EPPLER 555 AIRFOIL (e555-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 555 AIRFOIL (e555-il) Reynolds number: 100,000 Max Cl/Cd: 51.16 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e555-il-100000-n5.txt Download as CSV file: xf-e555-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 555 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.5663 0.09845 0.09279 -0.0551 1.0000 0.0189
-13.500 -0.5993 0.08831 0.08245 -0.0608 1.0000 0.0181
-13.250 -0.6250 0.08075 0.07469 -0.0648 1.0000 0.0180
-13.000 -0.6433 0.07515 0.06893 -0.0675 1.0000 0.0179
-12.750 -0.6623 0.06967 0.06323 -0.0696 1.0000 0.0177
-12.500 -0.6730 0.06577 0.05920 -0.0708 1.0000 0.0180
-12.250 -0.6838 0.06187 0.05511 -0.0717 1.0000 0.0180
-12.000 -0.6914 0.05864 0.05174 -0.0721 1.0000 0.0183
-11.750 -0.6983 0.05560 0.04855 -0.0721 1.0000 0.0188
-11.500 -0.7029 0.05285 0.04564 -0.0717 1.0000 0.0191
-11.250 -0.7052 0.05034 0.04296 -0.0709 1.0000 0.0193
-11.000 -0.7063 0.04800 0.04043 -0.0697 1.0000 0.0198
-10.750 -0.7047 0.04591 0.03815 -0.0681 1.0000 0.0202
-10.500 -0.7007 0.04417 0.03632 -0.0663 1.0000 0.0207
-10.250 -0.6973 0.04270 0.03484 -0.0644 1.0000 0.0210
-10.000 -0.6959 0.04131 0.03344 -0.0622 1.0000 0.0215
-9.750 -0.6962 0.04002 0.03211 -0.0597 1.0000 0.0222
-9.500 -0.6991 0.03883 0.03089 -0.0566 1.0000 0.0228
-9.250 -0.7063 0.03775 0.02978 -0.0530 1.0000 0.0233
-9.000 -0.7120 0.03663 0.02860 -0.0497 1.0000 0.0241
-8.750 -0.7147 0.03546 0.02738 -0.0470 1.0000 0.0251
-8.500 -0.7081 0.03411 0.02607 -0.0464 0.9983 0.0266
-8.250 -0.6790 0.03269 0.02453 -0.0488 0.9924 0.0297
-8.000 -0.6525 0.03104 0.02289 -0.0513 0.9853 0.0326
-7.750 -0.6264 0.02950 0.02128 -0.0536 0.9776 0.0380
-7.500 -0.5986 0.02791 0.01965 -0.0562 0.9703 0.0453
-7.250 -0.5717 0.02631 0.01807 -0.0586 0.9622 0.0568
-7.000 -0.5450 0.02466 0.01650 -0.0610 0.9543 0.0778
-6.750 -0.5146 0.02268 0.01476 -0.0645 0.9477 0.1235
-6.500 -0.4886 0.02009 0.01286 -0.0682 0.9397 0.2358
-6.250 -0.4547 0.01965 0.01304 -0.0702 0.9337 0.3646
-6.000 -0.4202 0.01981 0.01304 -0.0716 0.9270 0.4041
-5.750 -0.3855 0.02003 0.01304 -0.0729 0.9201 0.4303
-5.500 -0.3464 0.02034 0.01320 -0.0746 0.9159 0.4487
-5.250 -0.3176 0.02058 0.01329 -0.0746 0.9069 0.4626
-5.000 -0.2810 0.02109 0.01376 -0.0754 0.9019 0.4762
-4.750 -0.2503 0.02140 0.01402 -0.0753 0.8942 0.4859
-4.500 -0.2132 0.02109 0.01347 -0.0774 0.8882 0.4944
-4.250 -0.1747 0.02084 0.01309 -0.0794 0.8833 0.4985
