EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 558 AIRFOIL (e558-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.55 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e558-il-1000000-n5.txt Download as CSV file: xf-e558-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 558 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.8336 0.08832 0.08498 -0.0530 1.0000 0.0063
-16.250 -0.8435 0.08348 0.08008 -0.0552 1.0000 0.0065
-16.000 -0.8560 0.07834 0.07487 -0.0576 1.0000 0.0065
-15.750 -0.8672 0.07352 0.06998 -0.0598 1.0000 0.0065
-15.500 -0.8810 0.06846 0.06483 -0.0621 1.0000 0.0065
-15.250 -0.8961 0.06344 0.05973 -0.0643 1.0000 0.0064
-15.000 -0.9110 0.05875 0.05497 -0.0663 1.0000 0.0066
-14.750 -0.9304 0.05371 0.04983 -0.0683 1.0000 0.0065
-14.500 -0.9486 0.04902 0.04506 -0.0699 1.0000 0.0065
-14.250 -0.9639 0.04484 0.04081 -0.0712 1.0000 0.0066
-14.000 -0.9841 0.04028 0.03615 -0.0724 1.0000 0.0065
-13.750 -1.0038 0.03597 0.03175 -0.0733 1.0000 0.0066
-13.500 -0.9998 0.03199 0.02767 -0.0777 0.9986 0.0067
-13.250 -0.9882 0.02768 0.02322 -0.0847 0.9955 0.0067
-13.000 -0.9713 0.02434 0.01974 -0.0911 0.9920 0.0068
-12.750 -0.9493 0.02277 0.01808 -0.0933 0.9887 0.0069
-12.500 -0.9234 0.02147 0.01670 -0.0955 0.9860 0.0070
-12.250 -0.8945 0.02038 0.01554 -0.0977 0.9840 0.0072
-12.000 -0.8684 0.01946 0.01456 -0.0990 0.9814 0.0073
-11.750 -0.8478 0.01865 0.01369 -0.0987 0.9764 0.0074
-11.500 -0.8193 0.01788 0.01287 -0.1000 0.9729 0.0075
-11.250 -0.7981 0.01717 0.01210 -0.0996 0.9667 0.0077
-11.000 -0.7741 0.01638 0.01125 -0.0998 0.9596 0.0079
-10.750 -0.7529 0.01573 0.01056 -0.0991 0.9495 0.0081
-10.500 -0.7219 0.01507 0.00986 -0.1003 0.9415 0.0084
-10.250 -0.6833 0.01442 0.00916 -0.1031 0.9336 0.0087
-10.000 -0.6328 0.01378 0.00847 -0.1083 0.9260 0.0092
-9.750 -0.5774 0.01320 0.00780 -0.1145 0.9123 0.0097
-9.500 -0.5371 0.01274 0.00720 -0.1175 0.8833 0.0104
-9.250 -0.5106 0.01246 0.00677 -0.1175 0.8522 0.0112
-9.000 -0.4869 0.01224 0.00642 -0.1168 0.8256 0.0119
-8.750 -0.4634 0.01198 0.00606 -0.1161 0.8030 0.0134
-8.500 -0.4397 0.01175 0.00573 -0.1154 0.7812 0.0151
-8.250 -0.4157 0.01148 0.00538 -0.1148 0.7623 0.0183
-8.000 -0.3915 0.01119 0.00504 -0.1143 0.7446 0.0229
-7.750 -0.3667 0.01092 0.00472 -0.1138 0.7282 0.0291
-7.500 -0.3419 0.01063 0.00440 -0.1133 0.7128 0.0375
-7.250 -0.3166 0.01035 0.00411 -0.1130 0.6986 0.0475
-7.000 -0.2912 0.01007 0.00382 -0.1126 0.6846 0.0594
-6.750 -0.2653 0.00980 0.00356 -0.1123 0.6711 0.0729
-6.500 -0.2393 0.00953 0.00331 -0.1121 0.6587 0.0877
