EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 66 AIRFOIL (e66-il) Reynolds number: 100,000 Max Cl/Cd: 63.7 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e66-il-100000-n5.txt Download as CSV file: xf-e66-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4085 0.09315 0.08849 -0.0384 1.0000 0.0243
-8.250 -0.4222 0.08968 0.08513 -0.0378 1.0000 0.0245
-8.000 -0.4332 0.08733 0.08285 -0.0362 1.0000 0.0243
-7.750 -0.4489 0.08488 0.08050 -0.0344 1.0000 0.0242
-7.500 -0.4459 0.07899 0.07464 -0.0405 0.9948 0.0242
-7.250 -0.4350 0.07178 0.06743 -0.0495 0.9880 0.0239
-7.000 -0.4212 0.06039 0.05591 -0.0641 0.9805 0.0236
-6.750 -0.4057 0.04917 0.04419 -0.0774 0.9732 0.0233
-6.500 -0.3853 0.04120 0.03548 -0.0850 0.9673 0.0234
-6.250 -0.3570 0.03541 0.02884 -0.0899 0.9631 0.0239
-6.000 -0.3242 0.03139 0.02407 -0.0933 0.9604 0.0248
-5.750 -0.2960 0.02955 0.02206 -0.0949 0.9565 0.0269
-5.500 -0.2666 0.02801 0.02017 -0.0962 0.9522 0.0304
-5.250 -0.2330 0.02608 0.01773 -0.0977 0.9492 0.0330
-5.000 -0.1990 0.02461 0.01618 -0.0998 0.9468 0.0375
-4.750 -0.1714 0.02366 0.01497 -0.1000 0.9418 0.0430
-4.500 -0.1403 0.02258 0.01384 -0.1012 0.9377 0.0492
-4.250 -0.1060 0.02168 0.01279 -0.1027 0.9347 0.0586
-4.000 -0.0721 0.02088 0.01192 -0.1042 0.9315 0.0710
-3.750 -0.0447 0.02030 0.01135 -0.1045 0.9256 0.0902
-3.500 -0.0109 0.01972 0.01081 -0.1061 0.9219 0.1189
-3.250 0.0255 0.01921 0.01038 -0.1081 0.9192 0.1600
-3.000 0.0512 0.01889 0.01013 -0.1080 0.9125 0.1977
-2.750 0.0844 0.01851 0.00985 -0.1094 0.9083 0.2437
-2.500 0.1207 0.01813 0.00957 -0.1112 0.9054 0.2968
-2.250 0.1458 0.01792 0.00947 -0.1109 0.8982 0.3458
-2.000 0.1789 0.01761 0.00930 -0.1120 0.8939 0.4060
-1.750 0.2150 0.01727 0.00911 -0.1135 0.8910 0.4712
-1.500 0.2383 0.01716 0.00912 -0.1126 0.8831 0.5276
-1.250 0.2715 0.01688 0.00898 -0.1134 0.8791 0.5928
-1.000 0.3016 0.01665 0.00888 -0.1134 0.8744 0.6557
-0.750 0.3255 0.01650 0.00886 -0.1122 0.8671 0.7146
-0.500 0.3560 0.01620 0.00866 -0.1119 0.8634 0.7783
-0.250 0.3733 0.01608 0.00864 -0.1092 0.8547 0.8422
0.000 0.4077 0.01571 0.00831 -0.1098 0.8503 0.9463
0.250 0.4395 0.01566 0.00816 -0.1107 0.8427 1.0000
0.500 0.4750 0.01560 0.00799 -0.1122 0.8370 1.0000
0.750 0.5084 0.01557 0.00787 -0.1133 0.8305 1.0000
1.000 0.5404 0.01554 0.00778 -0.1140 0.8231 1.0000
1.250 0.5728 0.01551 0.00769 -0.1148 0.8158 1.0000
1.500 0.6058 0.01545 0.00758 -0.1157 0.8081 1.0000
1.750 0.6352 0.01546 0.00758 -0.1159 0.7988 1.0000
2.000 0.6719 0.01532 0.00741 -0.1173 0.7918 1.0000
2.250 0.6990 0.01538 0.00746 -0.1171 0.7807 1.0000
2.500 0.7292 0.01538 0.00748 -0.1173 0.7703 1.0000
2.750 0.7622 0.01532 0.00742 -0.1181 0.7602 1.0000
3.000 0.7940 0.01528 0.00738 -0.1186 0.7488 1.0000
3.250 0.8226 0.01532 0.00746 -0.1185 0.7354 1.0000
3.500 0.8516 0.01536 0.00752 -0.1185 0.7213 1.0000
