EPPLER 556 AIRFOIL (e556-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 556 AIRFOIL (e556-il) Reynolds number: 100,000 Max Cl/Cd: 53.19 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e556-il-100000-n5.txt Download as CSV file: xf-e556-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 556 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5272 0.10021 0.09464 -0.0570 1.0000 0.0201
-13.250 -0.5554 0.09069 0.08500 -0.0623 1.0000 0.0197
-13.000 -0.5833 0.08243 0.07659 -0.0668 1.0000 0.0196
-12.750 -0.6059 0.07603 0.07003 -0.0700 1.0000 0.0194
-12.500 -0.6263 0.07046 0.06429 -0.0724 1.0000 0.0195
-12.250 -0.6409 0.06603 0.05971 -0.0738 1.0000 0.0194
-12.000 -0.6540 0.06204 0.05556 -0.0747 1.0000 0.0194
-11.750 -0.6663 0.05836 0.05171 -0.0751 1.0000 0.0196
-11.500 -0.6755 0.05522 0.04842 -0.0749 1.0000 0.0197
-11.250 -0.6828 0.05247 0.04552 -0.0742 1.0000 0.0199
-11.000 -0.6896 0.04990 0.04279 -0.0730 1.0000 0.0202
-10.750 -0.6951 0.04767 0.04039 -0.0714 1.0000 0.0206
-10.500 -0.7006 0.04573 0.03828 -0.0693 1.0000 0.0210
-10.250 -0.7062 0.04410 0.03661 -0.0668 1.0000 0.0215
-10.000 -0.7146 0.04278 0.03530 -0.0639 1.0000 0.0218
-9.750 -0.7253 0.04156 0.03407 -0.0605 1.0000 0.0221
-9.500 -0.7318 0.04023 0.03271 -0.0582 1.0000 0.0228
-9.250 -0.7336 0.03891 0.03133 -0.0562 1.0000 0.0236
-9.000 -0.7055 0.03715 0.02934 -0.0584 0.9952 0.0258
-8.750 -0.6794 0.03549 0.02767 -0.0601 0.9897 0.0273
-8.500 -0.6514 0.03393 0.02605 -0.0624 0.9842 0.0296
-8.250 -0.6262 0.03251 0.02450 -0.0638 0.9771 0.0326
-8.000 -0.6003 0.03098 0.02299 -0.0661 0.9700 0.0367
-7.750 -0.5727 0.02945 0.02142 -0.0684 0.9632 0.0425
-7.500 -0.5472 0.02807 0.01999 -0.0702 0.9553 0.0499
-7.250 -0.5161 0.02656 0.01848 -0.0732 0.9495 0.0618
-7.000 -0.4898 0.02514 0.01708 -0.0752 0.9414 0.0776
-6.750 -0.4566 0.02348 0.01552 -0.0787 0.9359 0.1063
-6.500 -0.4267 0.02162 0.01391 -0.0820 0.9289 0.1591
-6.250 -0.3936 0.01974 0.01285 -0.0860 0.9230 0.2933
-6.000 -0.3544 0.01976 0.01298 -0.0882 0.9191 0.3699
-5.750 -0.3252 0.01993 0.01301 -0.0885 0.9103 0.3999
-5.500 -0.2873 0.02012 0.01300 -0.0902 0.9056 0.4226
-5.250 -0.2555 0.02035 0.01309 -0.0907 0.8986 0.4379
-5.000 -0.2218 0.02059 0.01323 -0.0913 0.8923 0.4505
-4.750 -0.1832 0.02090 0.01344 -0.0927 0.8884 0.4648
-4.500 -0.1553 0.02105 0.01348 -0.0925 0.8792 0.4763
-4.250 -0.1175 0.02102 0.01334 -0.0941 0.8743 0.4831
-4.000 -0.0834 0.02057 0.01264 -0.0960 0.8667 0.4899