-6.250 -0.2130 0.00931 0.00309 -0.1118 0.6465 0.1026
-6.000 -0.1864 0.00910 0.00289 -0.1116 0.6342 0.1191
-5.750 -0.1598 0.00887 0.00270 -0.1115 0.6225 0.1384
-5.500 -0.1332 0.00868 0.00253 -0.1113 0.6114 0.1589
-5.250 -0.1059 0.00852 0.00240 -0.1112 0.6010 0.1765
-5.000 -0.0786 0.00840 0.00229 -0.1110 0.5904 0.1927
-4.750 -0.0512 0.00833 0.00219 -0.1109 0.5791 0.2032
-4.500 -0.0232 0.00828 0.00211 -0.1108 0.5697 0.2110
-4.000 0.0324 0.00820 0.00197 -0.1105 0.5498 0.2278
-3.750 0.0600 0.00817 0.00191 -0.1104 0.5401 0.2365
-3.500 0.0882 0.00815 0.00186 -0.1103 0.5312 0.2435
-3.250 0.1160 0.00812 0.00181 -0.1102 0.5226 0.2514
-3.000 0.1441 0.00811 0.00177 -0.1101 0.5136 0.2590
-2.750 0.1719 0.00811 0.00174 -0.1100 0.5047 0.2656
-2.500 0.2000 0.00810 0.00171 -0.1100 0.4966 0.2728
-2.250 0.2279 0.00813 0.00169 -0.1098 0.4888 0.2792
-2.000 0.2561 0.00811 0.00168 -0.1098 0.4812 0.2869
-1.750 0.2839 0.00815 0.00167 -0.1097 0.4728 0.2929
-1.500 0.3120 0.00815 0.00166 -0.1096 0.4657 0.2995
-1.250 0.3400 0.00817 0.00167 -0.1095 0.4586 0.3068
-1.000 0.3679 0.00821 0.00167 -0.1094 0.4521 0.3118
-0.750 0.3960 0.00822 0.00169 -0.1093 0.4452 0.3192
-0.500 0.4236 0.00827 0.00171 -0.1092 0.4376 0.3261
-0.250 0.4517 0.00830 0.00172 -0.1091 0.4318 0.3314
0.000 0.4796 0.00832 0.00175 -0.1090 0.4255 0.3388
0.250 0.5073 0.00839 0.00179 -0.1088 0.4192 0.3452
0.500 0.5353 0.00841 0.00182 -0.1088 0.4133 0.3516
0.750 0.5629 0.00847 0.00187 -0.1086 0.4069 0.3585
1.250 0.6185 0.00856 0.00197 -0.1084 0.3969 0.3722
1.500 0.6461 0.00862 0.00202 -0.1083 0.3912 0.3788
1.750 0.6733 0.00871 0.00209 -0.1081 0.3854 0.3852
2.000 0.7011 0.00875 0.00215 -0.1080 0.3806 0.3934
2.250 0.7286 0.00881 0.00222 -0.1078 0.3756 0.3998
2.500 0.7558 0.00889 0.00230 -0.1076 0.3706 0.4074
2.750 0.7832 0.00896 0.00238 -0.1074 0.3662 0.4156
3.000 0.8106 0.00902 0.00246 -0.1073 0.3613 0.4229
3.250 0.8376 0.00911 0.00256 -0.1070 0.3563 0.4311
3.500 0.8645 0.00921 0.00266 -0.1068 0.3517 0.4392
3.750 0.8918 0.00926 0.00276 -0.1066 0.3478 0.4496
4.000 0.9187 0.00935 0.00286 -0.1064 0.3428 0.4585
4.250 0.9452 0.00945 0.00298 -0.1061 0.3378 0.4688
4.500 0.9719 0.00954 0.00310 -0.1058 0.3334 0.4807
5.000 1.0249 0.00973 0.00336 -0.1052 0.3234 0.5064
5.250 1.0508 0.00985 0.00351 -0.1049 0.3184 0.5217
5.500 1.0773 0.00993 0.00365 -0.1046 0.3142 0.5396
5.750 1.1033 0.01003 0.00380 -0.1042 0.3091 0.5581
6.000 1.1286 0.01017 0.00398 -0.1038 0.3037 0.5798
6.250 1.1545 0.01025 0.00414 -0.1034 0.2992 0.6045
