EPPLER 339 AIRFOIL (e339-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 339 AIRFOIL (e339-il) Reynolds number: 50,000 Max Cl/Cd: 26.09 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e339-il-50000-n5.txt Download as CSV file: xf-e339-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 339 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2839 0.10268 0.09651 -0.0336 1.0000 0.1109
-8.500 -0.3059 0.10102 0.09504 -0.0368 1.0000 0.1148
-8.250 -0.3356 0.09965 0.09386 -0.0385 1.0000 0.1156
-8.000 -0.3260 0.09514 0.08949 -0.0373 1.0000 0.1172
-7.750 -0.3113 0.09158 0.08602 -0.0353 1.0000 0.1198
-7.500 -0.3194 0.08931 0.08392 -0.0337 1.0000 0.1217
-7.250 -0.3330 0.08750 0.08229 -0.0321 0.9971 0.1234
-7.000 -0.3378 0.08369 0.07835 -0.0423 0.9511 0.1332
-6.500 -0.2793 0.06886 0.06303 -0.0523 0.9124 0.0608
-6.250 -0.2585 0.06370 0.05757 -0.0558 0.8924 0.0520
-6.000 -0.2397 0.05889 0.05232 -0.0581 0.8730 0.0467
-5.750 -0.2181 0.05527 0.04843 -0.0594 0.8543 0.0455
-5.500 -0.1988 0.05194 0.04473 -0.0599 0.8359 0.0446
-5.250 -0.1802 0.04904 0.04144 -0.0596 0.8181 0.0445
-5.000 -0.1622 0.04639 0.03839 -0.0587 0.8012 0.0445
-4.750 -0.1438 0.04397 0.03554 -0.0575 0.7851 0.0449
-4.500 -0.1244 0.04172 0.03286 -0.0562 0.7701 0.0448
-4.250 -0.1033 0.03951 0.03018 -0.0549 0.7565 0.0447
-4.000 -0.0817 0.03752 0.02775 -0.0535 0.7427 0.0444
-3.750 -0.0591 0.03572 0.02554 -0.0522 0.7292 0.0443
-3.500 -0.0338 0.03397 0.02334 -0.0510 0.7170 0.0447
-3.250 -0.0064 0.03239 0.02132 -0.0502 0.7056 0.0459
-3.000 0.0204 0.03109 0.01970 -0.0494 0.6931 0.0486
-2.750 0.0497 0.02997 0.01838 -0.0492 0.6824 0.0521
-2.500 0.0848 0.02878 0.01685 -0.0494 0.6715 0.0553
-2.250 0.1190 0.02785 0.01581 -0.0500 0.6605 0.0620
-2.000 0.1506 0.02698 0.01477 -0.0501 0.6514 0.0707
-1.500 0.3703 0.02273 0.01272 -0.0755 0.6264 1.0000
-1.250 0.3925 0.02284 0.01249 -0.0747 0.6177 1.0000
-1.000 0.4143 0.02300 0.01237 -0.0738 0.6092 1.0000
-0.750 0.4362 0.02316 0.01227 -0.0729 0.6009 1.0000
-0.500 0.4580 0.02334 0.01222 -0.0721 0.5935 1.0000
-0.250 0.4791 0.02358 0.01228 -0.0711 0.5855 1.0000
0.000 0.5018 0.02375 0.01220 -0.0702 0.5795 1.0000
0.250 0.5215 0.02409 0.01246 -0.0692 0.5714 1.0000
0.500 0.5430 0.02434 0.01253 -0.0682 0.5650 1.0000
0.750 0.5641 0.02464 0.01268 -0.0672 0.5589 1.0000
1.000 0.5834 0.02505 0.01303 -0.0660 0.5519 1.0000
1.250 0.6049 0.02534 0.01317 -0.0650 0.5465 1.0000
1.500 0.6246 0.02576 0.01351 -0.0639 0.5407 1.0000
1.750 0.6429 0.02624 0.01396 -0.0626 0.5342 1.0000
2.000 0.6640 0.02658 0.01419 -0.0615 0.5292 1.0000
2.250 0.6832 0.02705 0.01460 -0.0602 0.5240 1.0000
2.500 0.6994 0.02768 0.01526 -0.0587 0.5178 1.0000
2.750 0.7192 0.02810 0.01562 -0.0575 0.5129 1.0000
3.000 0.7409 0.02844 0.01586 -0.0564 0.5089 1.0000
3.250 0.7524 0.02935 0.01689 -0.0544 0.5024 1.0000
3.500 0.7695 0.02993 0.01746 -0.0529 0.4974 1.0000
3.750 0.7905 0.03030 0.01776 -0.0517 0.4935 1.0000
4.000 0.8024 0.03120 0.01872 -0.0497 0.4881 1.0000
4.250 0.8137 0.03208 0.01967 -0.0475 0.4825 1.0000
4.500 0.8317 0.03260 0.02021 -0.0460 0.4783 1.0000
4.750 0.8545 0.03291 0.02045 -0.0451 0.4750 1.0000
5.000 0.8517 0.03451 0.02224 -0.0414 0.4683 1.0000
5.250 0.8630 0.03535 0.02312 -0.0392 0.4634 1.0000
5.500 0.8830 0.03576 0.02352 -0.0379 0.4597 1.0000
5.750 0.8865 0.03703 0.02491 -0.0349 0.4547 1.0000
6.000 0.8813 0.03866 0.02666 -0.0310 0.4487 1.0000
6.250 0.8960 0.03929 0.02730 -0.0291 0.4444 1.0000
6.500 0.9212 0.03947 0.02747 -0.0284 0.4414 1.0000
6.750 0.8796 0.04290 0.03108 -0.0211 0.4332 1.0000
7.000 0.8869 0.04392 0.03213 -0.0187 0.4285 1.0000
7.250 0.9143 0.04396 0.03218 -0.0182 0.4254 1.0000
7.500 0.8353 0.04979 0.03808 -0.0092 0.4146 1.0000
7.750 0.8546 0.05029 0.03861 -0.0081 0.4108 1.0000
8.000 0.8905 0.04981 0.03821 -0.0081 0.4083 1.0000
8.500 0.7779 0.06423 0.05265 -0.0042 0.3832 1.0000
8.750 0.7917 0.06543 0.05393 -0.0034 0.3784 1.0000
9.000 0.8185 0.06528 0.05384 -0.0025 0.3759 1.0000
9.500 0.8056 0.07217 0.06082 -0.0021 0.3604 1.0000
10.000 0.7981 0.07866 0.06742 -0.0021 0.3456 1.0000
10.500 0.7953 0.08484 0.07373 -0.0023 0.3314 1.0000
10.750 0.8211 0.08477 0.07376 -0.0014 0.3282 1.0000
11.000 0.7968 0.09063 0.07966 -0.0026 0.3174 1.0000
11.250 0.8185 0.09108 0.08020 -0.0019 0.3137 1.0000
11.500 0.8015 0.09620 0.08537 -0.0030 0.3039 1.0000
11.750 0.8196 0.09706 0.08636 -0.0026 0.2994 1.0000
12.000 0.8088 0.10161 0.09096 -0.0036 0.2909 1.0000
12.250 0.8228 0.10294 0.09240 -0.0034 0.2854 1.0000
12.750 0.8260 0.10899 0.09862 -0.0045 0.2717 1.0000
13.000 0.8523 0.10857 0.09833 -0.0035 0.2683 1.0000
13.250 0.8309 0.11493 0.10475 -0.0057 0.2581 1.0000
13.500 0.8544 0.11485 0.10480 -0.0049 0.2545 1.0000
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Polar data table (+)
Polar graphs
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