E193 (10.22%) (e193-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E193 (10.22%) (e193-il) Reynolds number: 500,000 Max Cl/Cd: 107.16 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e193-il-500000-n5.txt Download as CSV file: xf-e193-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E193 (10.22%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2907 0.07776 0.07565 -0.0402 1.0000 0.0091
-9.250 -0.3744 0.08660 0.08435 -0.0380 1.0000 0.0090
-9.000 -0.3773 0.08274 0.08052 -0.0393 1.0000 0.0089
-8.750 -0.3799 0.07930 0.07712 -0.0403 1.0000 0.0088
-8.500 -0.3821 0.07488 0.07273 -0.0428 0.9932 0.0087
-8.250 -0.3742 0.06799 0.06585 -0.0516 0.9764 0.0085
-8.000 -0.3617 0.05697 0.05478 -0.0689 0.9434 0.0083
-7.750 -0.3917 0.03195 0.02883 -0.0858 0.8895 0.0077
-7.500 -0.3891 0.02598 0.02209 -0.0854 0.8617 0.0078
-7.250 -0.3752 0.02287 0.01843 -0.0844 0.8406 0.0080
-7.000 -0.3569 0.02073 0.01584 -0.0836 0.8221 0.0082
-6.750 -0.3361 0.01913 0.01385 -0.0828 0.8058 0.0084
-6.500 -0.3138 0.01782 0.01220 -0.0821 0.7912 0.0086
-6.250 -0.2904 0.01673 0.01083 -0.0815 0.7776 0.0087
-6.000 -0.2663 0.01585 0.00970 -0.0809 0.7652 0.0089
-5.750 -0.2413 0.01514 0.00879 -0.0804 0.7535 0.0091
-5.500 -0.2159 0.01456 0.00803 -0.0801 0.7424 0.0094
-5.250 -0.1919 0.01354 0.00684 -0.0795 0.7325 0.0098
-5.000 -0.1668 0.01290 0.00608 -0.0791 0.7228 0.0101
-4.750 -0.1411 0.01235 0.00544 -0.0787 0.7138 0.0104
-4.500 -0.1152 0.01190 0.00488 -0.0784 0.7054 0.0107
-4.250 -0.0890 0.01148 0.00437 -0.0781 0.6970 0.0111
-4.000 -0.0626 0.01114 0.00393 -0.0778 0.6896 0.0115
-3.750 -0.0359 0.01082 0.00353 -0.0776 0.6820 0.0121
-3.500 -0.0090 0.01057 0.00319 -0.0773 0.6751 0.0126
-3.250 0.0181 0.01034 0.00287 -0.0772 0.6681 0.0133
-3.000 0.0450 0.01010 0.00256 -0.0769 0.6618 0.0152
-2.750 0.0723 0.00992 0.00233 -0.0768 0.6553 0.0175
-2.500 0.0992 0.00966 0.00210 -0.0766 0.6492 0.0311
-2.250 0.1262 0.00942 0.00194 -0.0765 0.6436 0.0608
-2.000 0.1531 0.00920 0.00182 -0.0764 0.6375 0.0944
-1.500 0.2068 0.00872 0.00164 -0.0762 0.6266 0.2016
-1.250 0.2336 0.00851 0.00158 -0.0762 0.6211 0.2583
-1.000 0.2602 0.00829 0.00154 -0.0760 0.6160 0.3277
-0.750 0.2867 0.00804 0.00152 -0.0759 0.6107 0.4087
-0.500 0.3130 0.00782 0.00151 -0.0757 0.6056 0.4887
-0.250 0.3393 0.00763 0.00151 -0.0754 0.6006 0.5602
0.000 0.3650 0.00741 0.00152 -0.0750 0.5954 0.6442
0.250 0.3890 0.00715 0.00156 -0.0741 0.5906 0.7437
0.500 0.4115 0.00688 0.00161 -0.0727 0.5859 0.8530
0.750 0.4509 0.00680 0.00166 -0.0748 0.5804 0.9501
1.000 0.4912 0.00685 0.00166 -0.0775 0.5753 0.9833
1.250 0.5321 0.00689 0.00166 -0.0804 0.5699 0.9981
1.500 0.5602 0.00696 0.00170 -0.0805 0.5646 1.0000
1.750 0.5857 0.00705 0.00173 -0.0800 0.5597 1.0000
2.000 0.6116 0.00711 0.00179 -0.0796 0.5541 1.0000
2.250 0.6373 0.00719 0.00185 -0.0792 0.5479 1.0000
2.500 0.6631 0.00728 0.00191 -0.0787 0.5416 1.0000
2.750 0.6890 0.00737 0.00197 -0.0783 0.5340 1.0000
3.000 0.7149 0.00747 0.00206 -0.0779 0.5262 1.0000
3.250 0.7406 0.00757 0.00214 -0.0775 0.5174 1.0000
3.500 0.7667 0.00767 0.00223 -0.0772 0.5087 1.0000
3.750 0.7923 0.00780 0.00233 -0.0768 0.4991 1.0000
