EPPLER 793 AIRFOIL (e793-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 793 AIRFOIL (e793-il) Reynolds number: 50,000 Max Cl/Cd: 30.44 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e793-il-50000-n5.txt Download as CSV file: xf-e793-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 793 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3438 0.10306 0.09578 -0.0512 1.0000 0.0606
-10.500 -0.3770 0.09245 0.08525 -0.0564 1.0000 0.0594
-10.250 -0.3956 0.08595 0.07883 -0.0588 1.0000 0.0592
-10.000 -0.4207 0.07913 0.07208 -0.0616 1.0000 0.0589
-9.750 -0.4497 0.07289 0.06589 -0.0639 1.0000 0.0585
-9.500 -0.4831 0.06765 0.06067 -0.0653 1.0000 0.0580
-9.250 -0.5193 0.06390 0.05696 -0.0647 1.0000 0.0575
-9.000 -0.5500 0.06028 0.05331 -0.0644 1.0000 0.0572
-8.750 -0.5736 0.05686 0.04976 -0.0636 1.0000 0.0572
-8.500 -0.5886 0.05373 0.04643 -0.0627 1.0000 0.0574
-8.250 -0.5973 0.05067 0.04309 -0.0620 1.0000 0.0580
-8.000 -0.5784 0.04671 0.03861 -0.0659 0.9929 0.0598
-7.750 -0.5467 0.04461 0.03645 -0.0692 0.9842 0.0625
-7.500 -0.5166 0.04211 0.03362 -0.0723 0.9746 0.0656
-7.250 -0.4857 0.03961 0.03069 -0.0748 0.9651 0.0685
-7.000 -0.4530 0.03781 0.02883 -0.0771 0.9563 0.0718
-6.750 -0.4212 0.03620 0.02704 -0.0792 0.9462 0.0777
-6.500 -0.3915 0.03467 0.02545 -0.0808 0.9355 0.0844
-6.250 -0.3580 0.03311 0.02376 -0.0829 0.9262 0.0941
-6.000 -0.3255 0.03161 0.02229 -0.0850 0.9161 0.1093
-5.750 -0.2949 0.03023 0.02090 -0.0868 0.9051 0.1336
-5.500 -0.2556 0.02893 0.01986 -0.0903 0.8974 0.1743
-5.250 -0.2260 0.02828 0.01938 -0.0916 0.8853 0.2171
-5.000 -0.1911 0.02788 0.01894 -0.0933 0.8751 0.2597
-4.750 -0.1531 0.02768 0.01870 -0.0951 0.8663 0.2952
-4.500 -0.1216 0.02756 0.01849 -0.0957 0.8549 0.3243
-4.250 -0.0816 0.02738 0.01823 -0.0974 0.8474 0.3513
-4.000 -0.0535 0.02726 0.01800 -0.0973 0.8349 0.3730
-3.750 -0.0205 0.02702 0.01757 -0.0980 0.8245 0.3950
-3.500 0.0143 0.02677 0.01722 -0.0988 0.8151 0.4141
-3.250 0.0427 0.02662 0.01696 -0.0986 0.8032 0.4312
-3.000 0.0777 0.02634 0.01654 -0.0994 0.7942 0.4489
-2.750 0.1070 0.02616 0.01623 -0.0995 0.7826 0.4652
-2.500 0.1352 0.02603 0.01604 -0.0992 0.7712 0.4796
-2.250 0.1701 0.02575 0.01563 -0.0999 0.7626 0.4955
-2.000 0.1953 0.02569 0.01550 -0.0992 0.7500 0.5095
-1.750 0.2246 0.02556 0.01526 -0.0992 0.7394 0.5247
-1.500 0.2563 0.02538 0.01496 -0.0995 0.7297 0.5404
-1.250 0.2820 0.02537 0.01487 -0.0990 0.7178 0.5557
-1.000 0.3131 0.02524 0.01463 -0.0992 0.7085 0.5721
-0.750 0.3398 0.02523 0.01455 -0.0988 0.6976 0.5883
-0.500 0.3656 0.02525 0.01452 -0.0982 0.6870 0.6043
-0.250 0.3959 0.02515 0.01434 -0.0981 0.6781 0.6221