-4.000 -0.1447 0.02067 0.01282 -0.0798 0.8744 0.5019
-3.750 -0.1053 0.02031 0.01229 -0.0822 0.8693 0.5063
-3.500 -0.0744 0.01991 0.01168 -0.0835 0.8596 0.5117
-3.250 -0.0370 0.01965 0.01132 -0.0852 0.8535 0.5145
-3.000 -0.0080 0.01949 0.01109 -0.0854 0.8436 0.5172
-2.750 0.0292 0.01923 0.01072 -0.0873 0.8369 0.5210
-2.500 0.0584 0.01901 0.01037 -0.0878 0.8264 0.5252
-2.250 0.0943 0.01869 0.00991 -0.0897 0.8186 0.5292
-2.000 0.1237 0.01857 0.00975 -0.0899 0.8085 0.5317
-1.750 0.1549 0.01845 0.00957 -0.0905 0.7993 0.5349
-1.500 0.1876 0.01828 0.00933 -0.0914 0.7902 0.5387
-1.250 0.2173 0.01813 0.00907 -0.0920 0.7797 0.5429
-1.000 0.2507 0.01796 0.00880 -0.0931 0.7710 0.5463
-0.750 0.2778 0.01792 0.00876 -0.0930 0.7600 0.5491
-0.500 0.3069 0.01786 0.00867 -0.0932 0.7499 0.5526
-0.250 0.3380 0.01777 0.00851 -0.0938 0.7404 0.5568
0.000 0.3661 0.01771 0.00837 -0.0941 0.7292 0.5612
0.250 0.3948 0.01767 0.00832 -0.0941 0.7194 0.5640
0.500 0.4231 0.01765 0.00830 -0.0942 0.7092 0.5673
0.750 0.4502 0.01766 0.00831 -0.0940 0.6984 0.5714
1.000 0.4799 0.01764 0.00822 -0.0945 0.6888 0.5762
1.250 0.5071 0.01765 0.00823 -0.0943 0.6780 0.5799
1.500 0.5338 0.01769 0.00831 -0.0941 0.6676 0.5833
1.750 0.5627 0.01771 0.00830 -0.0942 0.6582 0.5875
2.000 0.5891 0.01777 0.00837 -0.0941 0.6470 0.5925
2.250 0.6160 0.01783 0.00845 -0.0939 0.6367 0.5967
2.500 0.6434 0.01789 0.00853 -0.0937 0.6270 0.6010
2.750 0.6688 0.01799 0.00868 -0.0933 0.6158 0.6059
3.000 0.6961 0.01808 0.00877 -0.0933 0.6054 0.6112
3.250 0.7224 0.01817 0.00890 -0.0929 0.5953 0.6153
3.500 0.7473 0.01830 0.00910 -0.0924 0.5839 0.6206
3.750 0.7741 0.01843 0.00925 -0.0923 0.5732 0.6270
4.000 0.7999 0.01854 0.00941 -0.0918 0.5626 0.6318
4.250 0.8241 0.01869 0.00965 -0.0911 0.5505 0.6375
4.500 0.8496 0.01886 0.00986 -0.0907 0.5389 0.6440
4.750 0.8741 0.01901 0.01006 -0.0901 0.5276 0.6497
5.000 0.8986 0.01918 0.01029 -0.0895 0.5155 0.6570
5.250 0.9219 0.01938 0.01060 -0.0886 0.5029 0.6637
5.500 0.9455 0.01958 0.01088 -0.0879 0.4905 0.6713
5.750 0.9691 0.01980 0.01114 -0.0871 0.4781 0.6789
6.000 0.9921 0.02002 0.01143 -0.0862 0.4654 0.6871
6.250 1.0139 0.02027 0.01177 -0.0852 0.4518 0.6959
6.500 1.0354 0.02054 0.01213 -0.0841 0.4380 0.7060
6.750 1.0559 0.02081 0.01251 -0.0828 0.4240 0.7158
7.000 1.0761 0.02111 0.01291 -0.0815 0.4098 0.7271
7.250 1.0955 0.02143 0.01332 -0.0801 0.3952 0.7395
7.500 1.1133 0.02176 0.01375 -0.0783 0.3801 0.7528
8.000 1.1450 0.02249 0.01470 -0.0743 0.3485 0.7864
