EPPLER 668 AIRFOIL (e668-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 668 AIRFOIL (e668-il) Reynolds number: 200,000 Max Cl/Cd: 81.06 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e668-il-200000.txt Download as CSV file: xf-e668-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 668 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1438 0.09363 0.08999 -0.1104 0.9578 0.0483
-10.000 -0.1511 0.08977 0.08617 -0.1130 0.9529 0.0510
-9.750 -0.1752 0.07914 0.07557 -0.1296 0.9477 0.0523
-9.500 -0.1574 0.07696 0.07342 -0.1268 0.9469 0.0531
-9.250 -0.1392 0.07521 0.07167 -0.1263 0.9459 0.0543
-9.000 -0.1273 0.07162 0.06807 -0.1295 0.9444 0.0560
-8.750 -0.1411 0.06849 0.06497 -0.1302 0.9384 0.0566
-8.500 -0.1593 0.06319 0.05966 -0.1351 0.9326 0.0578
-8.250 -0.1742 0.05885 0.05521 -0.1387 0.9287 0.0585
-8.000 -0.2154 0.06003 0.05644 -0.1284 0.9191 0.0572
-7.750 -0.2248 0.05661 0.05285 -0.1290 0.9155 0.0588
-7.500 -0.2660 0.05770 0.05398 -0.1181 0.9068 0.0585
-7.250 -0.3293 0.04225 0.03724 -0.1121 0.8995 0.0267
-7.000 -0.3115 0.03705 0.03135 -0.1127 0.8980 0.0237
-6.750 -0.3458 0.03784 0.03216 -0.1021 0.8898 0.0238
-6.500 -0.3305 0.03428 0.02801 -0.1011 0.8869 0.0227
-6.250 -0.3053 0.03180 0.02504 -0.1012 0.8851 0.0230
-6.000 -0.2752 0.02994 0.02281 -0.1020 0.8838 0.0238
-5.750 -0.2412 0.02853 0.02110 -0.1035 0.8826 0.0267
-5.500 -0.2499 0.02875 0.02135 -0.0976 0.8762 0.0282
-5.250 -0.2289 0.02792 0.02031 -0.0965 0.8729 0.0299
-5.000 -0.2005 0.02663 0.01898 -0.0968 0.8706 0.0329
-4.750 -0.1688 0.02575 0.01806 -0.0978 0.8689 0.0388
-4.500 -0.1339 0.02490 0.01724 -0.0994 0.8675 0.0481
-4.250 -0.0966 0.02407 0.01643 -0.1014 0.8664 0.0639
-4.000 -0.1066 0.02447 0.01686 -0.0953 0.8583 0.0703
-3.750 -0.0777 0.02383 0.01631 -0.0959 0.8554 0.0984
-3.500 -0.0438 0.02294 0.01582 -0.0977 0.8534 0.1697
-3.250 -0.0072 0.02212 0.01553 -0.1002 0.8519 0.2954
-3.000 0.0306 0.02132 0.01536 -0.1027 0.8508 0.4551
-2.750 0.0255 0.02165 0.01604 -0.0974 0.8421 0.5352
-2.500 0.0489 0.02149 0.01639 -0.0960 0.8389 0.6694
-2.250 0.0786 0.02168 0.01668 -0.0953 0.8367 0.7422
-2.000 0.1127 0.02191 0.01683 -0.0955 0.8352 0.7809
-1.750 0.1056 0.02269 0.01762 -0.0894 0.8252 0.8002
-1.500 0.1327 0.02289 0.01774 -0.0884 0.8223 0.8235
-1.250 0.1631 0.02294 0.01772 -0.0878 0.8205 0.8425
-1.000 0.1597 0.02355 0.01832 -0.0822 0.8110 0.8578
-0.750 0.1813 0.02355 0.01827 -0.0802 0.8074 0.8739
-0.500 0.2075 0.02341 0.01808 -0.0787 0.8053 0.8899
-0.250 0.2045 0.02381 0.01847 -0.0732 0.7958 0.9051
0.000 0.2245 0.02363 0.01826 -0.0709 0.7920 0.9204
0.250 0.2523 0.02331 0.01788 -0.0700 0.7899 0.9349
0.500 0.2848 0.02299 0.01751 -0.0700 0.7885 0.9492
0.750 0.2933 0.02349 0.01801 -0.0676 0.7774 0.9658
1.000 0.3452 0.02334 0.01780 -0.0719 0.7759 0.9758
1.250 0.4007 0.02314 0.01755 -0.0770 0.7748 0.9837
1.500 0.4601 0.02287 0.01723 -0.0829 0.7742 0.9884
1.750 0.5181 0.02247 0.01680 -0.0884 0.7737 0.9917
2.000 0.5750 0.02202 0.01632 -0.0936 0.7733 0.9941
2.250 0.6303 0.02148 0.01577 -0.0986 0.7727 0.9957
2.500 0.5671 0.02247 0.01677 -0.0838 0.7524 1.0000
2.750 0.6314 0.02152 0.01582 -0.0895 0.7552 1.0000
3.000 0.6956 0.02072 0.01502 -0.0957 0.7564 1.0000
3.250 0.6821 0.02085 0.01515 -0.0887 0.7447 1.0000
3.500 0.7107 0.02054 0.01487 -0.0889 0.7397 1.0000
3.750 0.7741 0.01941 0.01377 -0.0945 0.7419 1.0000