0.000 0.4187 0.02528 0.01447 -0.0972 0.6670 0.6392
0.250 0.4482 0.02520 0.01432 -0.0970 0.6587 0.6585
0.500 0.4702 0.02534 0.01449 -0.0958 0.6480 0.6772
0.750 0.4956 0.02537 0.01451 -0.0950 0.6393 0.6979
1.000 0.5192 0.02545 0.01460 -0.0940 0.6298 0.7204
1.250 0.5420 0.02555 0.01472 -0.0928 0.6208 0.7450
1.500 0.5645 0.02558 0.01478 -0.0914 0.6124 0.7720
1.750 0.5842 0.02569 0.01495 -0.0896 0.6038 0.8028
2.000 0.6058 0.02568 0.01499 -0.0880 0.5955 0.8414
2.250 0.6306 0.02574 0.01512 -0.0872 0.5871 0.8970
2.500 0.6702 0.02583 0.01514 -0.0897 0.5784 1.0000
2.750 0.6978 0.02630 0.01549 -0.0905 0.5697 1.0000
3.000 0.7272 0.02667 0.01572 -0.0912 0.5617 1.0000
3.250 0.7534 0.02718 0.01614 -0.0914 0.5538 1.0000
3.500 0.7796 0.02766 0.01653 -0.0915 0.5458 1.0000
3.750 0.8071 0.02810 0.01688 -0.0917 0.5386 1.0000
4.000 0.8292 0.02875 0.01751 -0.0912 0.5303 1.0000
4.250 0.8621 0.02896 0.01758 -0.0919 0.5246 1.0000
4.500 0.8768 0.02994 0.01864 -0.0906 0.5154 1.0000
4.750 0.9073 0.03023 0.01884 -0.0909 0.5094 1.0000
5.000 0.9235 0.03120 0.01986 -0.0898 0.5013 1.0000
5.250 0.9491 0.03171 0.02036 -0.0896 0.4947 1.0000
5.500 0.9720 0.03237 0.02102 -0.0891 0.4881 1.0000
5.750 0.9889 0.03331 0.02201 -0.0880 0.4805 1.0000
6.000 1.0210 0.03354 0.02220 -0.0884 0.4753 1.0000
6.250 1.0279 0.03498 0.02377 -0.0863 0.4670 1.0000
6.500 1.0533 0.03551 0.02430 -0.0860 0.4610 1.0000
6.750 1.0718 0.03643 0.02527 -0.0851 0.4547 1.0000
7.000 1.0820 0.03772 0.02668 -0.0833 0.4473 1.0000
7.250 1.1150 0.03787 0.02680 -0.0838 0.4424 1.0000
7.500 1.1103 0.03998 0.02908 -0.0807 0.4343 1.0000
7.750 1.1312 0.04073 0.02987 -0.0799 0.4284 1.0000
8.000 1.1546 0.04137 0.03056 -0.0795 0.4231 1.0000
8.250 1.1371 0.04406 0.03342 -0.0753 0.4148 1.0000
8.500 1.1714 0.04408 0.03346 -0.0757 0.4101 1.0000
8.750 1.1373 0.04806 0.03760 -0.0709 0.4016 1.0000
9.000 1.1532 0.04908 0.03868 -0.0699 0.3956 1.0000
9.250 1.2062 0.04774 0.03736 -0.0712 0.3921 1.0000
9.500 1.1207 0.05645 0.04626 -0.0660 0.3797 1.0000
9.750 1.1723 0.05437 0.04422 -0.0659 0.3768 1.0000
10.000 1.0930 0.06497 0.05494 -0.0647 0.3626 1.0000
10.250 1.1384 0.06278 0.05282 -0.0637 0.3603 1.0000
10.750 1.1160 0.07138 0.06158 -0.0634 0.3436 1.0000
11.750 1.0267 0.09808 0.08859 -0.0691 0.3005 1.0000
12.000 1.0559 0.09714 0.08776 -0.0678 0.2973 1.0000
12.500 1.0533 0.10475 0.09553 -0.0692 0.2818 1.0000
13.000 1.0515 0.11238 0.10332 -0.0709 0.2666 1.0000
13.250 1.0264 0.12034 0.11133 -0.0739 0.2552 1.0000
13.500 1.0520 0.11970 0.11080 -0.0727 0.2514 1.0000
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Polar data table (+)
Polar graphs
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