E64 (8.45%) (e64-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E64 (8.45%) (e64-il) Reynolds number: 100,000 Max Cl/Cd: 62.31 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e64-il-100000-n5.txt Download as CSV file: xf-e64-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E64 (8.45%)
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 -0.3140 0.08517 0.08059 -0.0355 1.0000 0.0324
-8.250 -0.3162 0.08200 0.07748 -0.0346 1.0000 0.0315
-8.000 -0.3924 0.09073 0.08587 -0.0341 1.0000 0.0309
-7.750 -0.3988 0.08783 0.08305 -0.0333 1.0000 0.0291
-7.500 -0.4225 0.08330 0.07865 -0.0343 1.0000 0.0252
-7.250 -0.4260 0.08081 0.07624 -0.0332 1.0000 0.0248
-7.000 -0.4311 0.07755 0.07304 -0.0338 1.0000 0.0246
-6.750 -0.4346 0.07395 0.06950 -0.0351 1.0000 0.0243
-6.500 -0.4356 0.07000 0.06557 -0.0372 1.0000 0.0240
-6.250 -0.4335 0.06556 0.06112 -0.0399 1.0000 0.0236
-6.000 -0.4279 0.06042 0.05591 -0.0433 1.0000 0.0233
-5.750 -0.4031 0.05291 0.04814 -0.0516 0.9967 0.0234
-5.500 -0.3707 0.04543 0.04020 -0.0598 0.9923 0.0233
-5.250 -0.3368 0.03921 0.03340 -0.0659 0.9883 0.0229
-5.000 -0.3005 0.03392 0.02742 -0.0707 0.9854 0.0223
-4.750 -0.2666 0.03005 0.02288 -0.0735 0.9819 0.0221
-4.500 -0.2323 0.02709 0.01931 -0.0756 0.9785 0.0221
-4.250 -0.1971 0.02486 0.01657 -0.0774 0.9755 0.0225
-4.000 -0.1612 0.02309 0.01444 -0.0791 0.9730 0.0232
-3.750 -0.1304 0.02174 0.01284 -0.0798 0.9684 0.0243
-3.500 -0.0972 0.02066 0.01164 -0.0812 0.9643 0.0272
-3.250 -0.0615 0.01980 0.01065 -0.0830 0.9609 0.0309
-3.000 -0.0298 0.01897 0.00966 -0.0838 0.9557 0.0343
-2.750 0.0044 0.01817 0.00875 -0.0852 0.9510 0.0433
-2.500 0.0410 0.01707 0.00807 -0.0874 0.9477 0.1227
-2.250 0.0709 0.01613 0.00792 -0.0887 0.9422 0.2992
-2.000 0.1031 0.01563 0.00778 -0.0898 0.9368 0.4205
-1.750 0.1384 0.01523 0.00765 -0.0913 0.9330 0.5333
-1.500 0.1639 0.01495 0.00758 -0.0905 0.9252 0.6278
-1.250 0.1941 0.01463 0.00748 -0.0903 0.9203 0.7280
-1.000 0.2154 0.01437 0.00738 -0.0881 0.9123 0.8235
-0.750 0.2538 0.01399 0.00703 -0.0896 0.9070 1.0000
-0.500 0.2868 0.01399 0.00683 -0.0907 0.8998 1.0000
-0.250 0.3228 0.01395 0.00664 -0.0923 0.8934 1.0000
0.000 0.3567 0.01394 0.00650 -0.0935 0.8863 1.0000
0.250 0.3912 0.01390 0.00635 -0.0947 0.8790 1.0000
0.500 0.4230 0.01389 0.00625 -0.0954 0.8705 1.0000
0.750 0.4586 0.01380 0.00610 -0.0967 0.8634 1.0000
1.000 0.4884 0.01380 0.00606 -0.0970 0.8530 1.0000
1.250 0.5216 0.01375 0.00596 -0.0978 0.8440 1.0000
1.500 0.5553 0.01366 0.00585 -0.0987 0.8344 1.0000
1.750 0.5850 0.01366 0.00585 -0.0988 0.8222 1.0000
2.000 0.6155 0.01364 0.00583 -0.0990 0.8095 1.0000
