EPPLER 793 AIRFOIL (e793-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 793 AIRFOIL (e793-il) Reynolds number: 100,000 Max Cl/Cd: 52.37 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e793-il-100000-n5.txt Download as CSV file: xf-e793-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3840 0.09663 0.09133 -0.0530 1.0000 0.0356
-11.250 -0.4674 0.07601 0.07064 -0.0645 1.0000 0.0343
-11.000 -0.5386 0.06266 0.05705 -0.0735 1.0000 0.0333
-10.750 -0.5783 0.05644 0.05066 -0.0765 1.0000 0.0330
-10.500 -0.6109 0.05274 0.04686 -0.0763 1.0000 0.0328
-10.250 -0.6437 0.05016 0.04422 -0.0742 1.0000 0.0327
-10.000 -0.6624 0.04778 0.04171 -0.0724 1.0000 0.0328
-9.750 -0.6544 0.04468 0.03836 -0.0748 0.9953 0.0331
-9.500 -0.6304 0.04148 0.03486 -0.0790 0.9871 0.0336
-9.250 -0.6046 0.03874 0.03182 -0.0823 0.9792 0.0343
-9.000 -0.5763 0.03635 0.02915 -0.0852 0.9716 0.0353
-8.750 -0.5503 0.03426 0.02669 -0.0871 0.9622 0.0367
-8.500 -0.5213 0.03259 0.02495 -0.0890 0.9543 0.0379
-8.250 -0.4908 0.03112 0.02343 -0.0908 0.9463 0.0393
-8.000 -0.4624 0.02971 0.02189 -0.0920 0.9372 0.0407
-7.750 -0.4288 0.02827 0.02030 -0.0939 0.9306 0.0423
-7.500 -0.4008 0.02704 0.01896 -0.0947 0.9208 0.0439
-7.250 -0.3658 0.02579 0.01771 -0.0970 0.9146 0.0465
-7.000 -0.3369 0.02479 0.01658 -0.0978 0.9042 0.0500
-6.750 -0.3000 0.02359 0.01535 -0.1004 0.8978 0.0548
-6.500 -0.2712 0.02257 0.01426 -0.1012 0.8865 0.0606
-6.250 -0.2366 0.02145 0.01308 -0.1032 0.8782 0.0707
-6.000 -0.2049 0.02039 0.01207 -0.1046 0.8676 0.0901
-5.750 -0.1729 0.01946 0.01121 -0.1060 0.8569 0.1191
-5.500 -0.1371 0.01862 0.01047 -0.1080 0.8477 0.1574
-5.250 -0.1071 0.01806 0.01007 -0.1088 0.8352 0.2030
-5.000 -0.0746 0.01771 0.00977 -0.1099 0.8236 0.2460
-4.750 -0.0398 0.01747 0.00942 -0.1111 0.8130 0.2756
-4.500 -0.0104 0.01732 0.00922 -0.1113 0.7998 0.2970
-4.250 0.0199 0.01720 0.00901 -0.1116 0.7871 0.3174
-4.000 0.0509 0.01709 0.00879 -0.1120 0.7751 0.3364
-3.750 0.0815 0.01699 0.00858 -0.1122 0.7631 0.3536
-3.500 0.1098 0.01692 0.00841 -0.1121 0.7499 0.3689
-3.250 0.1387 0.01685 0.00824 -0.1121 0.7375 0.3834
-3.000 0.1683 0.01678 0.00804 -0.1122 0.7260 0.3977
-2.750 0.1963 0.01673 0.00787 -0.1120 0.7136 0.4112
-2.500 0.2237 0.01668 0.00778 -0.1117 0.7013 0.4233
-2.250 0.2520 0.01664 0.00765 -0.1116 0.6903 0.4357
-2.000 0.2800 0.01662 0.00751 -0.1114 0.6788 0.4487
-1.750 0.3068 0.01661 0.00746 -0.1110 0.6671 0.4607
-1.500 0.3346 0.01660 0.00737 -0.1108 0.6568 0.4727
-1.250 0.3618 0.01661 0.00730 -0.1105 0.6459 0.4857
-1.000 0.3887 0.01663 0.00727 -0.1102 0.6352 0.4988
-0.500 0.4424 0.01669 0.00725 -0.1094 0.6152 0.5246
-0.250 0.4695 0.01674 0.00724 -0.1091 0.6061 0.5389
0.000 0.4960 0.01680 0.00727 -0.1087 0.5963 0.5539
0.250 0.5225 0.01687 0.00731 -0.1083 0.5874 0.5688
0.500 0.5487 0.01694 0.00737 -0.1078 0.5784 0.5843
0.750 0.5748 0.01702 0.00746 -0.1073 0.5697 0.6004
1.000 0.6008 0.01711 0.00753 -0.1068 0.5613 0.6176
1.250 0.6267 0.01722 0.00764 -0.1063 0.5529 0.6357
1.500 0.6526 0.01732 0.00774 -0.1058 0.5448 0.6549
1.750 0.6782 0.01744 0.00788 -0.1052 0.5370 0.6754
