EPPLER 668 AIRFOIL (e668-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 668 AIRFOIL (e668-il) Reynolds number: 1,000,000 Max Cl/Cd: 135.79 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e668-il-1000000-n5.txt Download as CSV file: xf-e668-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.3661 0.07548 0.07250 -0.1218 0.8178 0.0026
-13.500 -0.4336 0.05992 0.05684 -0.1295 0.8167 0.0026
-13.250 -0.4717 0.04802 0.04478 -0.1372 0.8154 0.0025
-13.000 -0.4966 0.04002 0.03660 -0.1434 0.8140 0.0025
-12.750 -0.5154 0.03514 0.03157 -0.1460 0.8124 0.0025
-12.500 -0.5327 0.03150 0.02774 -0.1463 0.8109 0.0025
-12.250 -0.5423 0.02900 0.02509 -0.1453 0.8092 0.0025
-12.000 -0.5455 0.02721 0.02316 -0.1438 0.8076 0.0025
-11.750 -0.5505 0.02545 0.02124 -0.1415 0.8060 0.0025
-11.500 -0.5555 0.02396 0.01959 -0.1385 0.8044 0.0025
-11.250 -0.5548 0.02284 0.01833 -0.1357 0.8031 0.0025
-11.000 -0.5468 0.02161 0.01696 -0.1339 0.8023 0.0025
-10.750 -0.5344 0.02056 0.01578 -0.1325 0.8013 0.0025
-10.500 -0.5207 0.01947 0.01455 -0.1312 0.8002 0.0026
-10.250 -0.5034 0.01862 0.01359 -0.1303 0.7992 0.0026
-10.000 -0.4862 0.01767 0.01249 -0.1293 0.7983 0.0026
-9.750 -0.4668 0.01686 0.01157 -0.1286 0.7973 0.0026
-9.500 -0.4454 0.01621 0.01083 -0.1281 0.7962 0.0026
-9.250 -0.4239 0.01553 0.01005 -0.1276 0.7951 0.0026
-9.000 -0.4014 0.01490 0.00933 -0.1271 0.7941 0.0027
-8.750 -0.3782 0.01433 0.00867 -0.1268 0.7932 0.0027
-8.500 -0.3545 0.01379 0.00804 -0.1265 0.7922 0.0028
-8.250 -0.3299 0.01333 0.00751 -0.1263 0.7912 0.0028
-8.000 -0.3049 0.01290 0.00702 -0.1262 0.7901 0.0028
-7.750 -0.2794 0.01251 0.00655 -0.1261 0.7891 0.0028
-7.500 -0.2545 0.01200 0.00596 -0.1259 0.7880 0.0030
-7.250 -0.2285 0.01163 0.00555 -0.1259 0.7873 0.0032
-7.000 -0.2022 0.01129 0.00519 -0.1259 0.7864 0.0035
-6.750 -0.1755 0.01099 0.00487 -0.1260 0.7855 0.0038
-6.500 -0.1486 0.01072 0.00457 -0.1260 0.7845 0.0042
-6.250 -0.1215 0.01046 0.00428 -0.1261 0.7835 0.0048
-6.000 -0.0943 0.01020 0.00401 -0.1263 0.7825 0.0056
-5.750 -0.0668 0.00997 0.00378 -0.1264 0.7814 0.0068
-5.500 -0.0393 0.00975 0.00355 -0.1266 0.7802 0.0090
-5.250 -0.0116 0.00955 0.00335 -0.1268 0.7790 0.0114
-5.000 0.0163 0.00936 0.00317 -0.1270 0.7780 0.0148
-4.750 0.0442 0.00918 0.00300 -0.1273 0.7769 0.0186
-4.500 0.0722 0.00899 0.00283 -0.1275 0.7757 0.0243
-4.250 0.1002 0.00879 0.00267 -0.1278 0.7745 0.0344
-4.000 0.1281 0.00857 0.00252 -0.1281 0.7731 0.0529
