EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 558 AIRFOIL (e558-il) Reynolds number: 200,000 Max Cl/Cd: 67.65 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e558-il-200000.txt Download as CSV file: xf-e558-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.5513 0.11030 0.10624 -0.0490 1.0000 0.0297
-14.500 -0.5824 0.10001 0.09586 -0.0543 1.0000 0.0291
-14.250 -0.6256 0.08809 0.08375 -0.0617 1.0000 0.0288
-14.000 -0.6507 0.08049 0.07601 -0.0663 1.0000 0.0282
-13.750 -0.6785 0.07309 0.06845 -0.0708 1.0000 0.0280
-13.500 -0.7017 0.06683 0.06201 -0.0746 1.0000 0.0279
-13.250 -0.7207 0.06149 0.05649 -0.0775 1.0000 0.0276
-13.000 -0.7361 0.05689 0.05173 -0.0797 1.0000 0.0276
-12.750 -0.7480 0.05298 0.04767 -0.0813 1.0000 0.0276
-12.500 -0.7580 0.04954 0.04410 -0.0824 1.0000 0.0278
-12.250 -0.7666 0.04651 0.04094 -0.0828 1.0000 0.0279
-12.000 -0.7753 0.04385 0.03816 -0.0828 1.0000 0.0282
-11.750 -0.7871 0.04144 0.03562 -0.0820 1.0000 0.0286
-11.500 -0.8010 0.03955 0.03363 -0.0798 1.0000 0.0287
-11.250 -0.8105 0.03775 0.03170 -0.0776 1.0000 0.0290
-11.000 -0.8123 0.03610 0.02991 -0.0755 1.0000 0.0293
-10.750 -0.8123 0.03464 0.02826 -0.0733 1.0000 0.0297
-10.500 -0.8058 0.03297 0.02666 -0.0711 1.0000 0.0304
-10.250 -0.7998 0.03171 0.02542 -0.0690 1.0000 0.0309
-10.000 -0.7936 0.03053 0.02424 -0.0669 1.0000 0.0316
-9.750 -0.7867 0.02941 0.02306 -0.0649 1.0000 0.0325
-9.500 -0.7787 0.02834 0.02193 -0.0630 1.0000 0.0333
-9.250 -0.7556 0.02716 0.02060 -0.0637 0.9977 0.0347
-9.000 -0.7184 0.02545 0.01898 -0.0676 0.9924 0.0369
-8.750 -0.6796 0.02414 0.01756 -0.0711 0.9860 0.0405
-8.500 -0.6421 0.02260 0.01603 -0.0748 0.9798 0.0464
-8.250 -0.6050 0.02077 0.01427 -0.0786 0.9732 0.0584
-8.000 -0.5704 0.01895 0.01260 -0.0816 0.9656 0.0875
-7.750 -0.5302 0.01783 0.01159 -0.0851 0.9599 0.1236
-7.500 -0.4946 0.01716 0.01096 -0.0872 0.9513 0.1507
-7.250 -0.4521 0.01664 0.01046 -0.0904 0.9461 0.1761
-7.000 -0.4167 0.01628 0.01007 -0.0921 0.9370 0.1979
-6.750 -0.3737 0.01600 0.00980 -0.0951 0.9319 0.2199
-6.500 -0.3373 0.01576 0.00951 -0.0966 0.9232 0.2371
-6.250 -0.2953 0.01546 0.00916 -0.0992 0.9174 0.2529
-6.000 -0.2539 0.01518 0.00883 -0.1016 0.9103 0.2672
-5.750 -0.2128 0.01489 0.00845 -0.1040 0.9016 0.2805
-5.500 -0.1716 0.01468 0.00814 -0.1064 0.8920 0.2931
-5.250 -0.1290 0.01439 0.00786 -0.1090 0.8819 0.3041
-5.000 -0.0924 0.01418 0.00753 -0.1105 0.8677 0.3148