4.000 0.8180 0.00793 0.00245 -0.0764 0.4880 1.0000
4.250 0.8438 0.00805 0.00257 -0.0760 0.4766 1.0000
4.500 0.8694 0.00820 0.00271 -0.0756 0.4644 1.0000
4.750 0.8947 0.00837 0.00287 -0.0752 0.4499 1.0000
5.000 0.9194 0.00858 0.00303 -0.0746 0.4314 1.0000
5.250 0.9427 0.00889 0.00323 -0.0739 0.4016 1.0000
5.500 0.9630 0.00945 0.00353 -0.0727 0.3467 1.0000
5.750 0.9796 0.01035 0.00404 -0.0711 0.2714 1.0000
6.000 0.9981 0.01111 0.00454 -0.0698 0.2178 1.0000
6.250 1.0179 0.01176 0.00500 -0.0686 0.1782 1.0000
6.500 1.0360 0.01252 0.00553 -0.0673 0.1348 1.0000
7.000 1.0721 0.01399 0.00664 -0.0645 0.0682 1.0000
7.250 1.0905 0.01466 0.00719 -0.0632 0.0463 1.0000
7.500 1.1066 0.01546 0.00786 -0.0615 0.0230 1.0000
7.750 1.1232 0.01620 0.00854 -0.0599 0.0120 1.0000
8.000 1.1417 0.01676 0.00914 -0.0585 0.0102 1.0000
8.250 1.1598 0.01733 0.00975 -0.0571 0.0092 1.0000
8.500 1.1775 0.01788 0.01037 -0.0556 0.0085 1.0000
8.750 1.1939 0.01845 0.01100 -0.0540 0.0080 1.0000
9.000 1.2074 0.01907 0.01169 -0.0518 0.0077 1.0000
9.250 1.2193 0.01977 0.01245 -0.0495 0.0074 1.0000
9.500 1.2300 0.02055 0.01332 -0.0471 0.0071 1.0000
9.750 1.2395 0.02145 0.01429 -0.0447 0.0068 1.0000
10.000 1.2460 0.02257 0.01550 -0.0422 0.0066 1.0000
10.250 1.2529 0.02372 0.01673 -0.0399 0.0065 1.0000
10.500 1.2612 0.02485 0.01795 -0.0380 0.0064 1.0000
10.750 1.2687 0.02609 0.01928 -0.0362 0.0063 1.0000
11.000 1.2748 0.02752 0.02080 -0.0345 0.0062 1.0000
11.250 1.2812 0.02901 0.02240 -0.0330 0.0061 1.0000
11.500 1.2872 0.03062 0.02410 -0.0316 0.0060 1.0000
11.750 1.2909 0.03250 0.02607 -0.0303 0.0059 1.0000
12.000 1.2949 0.03443 0.02810 -0.0292 0.0058 1.0000
12.250 1.2983 0.03651 0.03028 -0.0283 0.0058 1.0000
12.500 1.3015 0.03866 0.03254 -0.0274 0.0057 1.0000
12.750 1.3045 0.04090 0.03488 -0.0268 0.0056 1.0000
13.000 1.3067 0.04328 0.03736 -0.0262 0.0055 1.0000
13.250 1.3090 0.04572 0.03990 -0.0257 0.0053 1.0000
13.500 1.3107 0.04828 0.04258 -0.0254 0.0053 1.0000
13.750 1.3119 0.05094 0.04535 -0.0252 0.0051 1.0000
14.000 1.3126 0.05377 0.04828 -0.0252 0.0050 1.0000
14.250 1.3131 0.05669 0.05131 -0.0252 0.0050 1.0000
14.500 1.3135 0.05969 0.05441 -0.0256 0.0048 1.0000
14.750 1.3119 0.06307 0.05791 -0.0259 0.0048 1.0000
15.000 1.3108 0.06648 0.06142 -0.0266 0.0048 1.0000
15.250 1.3074 0.07030 0.06537 -0.0273 0.0047 1.0000
15.500 1.3046 0.07416 0.06935 -0.0283 0.0047 1.0000
15.750 1.3003 0.07839 0.07371 -0.0294 0.0046 1.0000
16.000 1.2948 0.08291 0.07836 -0.0308 0.0046 1.0000
16.250 1.2889 0.08763 0.08321 -0.0324 0.0046 1.0000
16.500 1.2808 0.09285 0.08857 -0.0344 0.0045 1.0000
16.750 1.2735 0.09813 0.09399 -0.0366 0.0045 1.0000
17.000 1.2666 0.10351 0.09951 -0.0390 0.0045 1.0000
17.250 1.2571 0.10949 0.10564 -0.0418 0.0045 1.0000
17.500 1.2455 0.11604 0.11235 -0.0451 0.0044 1.0000
17.750 1.2372 0.12224 0.11871 -0.0484 0.0045 1.0000
18.000 1.2257 0.12919 0.12581 -0.0522 0.0044 1.0000
18.250 1.2154 0.13612 0.13287 -0.0562 0.0044 1.0000
18.500 1.2037 0.14360 0.14050 -0.0607 0.0044 1.0000
18.750 1.1923 0.15124 0.14828 -0.0653 0.0044 1.0000
19.000 1.1812 0.15910 0.15628 -0.0702 0.0044 1.0000
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