.750 1.4036 0.08384 0.07780 -0.0485 0.0666 1.0000
17.000 1.4010 0.08748 0.08142 -0.0489 0.0620 1.0000
17.250 1.4005 0.09105 0.08513 -0.0495 0.0576 1.0000
17.500 1.3980 0.09471 0.08874 -0.0500 0.0538 1.0000
17.750 1.3973 0.09845 0.09267 -0.0509 0.0502 1.0000
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Polar data table (+)
Polar graphs
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