4.000 0.7803 0.01952 0.01390 -0.0911 0.7309 1.0000
4.250 0.8286 0.01863 0.01304 -0.0942 0.7296 1.0000
4.500 0.8776 0.01768 0.01215 -0.0975 0.7282 1.0000
4.750 0.8879 0.01769 0.01221 -0.0947 0.7168 1.0000
5.000 0.9375 0.01669 0.01126 -0.0980 0.7144 1.0000
5.250 0.9531 0.01658 0.01121 -0.0959 0.7034 1.0000
5.500 1.0033 0.01558 0.01025 -0.0994 0.6992 1.0000
5.750 1.0220 0.01540 0.01014 -0.0977 0.6868 1.0000
6.000 1.0481 0.01509 0.00988 -0.0973 0.6741 1.0000
6.250 1.0780 0.01475 0.00957 -0.0975 0.6598 1.0000
6.500 1.1097 0.01444 0.00928 -0.0980 0.6428 1.0000
6.750 1.1399 0.01427 0.00907 -0.0983 0.6223 1.0000
7.000 1.1619 0.01438 0.00913 -0.0973 0.5979 1.0000
7.250 1.1835 0.01460 0.00927 -0.0963 0.5710 1.0000
7.500 1.2015 0.01499 0.00954 -0.0947 0.5425 1.0000
7.750 1.2157 0.01553 0.00995 -0.0926 0.5136 1.0000
8.000 1.2266 0.01620 0.01051 -0.0901 0.4848 1.0000
8.250 1.2351 0.01697 0.01118 -0.0874 0.4561 1.0000
8.500 1.2424 0.01784 0.01194 -0.0846 0.4278 1.0000
8.750 1.2487 0.01880 0.01279 -0.0818 0.4000 1.0000
9.000 1.2540 0.01987 0.01374 -0.0789 0.3723 1.0000
9.250 1.2592 0.02101 0.01478 -0.0763 0.3449 1.0000
9.500 1.2645 0.02220 0.01588 -0.0737 0.3175 1.0000
9.750 1.2695 0.02348 0.01706 -0.0713 0.2912 1.0000
10.000 1.2735 0.02488 0.01833 -0.0689 0.2658 1.0000
10.250 1.2794 0.02623 0.01961 -0.0668 0.2404 1.0000
10.500 1.2840 0.02771 0.02099 -0.0646 0.2167 1.0000
10.750 1.2888 0.02924 0.02245 -0.0626 0.1939 1.0000
11.000 1.2933 0.03086 0.02398 -0.0607 0.1728 1.0000
11.250 1.2984 0.03249 0.02555 -0.0589 0.1529 1.0000
11.500 1.3023 0.03428 0.02726 -0.0571 0.1354 1.0000
11.750 1.3059 0.03615 0.02906 -0.0554 0.1203 1.0000
12.000 1.3094 0.03810 0.03097 -0.0537 0.1068 1.0000
12.250 1.3138 0.04004 0.03291 -0.0523 0.0949 1.0000
12.500 1.3180 0.04207 0.03497 -0.0509 0.0845 1.0000
12.750 1.3211 0.04427 0.03719 -0.0496 0.0759 1.0000
13.000 1.3215 0.04678 0.03965 -0.0482 0.0689 1.0000
13.250 1.3272 0.04888 0.04186 -0.0473 0.0624 1.0000
13.500 1.3285 0.05146 0.04446 -0.0461 0.0573 1.0000
13.750 1.3331 0.05377 0.04686 -0.0454 0.0525 1.0000
14.000 1.3347 0.05647 0.04957 -0.0445 0.0487 1.0000
14.250 1.3398 0.05887 0.05210 -0.0439 0.0450 1.0000
14.500 1.3420 0.06158 0.05478 -0.0433 0.0420 1.0000
14.750 1.3464 0.06420 0.05757 -0.0428 0.0391 1.0000
15.000 1.3498 0.06691 0.06037 -0.0426 0.0366 1.0000
15.250 1.3535 0.06966 0.06310 -0.0422 0.0341 1.0000
15.500 1.3553 0.07273 0.06639 -0.0422 0.0320 1.0000
15.750 1.3571 0.07577 0.06951 -0.0424 0.0300 1.0000
16.000 1.3602 0.07874 0.07251 -0.0423 0.0281 1.0000
16.250 1.3593 0.08238 0.07639 -0.0427 0.0264 1.0000
16.500 1.3596 0.08581 0.07992 -0.0432 0.0249 1.0000
16.750 1.3632 0.08877 0.08285 -0.0433 0.0233 1.0000
17.000 1.3566 0.09344 0.08781 -0.0445 0.0221 1.0000
17.250 1.3523 0.09777 0.09231 -0.0459 0.0208 1.0000
17.500 1.3526 0.10130 0.09585 -0.0470 0.0197 1.0000
17.750 1.3491 0.10565 0.10036 -0.0481 0.0188 1.0000
18.000 1.3395 0.11120 0.10619 -0.0503 0.0180 1.0000
18.250 1.3321 0.11640 0.11159 -0.0527 0.0172 1.0000
18.500 1.3267 0.12128 0.11662 -0.0551 0.0165 1.0000
18.750 1.3319 0.12388 0.11910 -0.0560 0.0155 1.0000
19.000 1.3171 0.13086 0.12638 -0.0599 0.0153 1.0000
19.250 1.3022 0.13808 0.13388 -0.0641 0.0150 1.0000
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Polar data table (+)
Polar graphs
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