EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 639 AIRFOIL (e639-il) Reynolds number: 50,000 Max Cl/Cd: 25.54 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e639-il-50000-n5.txt Download as CSV file: xf-e639-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 639 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2762 0.10175 0.09589 -0.0325 1.0000 0.1114
-8.250 -0.2969 0.10066 0.09502 -0.0349 1.0000 0.1125
-8.000 -0.3163 0.09943 0.09399 -0.0359 1.0000 0.1129
-7.750 -0.2783 0.09302 0.08762 -0.0319 1.0000 0.1172
-7.500 -0.2841 0.09102 0.08581 -0.0307 1.0000 0.1198
-7.250 -0.2838 0.08781 0.08262 -0.0417 0.9471 0.1279
-7.000 -0.2514 0.08230 0.07713 -0.0430 0.9244 0.1340
-6.750 -0.2358 0.07796 0.07265 -0.0515 0.8938 0.1461
-6.500 -0.2180 0.07427 0.06879 -0.0567 0.8686 0.1610
-6.250 -0.1964 0.07066 0.06507 -0.0580 0.8454 0.1741
-6.000 -0.1774 0.06685 0.06118 -0.0583 0.8246 0.1833
-5.750 -0.1669 0.06403 0.05823 -0.0588 0.8043 0.1983
-5.500 -0.1376 0.05577 0.04864 -0.0669 0.7905 0.0672
-5.250 -0.1217 0.05256 0.04535 -0.0664 0.7738 0.0647
-5.000 -0.1060 0.04971 0.04222 -0.0658 0.7586 0.0620
-4.750 -0.0892 0.04692 0.03902 -0.0650 0.7451 0.0593
-4.500 -0.0714 0.04428 0.03588 -0.0639 0.7317 0.0570
-4.250 -0.0527 0.04219 0.03341 -0.0628 0.7186 0.0573
-4.000 -0.0329 0.04030 0.03119 -0.0618 0.7062 0.0582
-3.750 -0.0116 0.03843 0.02892 -0.0606 0.6951 0.0586
-3.500 0.0112 0.03662 0.02666 -0.0595 0.6846 0.0580
-3.250 0.0344 0.03497 0.02459 -0.0584 0.6734 0.0575
-3.000 0.0591 0.03347 0.02267 -0.0574 0.6633 0.0573
-2.750 0.0852 0.03210 0.02093 -0.0565 0.6541 0.0575
-2.500 0.1113 0.03095 0.01949 -0.0559 0.6440 0.0581
-2.250 0.1393 0.02994 0.01822 -0.0554 0.6355 0.0606
-2.000 0.1675 0.02911 0.01714 -0.0551 0.6260 0.0640
-1.750 0.1986 0.02832 0.01608 -0.0550 0.6176 0.0666
-1.500 0.2309 0.02754 0.01508 -0.0552 0.6093 0.0688
-1.250 0.2584 0.02691 0.01435 -0.0549 0.6013 0.0723
-1.000 0.2836 0.02649 0.01376 -0.0541 0.5939 0.0785
-0.750 0.3073 0.02615 0.01333 -0.0533 0.5867 0.0882
-0.500 0.4288 0.02237 0.01211 -0.0697 0.5768 1.0000
-0.250 0.4497 0.02271 0.01212 -0.0685 0.5693 1.0000
0.000 0.4716 0.02299 0.01207 -0.0674 0.5631 1.0000
0.250 0.4928 0.02334 0.01218 -0.0663 0.5569 1.0000
0.500 0.5134 0.02372 0.01237 -0.0652 0.5503 1.0000
0.750 0.5361 0.02400 0.01237 -0.0642 0.5454 1.0000
1.000 0.5551 0.02453 0.01281 -0.0630 0.5386 1.0000
1.250 0.5763 0.02492 0.01303 -0.0620 0.5332 1.0000
1.500 0.5985 0.02529 0.01321 -0.0610 0.5286 1.0000
1.750 0.6164 0.02592 0.01381 -0.0597 0.5221 1.0000
2.000 0.6378 0.02634 0.01409 -0.0586 0.5173 1.0000
2.250 0.6590 0.02680 0.01443 -0.0576 0.5128 1.0000
2.500 0.6759 0.02755 0.01518 -0.0563 0.5067 1.0000
2.750 0.6970 0.02803 0.01556 -0.0552 0.5022 1.0000
3.000 0.7191 0.02848 0.01589 -0.0543 0.4983 1.0000
3.250 0.7330 0.02945 0.01693 -0.0527 0.4922 1.0000
3.500 0.7530 0.03003 0.01747 -0.0516 0.4878 1.0000
3.750 0.7766 0.03041 0.01774 -0.0508 0.4844 1.0000
4.000 0.7871 0.03165 0.01908 -0.0490 0.4785 1.0000
4.250 0.8044 0.03243 0.01986 -0.0477 0.4737 1.0000
4.500 0.8273 0.03288 0.02027 -0.0469 0.4702 1.0000
4.750 0.8385 0.03412 0.02159 -0.0451 0.4651 1.0000
5.000 0.8501 0.03534 0.02287 -0.0435 0.4599 1.0000
5.250 0.8709 0.03595 0.02346 -0.0426 0.4562 1.0000
5.500 0.8901 0.03672 0.02425 -0.0415 0.4525 1.0000
5.750 0.8874 0.03892 0.02661 -0.0390 0.4459 1.0000
6.000 0.9045 0.03982 0.02755 -0.0378 0.4420 1.0000
6.250 0.9305 0.04015 0.02786 -0.0374 0.4391 1.0000
6.500 0.9073 0.04380 0.03170 -0.0337 0.4310 1.0000
6.750 0.9224 0.04487 0.03283 -0.0325 0.4269 1.0000
7.000 0.9492 0.04514 0.03312 -0.0321 0.4242 1.0000
7.250 0.8932 0.05120 0.03931 -0.0273 0.4137 1.0000
7.500 0.9159 0.05171 0.03986 -0.0266 0.4106 1.0000
7.750 0.9468 0.05170 0.03988 -0.0263 0.4083 1.0000
8.000 0.8762 0.06033 0.04856 -0.0241 0.3954 1.0000
8.250 0.9035 0.06023 0.04850 -0.0231 0.3933 1.0000
8.750 0.8810 0.06855 0.05692 -0.0231 0.3784 1.0000
9.000 0.8465 0.07525 0.06366 -0.0238 0.3674 1.0000
9.250 0.8704 0.07563 0.06411 -0.0230 0.3647 1.0000
9.500 0.8426 0.08170 0.07021 -0.0239 0.3546 1.0000
9.750 0.8628 0.08248 0.07110 -0.0232 0.3510 1.0000
10.000 0.8474 0.08728 0.07594 -0.0239 0.3427 1.0000
10.250 0.8596 0.08894 0.07768 -0.0236 0.3377 1.0000
10.500 0.8854 0.08905 0.07789 -0.0227 0.3348 1.0000
10.750 0.8608 0.09502 0.08390 -0.0240 0.3247 1.0000
11.000 0.8828 0.09554 0.08452 -0.0232 0.3212 1.0000
11.250 0.8660 0.10069 0.08973 -0.0244 0.3120 1.0000
11.500 0.8837 0.10171 0.09088 -0.0239 0.3076 1.0000
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Polar data table (+)
Polar graphs
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