-3.750 0.1560 0.00833 0.00239 -0.1284 0.7717 0.0783
-3.500 0.1840 0.00812 0.00226 -0.1287 0.7702 0.1010
-3.250 0.2121 0.00792 0.00215 -0.1290 0.7684 0.1258
-3.000 0.2403 0.00772 0.00205 -0.1293 0.7666 0.1557
-2.750 0.2685 0.00748 0.00195 -0.1297 0.7647 0.1988
-2.500 0.2968 0.00726 0.00186 -0.1301 0.7626 0.2418
-2.250 0.3252 0.00704 0.00176 -0.1305 0.7605 0.2885
-2.000 0.3538 0.00684 0.00168 -0.1309 0.7583 0.3337
-1.750 0.3824 0.00664 0.00163 -0.1314 0.7561 0.3852
-1.500 0.4109 0.00643 0.00158 -0.1318 0.7536 0.4380
-1.250 0.4396 0.00623 0.00154 -0.1323 0.7507 0.4918
-1.000 0.4684 0.00603 0.00150 -0.1327 0.7478 0.5487
-0.750 0.4972 0.00586 0.00146 -0.1331 0.7447 0.6023
-0.500 0.5258 0.00573 0.00145 -0.1335 0.7416 0.6503
-0.250 0.5544 0.00565 0.00148 -0.1338 0.7375 0.6850
0.000 0.5829 0.00562 0.00150 -0.1340 0.7330 0.7100
0.250 0.6111 0.00561 0.00151 -0.1341 0.7286 0.7280
0.500 0.6395 0.00562 0.00155 -0.1344 0.7234 0.7426
0.750 0.6676 0.00564 0.00157 -0.1345 0.7171 0.7533
1.000 0.6956 0.00568 0.00159 -0.1346 0.7104 0.7618
1.250 0.7230 0.00571 0.00162 -0.1346 0.7017 0.7685
1.500 0.7505 0.00577 0.00165 -0.1346 0.6921 0.7750
1.750 0.7771 0.00585 0.00170 -0.1344 0.6810 0.7803
2.000 0.8029 0.00596 0.00177 -0.1341 0.6674 0.7858
2.250 0.8283 0.00610 0.00184 -0.1337 0.6511 0.7910
2.500 0.8525 0.00628 0.00194 -0.1331 0.6303 0.7951
2.750 0.8749 0.00651 0.00209 -0.1321 0.6069 0.7993
3.000 0.8967 0.00677 0.00225 -0.1311 0.5814 0.8037
3.250 0.9183 0.00705 0.00243 -0.1300 0.5573 0.8075
3.500 0.9387 0.00737 0.00263 -0.1287 0.5316 0.8105
3.750 0.9583 0.00768 0.00285 -0.1272 0.5047 0.8131
4.000 0.9771 0.00801 0.00308 -0.1256 0.4783 0.8158
4.500 1.0139 0.00868 0.00355 -0.1223 0.4290 0.8209
4.750 1.0301 0.00905 0.00381 -0.1202 0.4044 0.8235
5.000 1.0449 0.00937 0.00404 -0.1179 0.3822 0.8258
5.250 1.0573 0.00977 0.00435 -0.1151 0.3586 0.8283
5.500 1.0713 0.01016 0.00466 -0.1126 0.3356 0.8308
5.750 1.0845 0.01061 0.00502 -0.1102 0.3130 0.8335
6.000 1.0989 0.01104 0.00537 -0.1079 0.2926 0.8363
6.250 1.1135 0.01150 0.00575 -0.1058 0.2727 0.8390
6.500 1.1273 0.01199 0.00616 -0.1036 0.2530 0.8415
6.750 1.1406 0.01251 0.00661 -0.1014 0.2338 0.8440
7.000 1.1540 0.01306 0.00709 -0.0993 0.2139 0.8467
7.250 1.1681 0.01361 0.00759 -0.0973 0.1966 0.8495
7.500 1.1810 0.01425 0.00814 -0.0953 0.1778 0.8522
7.750 1.1945 0.01489 0.00872 -0.0934 0.1607 0.8548