-3.750 -0.0490 0.02039 0.01239 -0.0970 0.8601 0.4929
-3.500 -0.0139 0.02016 0.01205 -0.0984 0.8537 0.4965
-3.000 0.0580 0.01946 0.01100 -0.1021 0.8394 0.5062
-2.750 0.0872 0.01932 0.01081 -0.1023 0.8298 0.5088
-2.500 0.1227 0.01911 0.01051 -0.1037 0.8229 0.5119
-2.250 0.1535 0.01894 0.01025 -0.1044 0.8135 0.5160
-2.000 0.1881 0.01868 0.00984 -0.1060 0.8053 0.5208
-1.750 0.2201 0.01851 0.00961 -0.1068 0.7963 0.5238
-1.500 0.2501 0.01841 0.00947 -0.1072 0.7869 0.5267
-1.250 0.2836 0.01827 0.00926 -0.1082 0.7785 0.5306
-1.000 0.3123 0.01818 0.00910 -0.1086 0.7681 0.5349
-0.750 0.3456 0.01803 0.00884 -0.1097 0.7595 0.5390
-0.500 0.3735 0.01799 0.00879 -0.1097 0.7493 0.5418
-0.250 0.4023 0.01795 0.00873 -0.1098 0.7394 0.5453
0.000 0.4339 0.01788 0.00859 -0.1106 0.7305 0.5497
0.250 0.4619 0.01786 0.00850 -0.1108 0.7196 0.5546
0.500 0.4905 0.01784 0.00849 -0.1108 0.7102 0.5576
0.750 0.5188 0.01784 0.00848 -0.1109 0.7004 0.5611
1.000 0.5462 0.01786 0.00850 -0.1108 0.6901 0.5654
1.250 0.5770 0.01786 0.00841 -0.1115 0.6811 0.5707
1.500 0.6024 0.01791 0.00853 -0.1109 0.6705 0.5742
1.750 0.6296 0.01797 0.00860 -0.1108 0.6607 0.5784
2.000 0.6585 0.01801 0.00860 -0.1110 0.6514 0.5833
2.250 0.6845 0.01809 0.00872 -0.1107 0.6407 0.5880
2.500 0.7114 0.01817 0.00883 -0.1105 0.6313 0.5922
2.750 0.7381 0.01826 0.00894 -0.1103 0.6212 0.5975
3.000 0.7646 0.01838 0.00909 -0.1101 0.6107 0.6033
3.250 0.7914 0.01847 0.00921 -0.1098 0.6013 0.6078
3.500 0.8167 0.01860 0.00940 -0.1094 0.5906 0.6132
3.750 0.8429 0.01875 0.00959 -0.1091 0.5801 0.6194
4.000 0.8691 0.01887 0.00975 -0.1087 0.5704 0.6247
4.250 0.8936 0.01904 0.00999 -0.1081 0.5590 0.6314
4.500 0.9182 0.01921 0.01024 -0.1075 0.5478 0.6377
4.750 0.9433 0.01938 0.01045 -0.1070 0.5371 0.6442
5.000 0.9681 0.01957 0.01068 -0.1065 0.5256 0.6517
5.250 0.9908 0.01977 0.01100 -0.1055 0.5135 0.6586
5.500 1.0148 0.01999 0.01127 -0.1048 0.5017 0.6673
5.750 1.0380 0.02020 0.01155 -0.1039 0.4902 0.6751
6.000 1.0610 0.02044 0.01186 -0.1031 0.4780 0.6843
6.250 1.0822 0.02070 0.01223 -0.1019 0.4651 0.6936
6.500 1.1033 0.02097 0.01259 -0.1007 0.4521 0.7037
6.750 1.1242 0.02125 0.01296 -0.0995 0.4389 0.7154
7.000 1.1439 0.02155 0.01335 -0.0981 0.4254 0.7275
7.250 1.1626 0.02186 0.01375 -0.0965 0.4117 0.7405
7.500 1.1803 0.02219 0.01417 -0.0947 0.3978 0.7555
7.750 1.1964 0.02254 0.01462 -0.0927 0.3833 0.7729