3.750 0.8810 0.01540 0.00757 -0.1185 0.7063 1.0000
4.000 0.9093 0.01547 0.00766 -0.1184 0.6898 1.0000
4.250 0.9355 0.01560 0.00784 -0.1178 0.6715 1.0000
4.500 0.9624 0.01573 0.00798 -0.1174 0.6522 1.0000
4.750 0.9891 0.01588 0.00813 -0.1169 0.6315 1.0000
5.000 1.0136 0.01610 0.00835 -0.1160 0.6081 1.0000
5.250 1.0375 0.01635 0.00862 -0.1150 0.5830 1.0000
5.500 1.0606 0.01665 0.00888 -0.1139 0.5557 1.0000
5.750 1.0824 0.01701 0.00920 -0.1126 0.5263 1.0000
6.000 1.1029 0.01743 0.00956 -0.1111 0.4947 1.0000
6.250 1.1220 0.01793 0.01001 -0.1094 0.4615 1.0000
6.500 1.1396 0.01850 0.01049 -0.1075 0.4260 1.0000
6.750 1.1555 0.01917 0.01103 -0.1054 0.3893 1.0000
7.000 1.1703 0.01990 0.01165 -0.1031 0.3518 1.0000
7.250 1.1835 0.02072 0.01233 -0.1008 0.3151 1.0000
7.500 1.1961 0.02158 0.01308 -0.0983 0.2796 1.0000
7.750 1.2072 0.02250 0.01392 -0.0957 0.2468 1.0000
8.000 1.2180 0.02350 0.01481 -0.0931 0.2163 1.0000
8.250 1.2285 0.02457 0.01578 -0.0906 0.1863 1.0000
8.500 1.2383 0.02573 0.01682 -0.0882 0.1578 1.0000
8.750 1.2474 0.02697 0.01795 -0.0857 0.1313 1.0000
9.000 1.2564 0.02826 0.01916 -0.0833 0.1086 1.0000
9.250 1.2653 0.02960 0.02045 -0.0810 0.0909 1.0000
9.500 1.2737 0.03100 0.02186 -0.0787 0.0767 1.0000
9.750 1.2806 0.03254 0.02346 -0.0763 0.0656 1.0000
10.000 1.2856 0.03426 0.02515 -0.0739 0.0564 1.0000
10.250 1.2926 0.03588 0.02692 -0.0717 0.0490 1.0000
10.500 1.2947 0.03793 0.02900 -0.0693 0.0447 1.0000
10.750 1.2999 0.03983 0.03109 -0.0671 0.0407 1.0000
11.000 1.3038 0.04186 0.03323 -0.0652 0.0374 1.0000
11.250 1.3047 0.04425 0.03568 -0.0632 0.0346 1.0000
11.500 1.3105 0.04635 0.03800 -0.0616 0.0319 1.0000
11.750 1.3144 0.04870 0.04052 -0.0600 0.0300 1.0000
12.000 1.3171 0.05115 0.04313 -0.0587 0.0283 1.0000
12.250 1.3172 0.05401 0.04605 -0.0575 0.0267 1.0000
12.500 1.3210 0.05669 0.04898 -0.0564 0.0250 1.0000
12.750 1.3237 0.05954 0.05207 -0.0554 0.0235 1.0000
13.000 1.3249 0.06265 0.05541 -0.0546 0.0225 1.0000
13.250 1.3239 0.06592 0.05885 -0.0541 0.0214 1.0000
13.500 1.3213 0.06936 0.06243 -0.0539 0.0205 1.0000
13.750 1.3171 0.07315 0.06634 -0.0540 0.0197 1.0000
14.000 1.3108 0.07754 0.07094 -0.0542 0.0190 1.0000
14.250 1.3031 0.08224 0.07596 -0.0550 0.0184 1.0000
14.500 1.2936 0.08740 0.08142 -0.0562 0.0179 1.0000
14.750 1.2823 0.09306 0.08735 -0.0580 0.0175 1.0000
15.000 1.2694 0.09926 0.09382 -0.0604 0.0173 1.0000
15.250 1.2547 0.10609 0.10090 -0.0636 0.0172 1.0000
15.500 1.2386 0.11357 0.10863 -0.0676 0.0171 1.0000
15.750 1.2209 0.12183 0.11712 -0.0725 0.0172 1.0000
16.000 1.2018 0.13103 0.12654 -0.0783 0.0173 1.0000
16.250 1.1810 0.14135 0.13706 -0.0852 0.0175 1.0000
16.500 1.1587 0.15301 0.14887 -0.0931 0.0179 1.0000
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Polar data table (+)
Polar graphs
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