-4.750 -0.0566 0.01406 0.00733 -0.1118 0.8530 0.3249
-4.500 -0.0229 0.01391 0.00710 -0.1127 0.8377 0.3341
-4.250 0.0088 0.01386 0.00692 -0.1132 0.8220 0.3438
-4.000 0.0389 0.01376 0.00673 -0.1134 0.8065 0.3520
-3.750 0.0684 0.01375 0.00658 -0.1134 0.7915 0.3611
-3.500 0.0954 0.01368 0.00643 -0.1130 0.7757 0.3690
-3.250 0.1225 0.01367 0.00635 -0.1126 0.7605 0.3775
-3.000 0.1497 0.01362 0.00619 -0.1123 0.7462 0.3856
-2.750 0.1771 0.01362 0.00612 -0.1119 0.7327 0.3938
-2.500 0.2049 0.01361 0.00595 -0.1117 0.7198 0.4024
-2.250 0.2309 0.01357 0.00591 -0.1112 0.7060 0.4100
-2.000 0.2580 0.01360 0.00581 -0.1109 0.6932 0.4192
-1.750 0.2850 0.01356 0.00575 -0.1105 0.6815 0.4267
-1.500 0.3118 0.01359 0.00567 -0.1101 0.6690 0.4361
-1.250 0.3382 0.01356 0.00565 -0.1097 0.6572 0.4441
-1.000 0.3658 0.01362 0.00558 -0.1095 0.6468 0.4536
-0.750 0.3918 0.01358 0.00556 -0.1090 0.6350 0.4618
-0.500 0.4188 0.01365 0.00555 -0.1087 0.6244 0.4720
-0.250 0.4457 0.01365 0.00553 -0.1083 0.6143 0.4808
0.000 0.4723 0.01371 0.00555 -0.1080 0.6039 0.4914
0.250 0.4996 0.01376 0.00556 -0.1077 0.5949 0.5010
0.500 0.5257 0.01379 0.00560 -0.1073 0.5844 0.5122
0.750 0.5531 0.01387 0.00564 -0.1071 0.5761 0.5229
1.000 0.5789 0.01389 0.00572 -0.1066 0.5664 0.5344
1.250 0.6067 0.01402 0.00576 -0.1065 0.5586 0.5477
1.500 0.6320 0.01403 0.00588 -0.1059 0.5491 0.5600
1.750 0.6595 0.01414 0.00595 -0.1057 0.5417 0.5742
2.000 0.6849 0.01418 0.00610 -0.1052 0.5332 0.5896
2.250 0.7118 0.01427 0.00619 -0.1049 0.5259 0.6067
2.500 0.7375 0.01436 0.00637 -0.1044 0.5181 0.6256
2.750 0.7633 0.01442 0.00650 -0.1039 0.5106 0.6475
3.000 0.7896 0.01455 0.00668 -0.1035 0.5041 0.6739
3.250 0.8138 0.01458 0.00689 -0.1026 0.4968 0.7040
3.500 0.8386 0.01465 0.00705 -0.1018 0.4906 0.7432
3.750 0.8597 0.01468 0.00728 -0.1002 0.4840 0.7942
4.000 0.8784 0.01460 0.00741 -0.0978 0.4776 0.8729
4.250 0.9157 0.01471 0.00749 -0.0996 0.4716 1.0000
4.500 0.9414 0.01494 0.00775 -0.0994 0.4647 1.0000
4.750 0.9686 0.01518 0.00794 -0.0993 0.4584 1.0000
5.000 0.9968 0.01553 0.00819 -0.0995 0.4529 1.0000
5.250 1.0216 0.01578 0.00850 -0.0990 0.4465 1.0000
5.500 1.0483 0.01604 0.00872 -0.0989 0.4406 1.0000
5.750 1.0755 0.01640 0.00903 -0.0988 0.4352 1.0000
6.000 1.0995 0.01667 0.00937 -0.0982 0.4288 1.0000
6.250 1.1259 0.01695 0.00962 -0.0980 0.4232 1.0000
6.500 1.1523 0.01733 0.00997 -0.0978 0.4178 1.0000