8.000 1.2108 0.02291 0.01512 -0.0904 0.3685 0.7938
8.250 1.2224 0.02327 0.01561 -0.0876 0.3537 0.8204
8.500 1.2294 0.02356 0.01605 -0.0838 0.3395 0.8619
8.750 1.2359 0.02386 0.01645 -0.0802 0.3247 1.0000
9.000 1.2491 0.02459 0.01715 -0.0784 0.3079 1.0000
9.250 1.2605 0.02540 0.01794 -0.0763 0.2909 1.0000
9.500 1.2708 0.02628 0.01883 -0.0742 0.2735 1.0000
9.750 1.2796 0.02728 0.01981 -0.0720 0.2562 1.0000
10.000 1.2870 0.02839 0.02091 -0.0698 0.2395 1.0000
10.250 1.2931 0.02963 0.02213 -0.0676 0.2235 1.0000
10.500 1.2981 0.03101 0.02349 -0.0655 0.2083 1.0000
10.750 1.3023 0.03252 0.02500 -0.0634 0.1941 1.0000
11.000 1.3058 0.03416 0.02666 -0.0616 0.1810 1.0000
11.250 1.3083 0.03597 0.02846 -0.0598 0.1690 1.0000
11.500 1.3096 0.03795 0.03044 -0.0582 0.1578 1.0000
11.750 1.3123 0.03995 0.03249 -0.0569 0.1467 1.0000
12.000 1.3140 0.04211 0.03470 -0.0557 0.1370 1.0000
12.250 1.3133 0.04456 0.03716 -0.0547 0.1284 1.0000
12.500 1.3144 0.04700 0.03968 -0.0539 0.1196 1.0000
12.750 1.3140 0.04964 0.04237 -0.0532 0.1123 1.0000
13.000 1.3127 0.05248 0.04527 -0.0527 0.1053 1.0000
13.250 1.3120 0.05539 0.04828 -0.0524 0.0989 1.0000
13.500 1.3102 0.05850 0.05147 -0.0523 0.0930 1.0000
13.750 1.3076 0.06180 0.05482 -0.0524 0.0880 1.0000
14.000 1.3066 0.06508 0.05824 -0.0526 0.0825 1.0000
14.250 1.3017 0.06889 0.06206 -0.0531 0.0784 1.0000
14.500 1.3011 0.07230 0.06562 -0.0536 0.0738 1.0000
14.750 1.2982 0.07612 0.06955 -0.0543 0.0697 1.0000
15.000 1.2928 0.08031 0.07374 -0.0553 0.0666 1.0000
15.250 1.2917 0.08409 0.07770 -0.0562 0.0628 1.0000
15.500 1.2886 0.08822 0.08196 -0.0574 0.0595 1.0000
15.750 1.2841 0.09260 0.08639 -0.0589 0.0569 1.0000
16.000 1.2812 0.09681 0.09069 -0.0602 0.0543 1.0000
16.250 1.2784 0.10116 0.09524 -0.0618 0.0515 1.0000
16.500 1.2744 0.10574 0.09993 -0.0636 0.0491 1.0000
16.750 1.2707 0.11026 0.10450 -0.0655 0.0472 1.0000
17.000 1.2680 0.11467 0.10901 -0.0674 0.0452 1.0000
17.250 1.2640 0.11953 0.11407 -0.0696 0.0432 1.0000
17.500 1.2596 0.12447 0.11914 -0.0721 0.0414 1.0000
17.750 1.2560 0.12927 0.12403 -0.0746 0.0398 1.0000
18.000 1.2542 0.13362 0.12842 -0.0769 0.0384 1.0000
18.250 1.2502 0.13865 0.13358 -0.0796 0.0371 1.0000
18.500 1.2419 0.14479 0.13995 -0.0832 0.0359 1.0000
18.750 1.2332 0.15111 0.14645 -0.0871 0.0347 1.0000
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Polar data table (+)
Polar graphs
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