EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 66 AIRFOIL (e66-il) Reynolds number: 100,000 Max Cl/Cd: 64.57 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e66-il-100000.txt Download as CSV file: xf-e66-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 66 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4147 0.10419 0.09978 -0.0318 1.0000 0.1025
-7.750 -0.4430 0.10363 0.09935 -0.0304 1.0000 0.1028
-7.500 -0.4645 0.10171 0.09754 -0.0325 1.0000 0.1031
-7.250 -0.4188 0.09560 0.09134 -0.0252 1.0000 0.1076
-7.000 -0.4284 0.09384 0.08965 -0.0228 1.0000 0.1098
-6.750 -0.4427 0.09218 0.08808 -0.0208 1.0000 0.1120
-6.500 -0.4601 0.08977 0.08576 -0.0234 1.0000 0.1155
-6.250 -0.4749 0.08466 0.08070 -0.0325 1.0000 0.1180
-6.000 -0.4690 0.08266 0.07874 -0.0256 1.0000 0.1199
-5.750 -0.4660 0.08025 0.07634 -0.0236 1.0000 0.1230
-5.500 -0.4634 0.07352 0.06950 -0.0372 1.0000 0.1325
-5.250 -0.4581 0.07129 0.06733 -0.0327 1.0000 0.1344
-5.000 -0.4501 0.06865 0.06469 -0.0317 1.0000 0.1384
-4.750 -0.3677 0.03911 0.03276 -0.0657 1.0000 0.0619
-4.500 -0.3374 0.03452 0.02757 -0.0687 1.0000 0.0636
-4.250 -0.3087 0.03146 0.02407 -0.0702 1.0000 0.0651
-4.000 -0.2806 0.02925 0.02148 -0.0710 1.0000 0.0672
-3.750 -0.2535 0.02793 0.01973 -0.0713 1.0000 0.0738
-3.500 -0.2261 0.02617 0.01774 -0.0718 1.0000 0.0794
-3.250 -0.1936 0.02518 0.01652 -0.0730 0.9982 0.0911
-3.000 -0.1515 0.02428 0.01562 -0.0760 0.9938 0.1096
-2.750 -0.1113 0.02357 0.01489 -0.0787 0.9883 0.1455
-2.500 -0.0687 0.02318 0.01476 -0.0821 0.9838 0.2056
-2.250 -0.0334 0.02280 0.01466 -0.0843 0.9769 0.2716
-2.000 0.0083 0.02266 0.01486 -0.0874 0.9720 0.3580
-1.750 0.0396 0.02242 0.01494 -0.0886 0.9643 0.4451
-1.500 0.0788 0.02243 0.01532 -0.0908 0.9591 0.5530
-1.250 0.1045 0.02230 0.01549 -0.0902 0.9506 0.6504
-1.000 0.1330 0.02230 0.01579 -0.0896 0.9441 0.7594
-0.750 0.1506 0.02198 0.01575 -0.0865 0.9352 0.9056
-0.500 0.1904 0.02208 0.01559 -0.0897 0.9263 1.0000
-0.250 0.2342 0.02242 0.01567 -0.0933 0.9199 1.0000
0.000 0.2659 0.02271 0.01577 -0.0947 0.9106 1.0000
0.250 0.3114 0.02297 0.01585 -0.0982 0.9049 1.0000
0.500 0.3400 0.02324 0.01599 -0.0989 0.8946 1.0000
0.750 0.3788 0.02346 0.01609 -0.1011 0.8874 1.0000
1.000 0.4143 0.02362 0.01617 -0.1028 0.8787 1.0000
1.250 0.4461 0.02384 0.01631 -0.1037 0.8691 1.0000
1.500 0.4904 0.02380 0.01622 -0.1066 0.8630 1.0000
1.750 0.5191 0.02399 0.01638 -0.1069 0.8521 1.0000
2.000 0.5682 0.02371 0.01608 -0.1103 0.8475 1.0000
2.250 0.5953 0.02386 0.01623 -0.1103 0.8359 1.0000
2.500 0.6279 0.02385 0.01623 -0.1110 0.8259 1.0000
