EPPLER 682 AIRFOIL (e682-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 682 AIRFOIL (e682-il) Reynolds number: 200,000 Max Cl/Cd: 75.41 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e682-il-200000.txt Download as CSV file: xf-e682-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 682 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2229 0.11260 0.10899 -0.0909 0.9472 0.0509
-12.000 -0.2333 0.10666 0.10307 -0.1002 0.9415 0.0528
-11.750 -0.2359 0.10148 0.09789 -0.1058 0.9359 0.0530
-11.500 -0.2224 0.09688 0.09328 -0.1045 0.9336 0.0543
-11.250 -0.2069 0.09421 0.09057 -0.1050 0.9306 0.0554
-11.000 -0.1963 0.09125 0.08758 -0.1064 0.9273 0.0568
-10.750 -0.1927 0.08785 0.08418 -0.1081 0.9232 0.0585
-10.500 -0.1938 0.08377 0.08010 -0.1108 0.9191 0.0607
-10.250 -0.2040 0.07817 0.07451 -0.1157 0.9147 0.0627
-10.000 -0.2343 0.07118 0.06746 -0.1228 0.9086 0.0638
-9.750 -0.1767 0.05780 0.05431 -0.1170 0.8987 0.0681
-9.500 -0.1880 0.05362 0.05009 -0.1185 0.8965 0.0691
-9.250 -0.2056 0.04967 0.04610 -0.1194 0.8934 0.0697
-9.000 -0.2234 0.04640 0.04276 -0.1188 0.8899 0.0704
-8.750 -0.3178 0.05598 0.05181 -0.1161 0.8891 0.0677
-8.500 -0.3116 0.05390 0.04970 -0.1148 0.8865 0.0693
-8.250 -0.3107 0.05193 0.04762 -0.1128 0.8842 0.0715
-8.000 -0.3134 0.05014 0.04560 -0.1101 0.8819 0.0748
-7.000 -0.3270 0.03597 0.02930 -0.0924 0.8693 0.0431
-6.750 -0.3063 0.03325 0.02644 -0.0916 0.8678 0.0412
-6.500 -0.2926 0.03108 0.02400 -0.0895 0.8657 0.0396
-6.250 -0.2863 0.02968 0.02235 -0.0860 0.8619 0.0379
-6.000 -0.2704 0.02812 0.02042 -0.0837 0.8590 0.0363
-5.750 -0.2471 0.02688 0.01898 -0.0828 0.8570 0.0360
-5.500 -0.2190 0.02570 0.01767 -0.0828 0.8553 0.0362
-5.250 -0.1898 0.02470 0.01660 -0.0830 0.8538 0.0370
-5.000 -0.1614 0.02387 0.01574 -0.0832 0.8526 0.0384
-4.750 -0.1596 0.02409 0.01594 -0.0789 0.8482 0.0394
-4.500 -0.1597 0.02434 0.01617 -0.0743 0.8432 0.0406
-4.250 -0.1403 0.02387 0.01566 -0.0729 0.8405 0.0434
-4.000 -0.1180 0.02318 0.01500 -0.0721 0.8386 0.0470
-3.750 -0.0905 0.02267 0.01442 -0.0720 0.8371 0.0528
-3.500 -0.1195 0.02378 0.01553 -0.0625 0.8280 0.0530
-3.250 -0.1007 0.02303 0.01493 -0.0610 0.8251 0.0798
-3.000 -0.0948 0.02084 0.01433 -0.0581 0.8228 0.3955
-2.750 -0.1197 0.02114 0.01507 -0.0494 0.8140 0.4921
-2.500 -0.1205 0.02173 0.01693 -0.0407 0.8100 0.7809
-2.250 -0.0946 0.02248 0.01753 -0.0389 0.8079 0.8343
-2.000 -0.0626 0.02369 0.01866 -0.0365 0.8067 0.8658
-1.750 -0.0284 0.02495 0.01984 -0.0352 0.8040 0.8929
-1.500 0.2042 0.02557 0.02006 -0.0720 0.8134 0.9131
-1.250 0.2645 0.02538 0.01975 -0.0781 0.8124 0.9238
-1.000 0.2993 0.02532 0.01960 -0.0796 0.8098 0.9341
-0.750 0.3607 0.02475 0.01894 -0.0863 0.8089 0.9384
-0.500 0.4003 0.02444 0.01855 -0.0886 0.8073 0.9452
-0.250 0.4475 0.02394 0.01797 -0.0925 0.8060 0.9503
0.000 0.4515 0.02472 0.01879 -0.0893 0.7968 0.9594
0.250 0.4964 0.02422 0.01825 -0.0930 0.7945 0.9634
0.500 0.5386 0.02375 0.01773 -0.0960 0.7926 0.9674
0.750 0.5728 0.02341 0.01735 -0.0972 0.7908 0.9719
1.000 0.5909 0.02381 0.01780 -0.0967 0.7819 0.9768
1.250 0.6274 0.02342 0.01739 -0.0987 0.7789 0.9805
1.500 0.6620 0.02298 0.01693 -0.1000 0.7767 0.9837
1.750 0.6993 0.02257 0.01653 -0.1021 0.7733 0.9865
2.000 0.7205 0.02272 0.01673 -0.1018 0.7650 0.9900
2.250 0.7573 0.02212 0.01613 -0.1035 0.7622 0.9923
2.500 0.7952 0.02150 0.01550 -0.1053 0.7600 0.9944
2.750 0.8133 0.02174 0.01583 -0.1044 0.7506 0.9968
3.000 0.8500 0.02111 0.01521 -0.1061 0.7474 0.9987