6.750 1.1756 0.01761 0.01034 -0.0970 0.4116 1.0000
7.000 1.2014 0.01790 0.01061 -0.0967 0.4060 1.0000
7.250 1.2273 0.01830 0.01100 -0.0964 0.4007 1.0000
7.500 1.2493 0.01859 0.01140 -0.0955 0.3944 1.0000
7.750 1.2746 0.01889 0.01168 -0.0950 0.3888 1.0000
8.000 1.2990 0.01929 0.01210 -0.0945 0.3831 1.0000
8.250 1.3200 0.01959 0.01250 -0.0934 0.3766 1.0000
8.500 1.3449 0.01988 0.01276 -0.0929 0.3708 1.0000
8.750 1.3659 0.02027 0.01324 -0.0918 0.3645 1.0000
9.000 1.3866 0.02055 0.01359 -0.0907 0.3579 1.0000
9.250 1.4126 0.02094 0.01389 -0.0905 0.3519 1.0000
9.500 1.4277 0.02126 0.01441 -0.0883 0.3451 1.0000
9.750 1.4481 0.02153 0.01470 -0.0871 0.3385 1.0000
10.000 1.4666 0.02193 0.01516 -0.0857 0.3318 1.0000
10.250 1.4820 0.02222 0.01555 -0.0837 0.3243 1.0000
10.500 1.5000 0.02258 0.01589 -0.0821 0.3172 1.0000
10.750 1.5101 0.02292 0.01638 -0.0793 0.3094 1.0000
11.000 1.5260 0.02330 0.01670 -0.0774 0.3024 1.0000
11.250 1.5309 0.02375 0.01735 -0.0738 0.2949 1.0000
11.500 1.5424 0.02421 0.01777 -0.0714 0.2876 1.0000
11.750 1.5472 0.02482 0.01855 -0.0681 0.2795 1.0000
12.000 1.5547 0.02544 0.01912 -0.0654 0.2712 1.0000
12.250 1.5569 0.02625 0.02011 -0.0622 0.2620 1.0000
12.500 1.5600 0.02718 0.02104 -0.0594 0.2528 1.0000
12.750 1.5603 0.02832 0.02226 -0.0567 0.2423 1.0000
13.000 1.5606 0.02967 0.02369 -0.0542 0.2315 1.0000
13.250 1.5591 0.03129 0.02533 -0.0520 0.2209 1.0000
13.500 1.5557 0.03322 0.02726 -0.0500 0.2103 1.0000
13.750 1.5535 0.03529 0.02943 -0.0484 0.1992 1.0000
14.000 1.5492 0.03771 0.03188 -0.0471 0.1889 1.0000
14.250 1.5416 0.04056 0.03473 -0.0459 0.1791 1.0000
14.500 1.5349 0.04356 0.03778 -0.0451 0.1691 1.0000
14.750 1.5269 0.04686 0.04113 -0.0446 0.1595 1.0000
15.000 1.5152 0.05069 0.04496 -0.0444 0.1510 1.0000
15.250 1.5060 0.05451 0.04885 -0.0445 0.1419 1.0000
15.500 1.4953 0.05863 0.05302 -0.0448 0.1341 1.0000
15.750 1.4826 0.06316 0.05756 -0.0454 0.1265 1.0000
16.000 1.4725 0.06757 0.06204 -0.0462 0.1190 1.0000
16.250 1.4585 0.07258 0.06705 -0.0472 0.1126 1.0000
16.500 1.4492 0.07719 0.07175 -0.0484 0.1055 1.0000
16.750 1.4354 0.08245 0.07699 -0.0498 0.0999 1.0000
17.000 1.4268 0.08719 0.08184 -0.0512 0.0934 1.0000
17.250 1.4138 0.09256 0.08718 -0.0529 0.0881 1.0000
17.500 1.4054 0.09749 0.09222 -0.0546 0.0821 1.0000
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Polar data table (+)
Polar graphs
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