2.750 0.6756 0.02329 0.01571 -0.1138 0.8204 1.0000
3.000 0.7067 0.02320 0.01567 -0.1140 0.8094 1.0000
3.250 0.7614 0.02225 0.01479 -0.1177 0.8053 1.0000
3.500 0.7939 0.02201 0.01461 -0.1180 0.7936 1.0000
3.750 0.8327 0.02152 0.01423 -0.1192 0.7836 1.0000
4.000 0.8843 0.02049 0.01329 -0.1221 0.7765 1.0000
4.250 0.9192 0.02004 0.01293 -0.1225 0.7634 1.0000
4.500 0.9557 0.01952 0.01252 -0.1231 0.7497 1.0000
4.750 0.9931 0.01898 0.01206 -0.1237 0.7347 1.0000
5.000 1.0311 0.01843 0.01161 -0.1244 0.7180 1.0000
5.250 1.0566 0.01831 0.01156 -0.1232 0.6966 1.0000
5.500 1.0901 0.01798 0.01126 -0.1232 0.6749 1.0000
5.750 1.1142 0.01797 0.01130 -0.1217 0.6492 1.0000
6.000 1.1387 0.01798 0.01135 -0.1203 0.6212 1.0000
6.250 1.1616 0.01809 0.01144 -0.1186 0.5903 1.0000
6.500 1.1823 0.01831 0.01161 -0.1167 0.5564 1.0000
6.750 1.1993 0.01867 0.01192 -0.1142 0.5187 1.0000
7.000 1.2148 0.01917 0.01231 -0.1115 0.4784 1.0000
7.250 1.2277 0.01980 0.01283 -0.1085 0.4355 1.0000
7.500 1.2381 0.02060 0.01345 -0.1052 0.3908 1.0000
7.750 1.2461 0.02156 0.01420 -0.1017 0.3451 1.0000
8.000 1.2520 0.02269 0.01510 -0.0980 0.3003 1.0000
8.250 1.2551 0.02392 0.01609 -0.0940 0.2581 1.0000
8.500 1.2577 0.02532 0.01724 -0.0901 0.2192 1.0000
8.750 1.2602 0.02684 0.01853 -0.0864 0.1847 1.0000
9.000 1.2628 0.02853 0.02003 -0.0830 0.1552 1.0000
9.250 1.2665 0.03032 0.02168 -0.0798 0.1291 1.0000
9.500 1.2714 0.03232 0.02358 -0.0769 0.1071 1.0000
9.750 1.2780 0.03437 0.02552 -0.0742 0.0907 1.0000
10.000 1.2881 0.03646 0.02757 -0.0721 0.0780 1.0000
10.250 1.3075 0.03885 0.03002 -0.0710 0.0684 1.0000
10.500 1.3288 0.04138 0.03252 -0.0704 0.0608 1.0000
10.750 1.3495 0.04374 0.03512 -0.0694 0.0556 1.0000
11.000 1.3810 0.04759 0.03906 -0.0705 0.0505 1.0000
11.250 1.3858 0.04990 0.04178 -0.0676 0.0479 1.0000
11.500 1.3947 0.05301 0.04524 -0.0656 0.0459 1.0000
11.750 1.4004 0.05635 0.04890 -0.0634 0.0446 1.0000
12.000 1.4010 0.05961 0.05243 -0.0611 0.0434 1.0000
12.250 1.4011 0.06307 0.05607 -0.0591 0.0420 1.0000
12.500 1.3962 0.06845 0.06169 -0.0575 0.0410 1.0000
12.750 1.3792 0.07293 0.06648 -0.0549 0.0407 1.0000
13.000 1.3599 0.07672 0.07058 -0.0527 0.0405 1.0000
13.250 1.3399 0.08109 0.07524 -0.0513 0.0404 1.0000
13.500 1.3195 0.08603 0.08046 -0.0507 0.0405 1.0000
13.750 1.2986 0.09151 0.08619 -0.0510 0.0406 1.0000
14.000 1.2777 0.09755 0.09245 -0.0521 0.0407 1.0000
14.250 1.2564 0.10323 0.09839 -0.0540 0.0409 1.0000
14.500 1.2298 0.10945 0.10490 -0.0575 0.0416 1.0000
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Polar data table (+)
Polar graphs
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