2.000 0.7030 0.01755 0.00802 -0.1045 0.5291 0.6966
2.250 0.7280 0.01767 0.00815 -0.1037 0.5220 0.7201
2.500 0.7516 0.01778 0.00834 -0.1027 0.5141 0.7460
2.750 0.7757 0.01788 0.00843 -0.1017 0.5079 0.7749
3.000 0.7966 0.01798 0.00866 -0.1002 0.5001 0.8087
3.250 0.8176 0.01801 0.00876 -0.0984 0.4937 0.8522
3.500 0.8433 0.01804 0.00887 -0.0978 0.4868 0.9298
3.750 0.8732 0.01826 0.00905 -0.0984 0.4794 1.0000
4.000 0.9012 0.01855 0.00923 -0.0986 0.4734 1.0000
4.250 0.9268 0.01888 0.00956 -0.0984 0.4660 1.0000
4.500 0.9538 0.01918 0.00978 -0.0984 0.4599 1.0000
4.750 0.9793 0.01952 0.01012 -0.0982 0.4533 1.0000
5.000 1.0047 0.01986 0.01044 -0.0979 0.4467 1.0000
5.500 1.0552 0.02058 0.01115 -0.0973 0.4344 1.0000
5.750 1.0803 0.02093 0.01148 -0.0970 0.4284 1.0000
6.000 1.1057 0.02131 0.01183 -0.0967 0.4229 1.0000
6.250 1.1286 0.02173 0.01233 -0.0960 0.4163 1.0000
6.500 1.1535 0.02210 0.01268 -0.0956 0.4108 1.0000
6.750 1.1770 0.02253 0.01314 -0.0951 0.4050 1.0000
7.000 1.1992 0.02298 0.01366 -0.0943 0.3987 1.0000
7.250 1.2238 0.02337 0.01403 -0.0939 0.3935 1.0000
7.500 1.2451 0.02386 0.01460 -0.0930 0.3876 1.0000
7.750 1.2664 0.02433 0.01513 -0.0922 0.3813 1.0000
8.000 1.2906 0.02473 0.01551 -0.0917 0.3763 1.0000
8.250 1.3085 0.02530 0.01622 -0.0903 0.3697 1.0000
8.500 1.3288 0.02576 0.01673 -0.0893 0.3636 1.0000
8.750 1.3502 0.02622 0.01721 -0.0885 0.3581 1.0000
9.000 1.3658 0.02683 0.01796 -0.0868 0.3513 1.0000
9.250 1.3855 0.02728 0.01843 -0.0857 0.3455 1.0000
9.500 1.4008 0.02790 0.01916 -0.0840 0.3393 1.0000
9.750 1.4149 0.02849 0.01985 -0.0822 0.3328 1.0000
10.000 1.4328 0.02895 0.02029 -0.0808 0.3273 1.0000
10.250 1.4395 0.02976 0.02128 -0.0780 0.3205 1.0000
10.500 1.4524 0.03036 0.02193 -0.0761 0.3143 1.0000
10.750 1.4620 0.03116 0.02283 -0.0738 0.3081 1.0000
11.000 1.4691 0.03204 0.02383 -0.0714 0.3014 1.0000
11.250 1.4813 0.03276 0.02455 -0.0697 0.2955 1.0000
11.500 1.4831 0.03401 0.02600 -0.0671 0.2885 1.0000
11.750 1.4915 0.03496 0.02698 -0.0652 0.2823 1.0000
12.000 1.4935 0.03638 0.02856 -0.0631 0.2756 1.0000
12.250 1.4965 0.03778 0.03006 -0.0612 0.2689 1.0000
12.500 1.4997 0.03929 0.03165 -0.0595 0.2625 1.0000
12.750 1.4977 0.04126 0.03377 -0.0578 0.2553 1.0000
13.000 1.5009 0.04292 0.03545 -0.0565 0.2489 1.0000
13.250 1.4948 0.04554 0.03826 -0.0552 0.2416 1.0000
13.500 1.4970 0.04745 0.04017 -0.0542 0.2350 1.0000
13.750 1.4872 0.05079 0.04372 -0.0535 0.2277 1.0000
14.000 1.4862 0.05322 0.04617 -0.0529 0.2209 1.0000
14.250 1.4745 0.05715 0.05028 -0.0528 0.2136 1.0000
14.500 1.4708 0.06016 0.05332 -0.0527 0.2067 1.0000
14.750 1.4577 0.06465 0.05798 -0.0532 0.1995 1.0000
15.000 1.4523 0.06818 0.06153 -0.0535 0.1926 1.0000
15.250 1.4387 0.07315 0.06665 -0.0545 0.1855 1.0000
15.500 1.4324 0.07708 0.07061 -0.0553 0.1787 1.0000
15.750 1.4192 0.08232 0.07599 -0.0567 0.1719 1.0000
16.000 1.4120 0.08666 0.08036 -0.0578 0.1653 1.0000
16.250 1.4013 0.09175 0.08555 -0.0594 0.1589 1.0000
16.500 1.3930 0.09653 0.09040 -0.0610 0.1526 1.0000
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