6.500 1.1799 0.01036 0.00432 -0.1029 0.2938 0.6331
6.750 1.2042 0.01051 0.00453 -0.1023 0.2870 0.6640
7.000 1.2293 0.01059 0.00472 -0.1018 0.2816 0.7048
7.250 1.2532 0.01070 0.00494 -0.1011 0.2752 0.7501
7.500 1.2758 0.01081 0.00518 -0.1001 0.2692 0.8072
7.750 1.2941 0.01077 0.00538 -0.0981 0.2633 0.9044
8.000 1.3200 0.01095 0.00560 -0.0978 0.2559 1.0000
8.250 1.3437 0.01117 0.00582 -0.0971 0.2490 1.0000
8.500 1.3649 0.01150 0.00610 -0.0960 0.2378 1.0000
8.750 1.3847 0.01189 0.00642 -0.0946 0.2240 1.0000
9.000 1.4021 0.01232 0.00676 -0.0928 0.2084 1.0000
9.250 1.4196 0.01271 0.00711 -0.0911 0.1964 1.0000
9.500 1.4364 0.01313 0.00748 -0.0892 0.1847 1.0000
9.750 1.4516 0.01362 0.00791 -0.0871 0.1717 1.0000
10.000 1.4648 0.01421 0.00842 -0.0847 0.1567 1.0000
10.250 1.4773 0.01481 0.00896 -0.0823 0.1432 1.0000
10.500 1.4895 0.01544 0.00953 -0.0799 0.1309 1.0000
10.750 1.4990 0.01619 0.01021 -0.0772 0.1169 1.0000
11.000 1.5084 0.01695 0.01092 -0.0746 0.1052 1.0000
11.250 1.5166 0.01779 0.01170 -0.0719 0.0941 1.0000
11.500 1.5248 0.01864 0.01253 -0.0693 0.0853 1.0000
11.750 1.5313 0.01962 0.01347 -0.0667 0.0766 1.0000
12.000 1.5394 0.02056 0.01441 -0.0644 0.0699 1.0000
12.250 1.5460 0.02164 0.01548 -0.0621 0.0637 1.0000
12.500 1.5502 0.02292 0.01675 -0.0598 0.0575 1.0000
12.750 1.5546 0.02428 0.01812 -0.0578 0.0516 1.0000
13.000 1.5590 0.02573 0.01959 -0.0559 0.0472 1.0000
13.250 1.5609 0.02746 0.02133 -0.0541 0.0424 1.0000
13.500 1.5644 0.02917 0.02307 -0.0527 0.0387 1.0000
13.750 1.5666 0.03110 0.02504 -0.0514 0.0358 1.0000
14.000 1.5689 0.03313 0.02711 -0.0503 0.0329 1.0000
14.250 1.5688 0.03547 0.02948 -0.0493 0.0300 1.0000
14.500 1.5695 0.03784 0.03191 -0.0486 0.0278 1.0000
14.750 1.5678 0.04056 0.03467 -0.0480 0.0252 1.0000
15.000 1.5647 0.04352 0.03769 -0.0476 0.0227 1.0000
15.250 1.5616 0.04662 0.04084 -0.0474 0.0206 1.0000
15.500 1.5567 0.05002 0.04430 -0.0474 0.0185 1.0000
15.750 1.5521 0.05350 0.04784 -0.0476 0.0168 1.0000
16.000 1.5459 0.05729 0.05170 -0.0480 0.0154 1.0000
16.250 1.5410 0.06103 0.05551 -0.0485 0.0143 1.0000
16.500 1.5332 0.06523 0.05978 -0.0492 0.0131 1.0000
16.750 1.5283 0.06916 0.06379 -0.0500 0.0126 1.0000
17.000 1.5222 0.07336 0.06808 -0.0509 0.0118 1.0000
17.250 1.5165 0.07758 0.07237 -0.0520 0.0114 1.0000
17.500 1.5096 0.08204 0.07691 -0.0532 0.0109 1.0000
17.750 1.5037 0.08643 0.08138 -0.0545 0.0106 1.0000
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Polar data table (+)
Polar graphs
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