EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 558 AIRFOIL (e558-il) Reynolds number: 500,000 Max Cl/Cd: 100.12 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e558-il-500000.txt Download as CSV file: xf-e558-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.6059 0.13866 0.13588 -0.0318 1.0000 0.0146
-17.000 -0.6657 0.12112 0.11808 -0.0409 1.0000 0.0141
-16.750 -0.7007 0.11003 0.10678 -0.0468 1.0000 0.0138
-16.500 -0.7211 0.10234 0.09894 -0.0509 1.0000 0.0137
-16.250 -0.7386 0.09545 0.09192 -0.0546 1.0000 0.0138
-16.000 -0.7529 0.08944 0.08578 -0.0576 1.0000 0.0137
-15.750 -0.7617 0.08448 0.08071 -0.0601 1.0000 0.0138
-15.500 -0.7705 0.07972 0.07584 -0.0624 1.0000 0.0138
-15.250 -0.7777 0.07539 0.07141 -0.0643 1.0000 0.0137
-15.000 -0.7843 0.07121 0.06714 -0.0663 1.0000 0.0139
-14.750 -0.7886 0.06765 0.06350 -0.0675 1.0000 0.0138
-14.500 -0.7931 0.06414 0.05990 -0.0689 1.0000 0.0139
-14.250 -0.7997 0.06050 0.05618 -0.0703 1.0000 0.0142
-14.000 -0.8023 0.05761 0.05322 -0.0710 1.0000 0.0141
-13.750 -0.8065 0.05455 0.05009 -0.0717 1.0000 0.0142
-13.500 -0.8113 0.05146 0.04692 -0.0725 1.0000 0.0144
-13.250 -0.8149 0.04873 0.04414 -0.0728 1.0000 0.0144
-13.000 -0.8188 0.04602 0.04136 -0.0731 1.0000 0.0145
-12.750 -0.8233 0.04335 0.03863 -0.0732 1.0000 0.0145
-12.500 -0.8288 0.04066 0.03588 -0.0733 1.0000 0.0147
-12.250 -0.8352 0.03809 0.03325 -0.0730 1.0000 0.0147
-12.000 -0.8433 0.03558 0.03067 -0.0724 1.0000 0.0148
-11.750 -0.8565 0.03309 0.02811 -0.0713 1.0000 0.0149
-11.500 -0.8800 0.03060 0.02556 -0.0691 1.0000 0.0149
-11.250 -0.8854 0.02856 0.02341 -0.0684 1.0000 0.0150
-11.000 -0.8652 0.02649 0.02126 -0.0711 0.9974 0.0152
-10.750 -0.8322 0.02439 0.01910 -0.0758 0.9937 0.0157
-10.500 -0.8008 0.02291 0.01756 -0.0788 0.9893 0.0162
-10.250 -0.7665 0.02165 0.01623 -0.0819 0.9857 0.0168
-10.000 -0.7296 0.02053 0.01501 -0.0852 0.9832 0.0175
-9.750 -0.6997 0.01947 0.01387 -0.0868 0.9776 0.0183
-9.500 -0.6658 0.01820 0.01255 -0.0895 0.9735 0.0194
-9.250 -0.6282 0.01735 0.01164 -0.0923 0.9712 0.0210
-9.000 -0.6012 0.01637 0.01060 -0.0929 0.9632 0.0225
-8.750 -0.5650 0.01552 0.00970 -0.0952 0.9597 0.0253
-8.500 -0.5369 0.01459 0.00875 -0.0958 0.9515 0.0301
-8.250 -0.5036 0.01337 0.00764 -0.0978 0.9464 0.0487
-8.000 -0.4754 0.01249 0.00689 -0.0983 0.9375 0.0728
-7.750 -0.4395 0.01177 0.00626 -0.1003 0.9318 0.0957
-7.500 -0.4042 0.01116 0.00574 -0.1021 0.9231 0.1180
-7.250 -0.3602 0.01062 0.00527 -0.1057 0.9162 0.1411
-7.000 -0.3177 0.01022 0.00489 -0.1088 0.9051 0.1617
-6.750 -0.2746 0.00992 0.00455 -0.1120 0.8913 0.1798
