EPPLER 668 AIRFOIL (e668-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 668 AIRFOIL (e668-il) Reynolds number: 500,000 Max Cl/Cd: 113.23 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e668-il-500000-n5.txt Download as CSV file: xf-e668-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.1806 0.09268 0.08928 -0.1168 0.8408 0.0045
-12.000 -0.3582 0.04895 0.04533 -0.1379 0.8365 0.0040
-11.750 -0.3853 0.04113 0.03729 -0.1440 0.8343 0.0039
-11.500 -0.4068 0.03648 0.03245 -0.1458 0.8320 0.0039
-11.250 -0.4221 0.03327 0.02905 -0.1454 0.8297 0.0039
-11.000 -0.4351 0.03061 0.02617 -0.1437 0.8277 0.0039
-10.750 -0.4425 0.02863 0.02401 -0.1414 0.8258 0.0039
-10.500 -0.4511 0.02691 0.02206 -0.1380 0.8238 0.0039
-10.250 -0.4472 0.02534 0.02027 -0.1360 0.8221 0.0039
-10.000 -0.4404 0.02371 0.01839 -0.1342 0.8205 0.0040
-9.750 -0.4285 0.02236 0.01682 -0.1328 0.8192 0.0040
-9.500 -0.4131 0.02128 0.01557 -0.1318 0.8182 0.0040
-9.250 -0.3966 0.02020 0.01433 -0.1307 0.8170 0.0041
-9.000 -0.3785 0.01921 0.01318 -0.1298 0.8156 0.0042
-8.750 -0.3588 0.01836 0.01221 -0.1291 0.8142 0.0043
-8.500 -0.3381 0.01757 0.01128 -0.1285 0.8129 0.0044
-8.250 -0.3160 0.01691 0.01051 -0.1280 0.8117 0.0045
-8.000 -0.2941 0.01619 0.00970 -0.1275 0.8104 0.0046
-7.750 -0.2714 0.01554 0.00895 -0.1271 0.8091 0.0049
-7.500 -0.2473 0.01503 0.00837 -0.1269 0.8078 0.0053
-7.250 -0.2226 0.01458 0.00786 -0.1267 0.8068 0.0056
-7.000 -0.1975 0.01415 0.00734 -0.1265 0.8058 0.0061
-6.750 -0.1721 0.01374 0.00685 -0.1264 0.8047 0.0066
-6.500 -0.1464 0.01337 0.00643 -0.1264 0.8036 0.0074
-6.250 -0.1206 0.01304 0.00606 -0.1262 0.8024 0.0086
-6.000 -0.0949 0.01271 0.00572 -0.1262 0.8011 0.0101
-5.750 -0.0687 0.01242 0.00542 -0.1261 0.7999 0.0124
-5.500 -0.0423 0.01216 0.00517 -0.1262 0.7986 0.0166
-5.250 -0.0158 0.01190 0.00492 -0.1262 0.7972 0.0218
-5.000 0.0109 0.01163 0.00468 -0.1263 0.7957 0.0291
-4.750 0.0379 0.01138 0.00446 -0.1264 0.7943 0.0379
-4.500 0.0650 0.01113 0.00425 -0.1266 0.7931 0.0514
-4.250 0.0923 0.01087 0.00405 -0.1268 0.7918 0.0704
-4.000 0.1198 0.01062 0.00387 -0.1270 0.7905 0.0935
-3.750 0.1475 0.01039 0.00372 -0.1273 0.7892 0.1201
-3.500 0.1754 0.01017 0.00358 -0.1276 0.7880 0.1539
-3.250 0.2021 0.00991 0.00348 -0.1278 0.7863 0.1974
-3.000 0.2288 0.00962 0.00338 -0.1279 0.7843 0.2503
-2.750 0.2560 0.00936 0.00329 -0.1282 0.7822 0.3047
-2.500 0.2836 0.00908 0.00320 -0.1285 0.7801 0.3638
-2.250 0.3116 0.00882 0.00311 -0.1289 0.7782 0.4242
-2.000 0.3399 0.00854 0.00302 -0.1293 0.7763 0.4923
-1.750 0.3684 0.00828 0.00295 -0.1297 0.7745 0.5599
-1.500 0.3969 0.00809 0.00292 -0.1300 0.7726 0.6210
-1.250 0.4238 0.00799 0.00297 -0.1299 0.7700 0.6671
-1.000 0.4506 0.00795 0.00305 -0.1297 0.7670 0.7027
-0.750 0.4782 0.00795 0.00308 -0.1297 0.7642 0.7273
-0.500 0.5065 0.00795 0.00309 -0.1298 0.7615 0.7438
-0.250 0.5350 0.00795 0.00308 -0.1299 0.7591 0.7561
0.000 0.5636 0.00796 0.00307 -0.1301 0.7565 0.7664
0.250 0.5906 0.00799 0.00312 -0.1300 0.7525 0.7763
0.500 0.6177 0.00800 0.00315 -0.1299 0.7484 0.7832
0.750 0.6459 0.00799 0.00312 -0.1300 0.7448 0.7905
1.000 0.6739 0.00798 0.00311 -0.1301 0.7410 0.7964
1.250 0.7002 0.00801 0.00318 -0.1298 0.7357 0.8023
1.500 0.7281 0.00801 0.00317 -0.1299 0.7307 0.8084
1.750 0.7551 0.00801 0.00319 -0.1298 0.7253 0.8129
2.000 0.7813 0.00802 0.00322 -0.1295 0.7184 0.8176
2.250 0.8085 0.00803 0.00321 -0.1294 0.7116 0.8226