3.250 0.8875 0.02038 0.01447 -0.1077 0.7447 1.0000
3.500 0.8960 0.02070 0.01489 -0.1046 0.7352 1.0000
3.750 0.9248 0.02012 0.01433 -0.1046 0.7314 1.0000
4.000 0.9458 0.01988 0.01414 -0.1033 0.7253 1.0000
4.250 0.9655 0.01963 0.01394 -0.1018 0.7182 1.0000
4.500 0.9978 0.01887 0.01321 -0.1023 0.7147 1.0000
4.750 1.0094 0.01887 0.01331 -0.0994 0.7047 1.0000
5.000 1.0413 0.01806 0.01252 -0.0997 0.7001 1.0000
5.250 1.0541 0.01795 0.01252 -0.0970 0.6897 1.0000
5.500 1.0861 0.01712 0.01172 -0.0974 0.6843 1.0000
5.750 1.0969 0.01704 0.01174 -0.0942 0.6726 1.0000
6.000 1.1108 0.01682 0.01162 -0.0916 0.6610 1.0000
6.250 1.1267 0.01655 0.01143 -0.0892 0.6488 1.0000
6.500 1.1424 0.01627 0.01120 -0.0868 0.6343 1.0000
6.750 1.1600 0.01596 0.01091 -0.0846 0.6173 1.0000
7.000 1.1793 0.01569 0.01060 -0.0828 0.5980 1.0000
7.250 1.1892 0.01577 0.01064 -0.0794 0.5751 1.0000
7.500 1.1976 0.01593 0.01070 -0.0757 0.5500 1.0000
7.750 1.1994 0.01626 0.01092 -0.0709 0.5249 1.0000
8.000 1.1924 0.01666 0.01125 -0.0646 0.5019 1.0000
8.250 1.1770 0.01703 0.01155 -0.0567 0.4822 1.0000
8.500 1.1603 0.01750 0.01192 -0.0488 0.4617 1.0000
8.750 1.1452 0.01802 0.01239 -0.0416 0.4422 1.0000
9.000 1.1303 0.01859 0.01289 -0.0346 0.4225 1.0000
9.250 1.1152 0.01921 0.01342 -0.0279 0.4031 1.0000
9.500 1.1003 0.01983 0.01400 -0.0213 0.3832 1.0000
9.750 1.0871 0.02047 0.01457 -0.0153 0.3633 1.0000
10.000 1.0774 0.02133 0.01531 -0.0103 0.3400 1.0000
10.250 1.0757 0.02242 0.01630 -0.0071 0.3137 1.0000
10.500 1.0776 0.02365 0.01743 -0.0048 0.2866 1.0000
10.750 1.0800 0.02502 0.01869 -0.0028 0.2587 1.0000
11.000 1.0820 0.02655 0.02008 -0.0009 0.2292 1.0000
11.250 1.0863 0.02805 0.02148 0.0005 0.2041 1.0000
11.500 1.0903 0.02966 0.02300 0.0019 0.1798 1.0000
11.750 1.0958 0.03125 0.02452 0.0031 0.1558 1.0000
12.000 1.0997 0.03304 0.02621 0.0042 0.1312 1.0000
12.250 1.1016 0.03506 0.02810 0.0054 0.1041 1.0000
12.500 1.0977 0.03763 0.03043 0.0069 0.0733 1.0000
12.750 1.0879 0.04088 0.03346 0.0086 0.0470 1.0000
13.000 1.0851 0.04364 0.03620 0.0098 0.0385 1.0000
13.250 1.0831 0.04643 0.03901 0.0106 0.0338 1.0000
13.500 1.0841 0.04903 0.04171 0.0112 0.0318 1.0000
13.750 1.0870 0.05153 0.04430 0.0116 0.0295 1.0000
14.000 1.0899 0.05406 0.04691 0.0119 0.0281 1.0000
14.250 1.0905 0.05687 0.04976 0.0122 0.0270 1.0000
14.500 1.0925 0.05951 0.05243 0.0128 0.0260 1.0000
14.750 1.1005 0.06165 0.05470 0.0130 0.0252 1.0000
15.000 1.1097 0.06366 0.05681 0.0132 0.0246 1.0000
15.250 1.1194 0.06567 0.05893 0.0134 0.0239 1.0000
15.500 1.1275 0.06791 0.06126 0.0135 0.0229 1.0000
15.750 1.1353 0.07019 0.06363 0.0133 0.0221 1.0000
16.000 1.1436 0.07239 0.06588 0.0132 0.0213 1.0000
16.250 1.1593 0.07407 0.06759 0.0139 0.0206 1.0000
16.500 1.1681 0.07672 0.07042 0.0141 0.0204 1.0000
16.750 1.1707 0.07996 0.07388 0.0138 0.0203 1.0000
17.000 1.1715 0.08346 0.07759 0.0132 0.0202 1.0000
17.250 1.1677 0.08758 0.08194 0.0124 0.0201 1.0000
17.500 1.1619 0.09207 0.08667 0.0113 0.0201 1.0000
17.750 1.1529 0.09709 0.09192 0.0097 0.0201 1.0000
18.000 1.1415 0.10255 0.09762 0.0077 0.0201 1.0000
18.250 1.1305 0.10816 0.10344 0.0054 0.0202 1.0000
18.500 1.1164 0.11439 0.10989 0.0026 0.0202 1.0000
18.750 1.1021 0.12088 0.11658 -0.0007 0.0203 1.0000
19.000 1.0867 0.12785 0.12373 -0.0044 0.0204 1.0000
19.250 1.0733 0.13458 0.13065 -0.0086 0.0206 1.0000
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Polar data table (+)
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