-6.500 -0.2370 0.00967 0.00429 -0.1140 0.8732 0.1983
-6.250 -0.2044 0.00953 0.00410 -0.1149 0.8534 0.2154
-6.000 -0.1748 0.00947 0.00395 -0.1151 0.8335 0.2298
-5.750 -0.1468 0.00943 0.00383 -0.1150 0.8141 0.2414
-5.500 -0.1197 0.00938 0.00370 -0.1147 0.7961 0.2513
-5.250 -0.0925 0.00939 0.00358 -0.1144 0.7790 0.2600
-5.000 -0.0660 0.00932 0.00347 -0.1140 0.7626 0.2685
-4.750 -0.0390 0.00934 0.00336 -0.1136 0.7468 0.2768
-4.500 -0.0124 0.00929 0.00327 -0.1133 0.7322 0.2848
-4.250 0.0146 0.00932 0.00318 -0.1129 0.7180 0.2928
-4.000 0.0412 0.00927 0.00309 -0.1125 0.7038 0.3004
-3.750 0.0683 0.00928 0.00303 -0.1122 0.6900 0.3083
-3.500 0.0953 0.00927 0.00295 -0.1119 0.6773 0.3157
-3.250 0.1221 0.00928 0.00290 -0.1115 0.6649 0.3232
-3.000 0.1494 0.00930 0.00284 -0.1112 0.6521 0.3304
-2.750 0.1764 0.00928 0.00280 -0.1110 0.6401 0.3379
-2.500 0.2036 0.00934 0.00276 -0.1106 0.6288 0.3453
-2.250 0.2307 0.00931 0.00273 -0.1104 0.6173 0.3523
-2.000 0.2580 0.00935 0.00271 -0.1101 0.6063 0.3600
-1.750 0.2849 0.00939 0.00268 -0.1098 0.5954 0.3670
-1.500 0.3123 0.00938 0.00267 -0.1096 0.5850 0.3743
-1.250 0.3396 0.00947 0.00267 -0.1093 0.5752 0.3818
-1.000 0.3668 0.00945 0.00266 -0.1091 0.5649 0.3891
-0.750 0.3940 0.00951 0.00267 -0.1088 0.5554 0.3967
-0.500 0.4212 0.00954 0.00268 -0.1086 0.5458 0.4044
-0.250 0.4484 0.00958 0.00271 -0.1083 0.5372 0.4123
0.000 0.4757 0.00965 0.00272 -0.1081 0.5281 0.4198
0.250 0.5027 0.00967 0.00276 -0.1078 0.5196 0.4282
0.500 0.5299 0.00975 0.00279 -0.1076 0.5108 0.4367
0.750 0.5569 0.00979 0.00285 -0.1073 0.5032 0.4450
1.000 0.5841 0.00985 0.00290 -0.1071 0.4951 0.4542
1.250 0.6107 0.00993 0.00296 -0.1068 0.4876 0.4635
1.500 0.6382 0.00998 0.00302 -0.1066 0.4799 0.4735
1.750 0.6646 0.01006 0.00310 -0.1063 0.4726 0.4835
2.000 0.6919 0.01011 0.00319 -0.1061 0.4660 0.4949
2.250 0.7187 0.01018 0.00327 -0.1058 0.4591 0.5070
2.500 0.7451 0.01028 0.00338 -0.1055 0.4526 0.5195
2.750 0.7722 0.01032 0.00348 -0.1052 0.4460 0.5339
3.000 0.7985 0.01042 0.00359 -0.1049 0.4397 0.5504
3.250 0.8250 0.01050 0.00373 -0.1046 0.4340 0.5687
3.500 0.8517 0.01054 0.00386 -0.1043 0.4279 0.5900
3.750 0.8774 0.01065 0.00400 -0.1039 0.4219 0.6155
4.000 0.9035 0.01071 0.00417 -0.1035 0.4164 0.6454
4.250 0.9295 0.01074 0.00433 -0.1030 0.4109 0.6808
4.500 0.9542 0.01081 0.00450 -0.1024 0.4054 0.7247
4.750 0.9780 0.01084 0.00471 -0.1015 0.4002 0.7799
5.000 0.9990 0.01077 0.00488 -0.0998 0.3951 0.8537
5.250 1.0266 0.01073 0.00497 -0.0995 0.3896 1.0000
5.500 1.0523 0.01096 0.00516 -0.0992 0.3843 1.0000
5.750 1.0787 0.01109 0.00532 -0.0989 0.3791 1.0000