2.250 0.6462 0.01361 0.00580 -0.0993 0.7959 1.0000
2.500 0.6769 0.01359 0.00579 -0.0995 0.7810 1.0000
2.750 0.7074 0.01358 0.00581 -0.0996 0.7649 1.0000
3.000 0.7381 0.01358 0.00581 -0.0998 0.7476 1.0000
3.250 0.7656 0.01365 0.00591 -0.0994 0.7269 1.0000
3.500 0.7945 0.01372 0.00600 -0.0992 0.7053 1.0000
3.750 0.8214 0.01384 0.00613 -0.0986 0.6805 1.0000
4.000 0.8481 0.01401 0.00628 -0.0981 0.6540 1.0000
4.250 0.8740 0.01421 0.00646 -0.0973 0.6248 1.0000
4.500 0.8990 0.01448 0.00671 -0.0965 0.5923 1.0000
4.750 0.9228 0.01481 0.00697 -0.0954 0.5565 1.0000
5.000 0.9456 0.01521 0.00728 -0.0942 0.5175 1.0000
5.250 0.9673 0.01569 0.00765 -0.0929 0.4756 1.0000
5.500 0.9879 0.01625 0.00812 -0.0915 0.4319 1.0000
5.750 1.0076 0.01690 0.00863 -0.0900 0.3867 1.0000
6.000 1.0264 0.01762 0.00920 -0.0884 0.3391 1.0000
6.250 1.0437 0.01849 0.00985 -0.0867 0.2877 1.0000
6.500 1.0599 0.01950 0.01058 -0.0850 0.2320 1.0000
6.750 1.0757 0.02062 0.01143 -0.0834 0.1770 1.0000
7.000 1.0920 0.02176 0.01232 -0.0819 0.1319 1.0000
7.250 1.1080 0.02299 0.01331 -0.0804 0.0896 1.0000
7.500 1.1227 0.02439 0.01449 -0.0787 0.0568 1.0000
7.750 1.1371 0.02583 0.01588 -0.0768 0.0391 1.0000
8.000 1.1508 0.02728 0.01739 -0.0747 0.0326 1.0000
8.250 1.1645 0.02865 0.01894 -0.0726 0.0291 1.0000
8.500 1.1752 0.03024 0.02064 -0.0703 0.0269 1.0000
8.750 1.1859 0.03180 0.02237 -0.0679 0.0256 1.0000
9.000 1.1966 0.03335 0.02411 -0.0655 0.0245 1.0000
9.250 1.2079 0.03494 0.02587 -0.0634 0.0232 1.0000
9.500 1.2188 0.03652 0.02759 -0.0614 0.0218 1.0000
9.750 1.2283 0.03823 0.02939 -0.0594 0.0207 1.0000
10.000 1.2369 0.04047 0.03171 -0.0575 0.0198 1.0000
10.250 1.2492 0.04265 0.03417 -0.0558 0.0194 1.0000
10.500 1.2603 0.04507 0.03687 -0.0541 0.0191 1.0000
10.750 1.2688 0.04772 0.03983 -0.0523 0.0187 1.0000
11.000 1.2737 0.05062 0.04305 -0.0503 0.0185 1.0000
11.250 1.2743 0.05372 0.04649 -0.0482 0.0183 1.0000
11.500 1.2708 0.05706 0.05016 -0.0462 0.0182 1.0000
11.750 1.2635 0.06069 0.05412 -0.0445 0.0181 1.0000
12.000 1.2528 0.06467 0.05842 -0.0432 0.0180 1.0000
12.250 1.2395 0.06906 0.06311 -0.0425 0.0180 1.0000
12.500 1.2238 0.07395 0.06829 -0.0427 0.0180 1.0000
12.750 1.2061 0.07944 0.07405 -0.0439 0.0181 1.0000
13.000 1.1869 0.08559 0.08045 -0.0461 0.0181 1.0000
13.250 1.1665 0.09254 0.08762 -0.0495 0.0182 1.0000
13.500 1.1451 0.10042 0.09571 -0.0542 0.0183 1.0000
13.750 1.1229 0.10938 0.10485 -0.0600 0.0185 1.0000
14.000 1.0999 0.11969 0.11531 -0.0671 0.0187 1.0000
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Polar data table (+)
Polar graphs
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