8.000 1.2085 0.01553 0.00930 -0.0916 0.1448 0.8576
8.250 1.2222 0.01619 0.00991 -0.0898 0.1297 0.8604
8.500 1.2354 0.01690 0.01057 -0.0880 0.1140 0.8634
8.750 1.2485 0.01765 0.01125 -0.0863 0.0993 0.8664
9.000 1.2631 0.01834 0.01191 -0.0848 0.0890 0.8696
9.250 1.2773 0.01905 0.01260 -0.0832 0.0796 0.8730
9.500 1.2905 0.01982 0.01334 -0.0816 0.0695 0.8771
9.750 1.3053 0.02051 0.01404 -0.0802 0.0624 0.8813
10.000 1.3196 0.02126 0.01479 -0.0788 0.0560 0.8857
10.250 1.3329 0.02205 0.01558 -0.0773 0.0495 0.8907
10.500 1.3462 0.02284 0.01639 -0.0758 0.0436 0.8971
10.750 1.3587 0.02367 0.01724 -0.0743 0.0380 0.9048
11.250 1.3821 0.02536 0.01903 -0.0710 0.0286 0.9630
11.750 1.4069 0.02734 0.02102 -0.0685 0.0206 1.0000
12.000 1.4189 0.02841 0.02210 -0.0673 0.0179 1.0000
12.250 1.4305 0.02952 0.02321 -0.0660 0.0152 1.0000
12.500 1.4429 0.03059 0.02431 -0.0649 0.0137 1.0000
12.750 1.4541 0.03177 0.02553 -0.0638 0.0123 1.0000
13.000 1.4661 0.03292 0.02671 -0.0627 0.0110 1.0000
13.250 1.4763 0.03423 0.02805 -0.0616 0.0100 1.0000
13.500 1.4877 0.03546 0.02933 -0.0606 0.0093 1.0000
13.750 1.4980 0.03681 0.03073 -0.0596 0.0085 1.0000
14.000 1.5070 0.03831 0.03228 -0.0585 0.0076 1.0000
14.250 1.5170 0.03976 0.03378 -0.0576 0.0070 1.0000
14.500 1.5257 0.04134 0.03541 -0.0567 0.0063 1.0000
14.750 1.5335 0.04306 0.03718 -0.0558 0.0057 1.0000
15.000 1.5414 0.04481 0.03899 -0.0550 0.0049 1.0000
15.250 1.5477 0.04675 0.04099 -0.0542 0.0043 1.0000
15.500 1.5545 0.04871 0.04300 -0.0536 0.0040 1.0000
15.750 1.5594 0.05089 0.04525 -0.0529 0.0033 1.0000
16.000 1.5633 0.05324 0.04767 -0.0524 0.0028 1.0000
16.250 1.5682 0.05555 0.05005 -0.0519 0.0026 1.0000
16.500 1.5716 0.05809 0.05267 -0.0516 0.0023 1.0000
16.750 1.5726 0.06099 0.05565 -0.0513 0.0019 1.0000
17.000 1.5746 0.06384 0.05858 -0.0513 0.0017 1.0000
17.250 1.5759 0.06683 0.06166 -0.0513 0.0016 1.0000
17.500 1.5758 0.07010 0.06503 -0.0515 0.0014 1.0000
17.750 1.5755 0.07348 0.06851 -0.0519 0.0013 1.0000
18.000 1.5732 0.07722 0.07235 -0.0524 0.0012 1.0000
18.250 1.5686 0.08140 0.07663 -0.0532 0.0010 1.0000
18.500 1.5658 0.08539 0.08072 -0.0541 0.0010 1.0000
18.750 1.5621 0.08961 0.08505 -0.0552 0.0010 1.0000
19.000 1.5576 0.09406 0.08961 -0.0566 0.0009 1.0000
19.250 1.5520 0.09877 0.09444 -0.0582 0.0009 1.0000
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Polar data table (+)
Polar graphs
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