2.500 0.8350 0.00805 0.00323 -0.1292 0.7026 0.8266
2.750 0.8607 0.00807 0.00326 -0.1288 0.6928 0.8297
3.000 0.8861 0.00811 0.00328 -0.1284 0.6810 0.8330
3.250 0.9110 0.00818 0.00331 -0.1279 0.6664 0.8362
3.500 0.9352 0.00830 0.00337 -0.1272 0.6492 0.8393
3.750 0.9579 0.00846 0.00346 -0.1263 0.6292 0.8419
4.000 0.9781 0.00867 0.00359 -0.1249 0.6067 0.8444
4.250 0.9966 0.00895 0.00377 -0.1232 0.5811 0.8471
4.500 1.0135 0.00928 0.00400 -0.1212 0.5550 0.8502
4.750 1.0287 0.00966 0.00426 -0.1189 0.5282 0.8534
5.250 1.0533 0.01040 0.00483 -0.1131 0.4783 0.8596
5.500 1.0622 0.01084 0.00518 -0.1097 0.4536 0.8631
5.750 1.0735 0.01130 0.00556 -0.1068 0.4303 0.8668
6.250 1.0941 0.01237 0.00646 -0.1010 0.3811 0.8740
6.500 1.1035 0.01297 0.00697 -0.0981 0.3572 0.8776
6.750 1.1150 0.01355 0.00749 -0.0956 0.3349 0.8816
7.000 1.1266 0.01420 0.00806 -0.0933 0.3133 0.8856
7.250 1.1379 0.01486 0.00865 -0.0910 0.2910 0.8893
7.500 1.1496 0.01552 0.00926 -0.0887 0.2705 0.8939
7.750 1.1612 0.01625 0.00992 -0.0866 0.2502 0.8989
8.000 1.1734 0.01697 0.01058 -0.0847 0.2292 0.9038
8.250 1.1841 0.01774 0.01129 -0.0825 0.2079 0.9098
8.750 1.2064 0.01926 0.01272 -0.0784 0.1712 0.9291
9.000 1.2200 0.02001 0.01346 -0.0769 0.1540 0.9519
9.500 1.2466 0.02183 0.01513 -0.0743 0.1202 1.0000
9.750 1.2596 0.02279 0.01603 -0.0729 0.1058 1.0000
10.250 1.2865 0.02468 0.01785 -0.0704 0.0827 1.0000
10.500 1.2997 0.02564 0.01880 -0.0692 0.0738 1.0000
10.750 1.3122 0.02667 0.01981 -0.0680 0.0649 1.0000
11.000 1.3247 0.02772 0.02085 -0.0667 0.0578 1.0000
11.250 1.3366 0.02882 0.02195 -0.0655 0.0511 1.0000
11.500 1.3488 0.02991 0.02306 -0.0643 0.0454 1.0000
11.750 1.3600 0.03111 0.02427 -0.0631 0.0404 1.0000
12.000 1.3707 0.03235 0.02552 -0.0619 0.0356 1.0000
12.250 1.3820 0.03359 0.02679 -0.0608 0.0317 1.0000
12.500 1.3913 0.03499 0.02821 -0.0596 0.0280 1.0000
12.750 1.4016 0.03636 0.02962 -0.0585 0.0251 1.0000
13.000 1.4105 0.03786 0.03116 -0.0574 0.0222 1.0000
13.250 1.4196 0.03939 0.03274 -0.0564 0.0201 1.0000
13.500 1.4281 0.04101 0.03441 -0.0554 0.0182 1.0000
13.750 1.4363 0.04269 0.03614 -0.0545 0.0164 1.0000
14.000 1.4438 0.04447 0.03798 -0.0536 0.0147 1.0000
14.250 1.4512 0.04631 0.03989 -0.0529 0.0132 1.0000
14.500 1.4575 0.04831 0.04196 -0.0521 0.0120 1.0000
14.750 1.4641 0.05033 0.04405 -0.0515 0.0111 1.0000
15.000 1.4687 0.05260 0.04637 -0.0509 0.0098 1.0000
15.250 1.4744 0.05480 0.04868 -0.0504 0.0091 1.0000
15.500 1.4789 0.05721 0.05118 -0.0500 0.0085 1.0000
15.750 1.4819 0.05985 0.05389 -0.0498 0.0078 1.0000
16.000 1.4852 0.06252 0.05666 -0.0496 0.0072 1.0000
16.250 1.4877 0.06535 0.05960 -0.0495 0.0067 1.0000
16.500 1.4891 0.06839 0.06275 -0.0496 0.0062 1.0000
16.750 1.4886 0.07176 0.06621 -0.0499 0.0057 1.0000
17.000 1.4889 0.07513 0.06970 -0.0503 0.0053 1.0000
17.250 1.4881 0.07872 0.07341 -0.0509 0.0049 1.0000
17.500 1.4858 0.08260 0.07739 -0.0517 0.0045 1.0000
17.750 1.4821 0.08679 0.08170 -0.0527 0.0042 1.0000
18.000 1.4781 0.09113 0.08616 -0.0538 0.0040 1.0000
18.250 1.4737 0.09562 0.09078 -0.0552 0.0036 1.0000
18.500 1.4680 0.10042 0.09572 -0.0569 0.0035 1.0000
18.750 1.4614 0.10543 0.10085 -0.0588 0.0033 1.0000
19.000 1.4539 0.11070 0.10626 -0.0609 0.0031 1.0000
19.250 1.4450 0.11630 0.11199 -0.0634 0.0030 1.0000
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Polar data table (+)
Polar graphs
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