8.250 1.1579 0.02288 0.01519 -0.0718 0.3324 0.8083
8.500 1.1679 0.02326 0.01569 -0.0687 0.3162 0.8382
9.000 1.1836 0.02409 0.01669 -0.0623 0.2833 1.0000
9.250 1.1952 0.02491 0.01747 -0.0603 0.2652 1.0000
9.500 1.2050 0.02583 0.01834 -0.0582 0.2475 1.0000
9.750 1.2137 0.02685 0.01933 -0.0561 0.2301 1.0000
10.000 1.2213 0.02797 0.02043 -0.0540 0.2134 1.0000
10.250 1.2276 0.02921 0.02165 -0.0519 0.1979 1.0000
10.500 1.2329 0.03059 0.02302 -0.0499 0.1835 1.0000
10.750 1.2371 0.03210 0.02452 -0.0479 0.1703 1.0000
11.000 1.2405 0.03375 0.02617 -0.0462 0.1580 1.0000
11.250 1.2446 0.03546 0.02791 -0.0446 0.1463 1.0000
11.500 1.2476 0.03732 0.02981 -0.0432 0.1357 1.0000
11.750 1.2488 0.03941 0.03191 -0.0420 0.1263 1.0000
12.000 1.2499 0.04161 0.03415 -0.0409 0.1175 1.0000
12.250 1.2517 0.04387 0.03650 -0.0400 0.1092 1.0000
12.500 1.2498 0.04653 0.03916 -0.0393 0.1025 1.0000
12.750 1.2519 0.04897 0.04173 -0.0388 0.0952 1.0000
13.000 1.2487 0.05198 0.04474 -0.0385 0.0899 1.0000
13.250 1.2500 0.05469 0.04759 -0.0383 0.0838 1.0000
13.500 1.2469 0.05792 0.05087 -0.0384 0.0791 1.0000
13.750 1.2456 0.06109 0.05414 -0.0385 0.0744 1.0000
14.000 1.2441 0.06441 0.05757 -0.0389 0.0700 1.0000
14.250 1.2391 0.06821 0.06138 -0.0396 0.0667 1.0000
14.500 1.2385 0.07165 0.06498 -0.0401 0.0627 1.0000
14.750 1.2355 0.07548 0.06894 -0.0411 0.0592 1.0000
15.000 1.2307 0.07961 0.07309 -0.0422 0.0566 1.0000
15.250 1.2291 0.08346 0.07710 -0.0432 0.0536 1.0000
15.500 1.2259 0.08763 0.08141 -0.0446 0.0508 1.0000
15.750 1.2215 0.09206 0.08591 -0.0462 0.0485 1.0000
16.000 1.2180 0.09635 0.09025 -0.0478 0.0465 1.0000
16.250 1.2149 0.10083 0.09493 -0.0495 0.0442 1.0000
16.500 1.2109 0.10547 0.09970 -0.0515 0.0422 1.0000
16.750 1.2067 0.11017 0.10448 -0.0537 0.0405 1.0000
17.000 1.2041 0.11453 0.10886 -0.0556 0.0390 1.0000
17.250 1.1987 0.11978 0.11435 -0.0582 0.0375 1.0000
17.500 1.1930 0.12511 0.11985 -0.0609 0.0360 1.0000
17.750 1.1877 0.13038 0.12525 -0.0639 0.0347 1.0000
18.000 1.1842 0.13528 0.13021 -0.0667 0.0335 1.0000
18.250 1.1831 0.13960 0.13455 -0.0691 0.0323 1.0000
18.500 1.1720 0.14658 0.14178 -0.0734 0.0315 1.0000
18.750 1.1598 0.15397 0.14939 -0.0780 0.0308 1.0000
19.000 1.1444 0.16237 0.15799 -0.0835 0.0302 1.0000
19.250 1.1219 0.17308 0.16889 -0.0905 0.0299 1.0000
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Polar data table (+)
Polar graphs
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