6.000 1.1041 0.01129 0.00549 -0.0985 0.3737 1.0000
6.250 1.1289 0.01157 0.00572 -0.0979 0.3685 1.0000
6.500 1.1547 0.01170 0.00590 -0.0976 0.3636 1.0000
6.750 1.1797 0.01189 0.00609 -0.0970 0.3583 1.0000
7.000 1.2036 0.01217 0.00633 -0.0964 0.3530 1.0000
7.250 1.2285 0.01234 0.00655 -0.0958 0.3479 1.0000
7.500 1.2528 0.01253 0.00675 -0.0952 0.3423 1.0000
7.750 1.2754 0.01282 0.00701 -0.0943 0.3366 1.0000
8.000 1.2995 0.01301 0.00725 -0.0937 0.3314 1.0000
8.250 1.3226 0.01321 0.00748 -0.0928 0.3255 1.0000
8.500 1.3438 0.01354 0.00777 -0.0917 0.3197 1.0000
8.750 1.3668 0.01372 0.00802 -0.0909 0.3142 1.0000
9.000 1.3874 0.01396 0.00828 -0.0896 0.3081 1.0000
9.250 1.4058 0.01428 0.00859 -0.0880 0.3015 1.0000
9.500 1.4259 0.01449 0.00885 -0.0867 0.2938 1.0000
9.750 1.4422 0.01488 0.00921 -0.0847 0.2866 1.0000
10.000 1.4627 0.01512 0.00952 -0.0835 0.2791 1.0000
10.250 1.4777 0.01556 0.00992 -0.0815 0.2707 1.0000
10.500 1.4968 0.01587 0.01029 -0.0801 0.2623 1.0000
10.750 1.5116 0.01635 0.01075 -0.0781 0.2533 1.0000
11.000 1.5273 0.01680 0.01122 -0.0764 0.2438 1.0000
11.250 1.5416 0.01733 0.01176 -0.0744 0.2340 1.0000
11.500 1.5527 0.01801 0.01241 -0.0722 0.2223 1.0000
11.750 1.5622 0.01880 0.01316 -0.0698 0.2099 1.0000
12.000 1.5715 0.01963 0.01398 -0.0675 0.1969 1.0000
12.250 1.5787 0.02061 0.01494 -0.0651 0.1842 1.0000
12.500 1.5843 0.02174 0.01605 -0.0627 0.1723 1.0000
12.750 1.5877 0.02305 0.01735 -0.0603 0.1608 1.0000
13.000 1.5892 0.02459 0.01886 -0.0579 0.1496 1.0000
13.250 1.5893 0.02633 0.02059 -0.0557 0.1387 1.0000
13.500 1.5902 0.02814 0.02240 -0.0539 0.1284 1.0000
13.750 1.5892 0.03022 0.02449 -0.0522 0.1193 1.0000
14.000 1.5855 0.03265 0.02692 -0.0507 0.1108 1.0000
14.250 1.5821 0.03521 0.02950 -0.0495 0.1023 1.0000
14.500 1.5785 0.03794 0.03226 -0.0486 0.0952 1.0000
14.750 1.5709 0.04120 0.03554 -0.0479 0.0882 1.0000
15.000 1.5666 0.04427 0.03866 -0.0475 0.0821 1.0000
15.250 1.5577 0.04798 0.04240 -0.0473 0.0768 1.0000
15.500 1.5517 0.05148 0.04597 -0.0473 0.0713 1.0000
15.750 1.5408 0.05572 0.05024 -0.0475 0.0667 1.0000
16.000 1.5341 0.05958 0.05418 -0.0480 0.0621 1.0000
16.250 1.5224 0.06421 0.05885 -0.0487 0.0582 1.0000
16.500 1.5143 0.06850 0.06321 -0.0495 0.0540 1.0000
16.750 1.5018 0.07351 0.06827 -0.0506 0.0505 1.0000
17.000 1.4927 0.07817 0.07301 -0.0518 0.0468 1.0000
17.250 1.4799 0.08347 0.07836 -0.0533 0.0434 1.0000
17.500 1.4696 0.08852 0.08348 -0.0548 0.0398 1.0000
17.750 1.4567 0.09407 0.08909 -0.0566 0.0369 1.0000
18.000 1.4460 0.09936 0.09446 -0.0584 0.0335 1.0000
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