EPPLER 556 AIRFOIL (e556-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 556 AIRFOIL (e556-il) Reynolds number: 200,000 Max Cl/Cd: 72.26 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e556-il-200000.txt Download as CSV file: xf-e556-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4937 0.10899 0.10520 -0.0528 1.0000 0.0267
-13.250 -0.5046 0.10195 0.09813 -0.0556 1.0000 0.0256
-13.000 -0.5336 0.09198 0.08809 -0.0610 1.0000 0.0250
-12.750 -0.5610 0.08371 0.07973 -0.0656 1.0000 0.0244
-12.500 -0.5920 0.07597 0.07185 -0.0698 1.0000 0.0240
-12.250 -0.6201 0.06946 0.06519 -0.0730 1.0000 0.0233
-12.000 -0.6930 0.05917 0.05432 -0.0778 1.0000 0.0217
-11.750 -0.7149 0.05554 0.05051 -0.0779 1.0000 0.0215
-11.500 -0.7330 0.05319 0.04800 -0.0770 1.0000 0.0213
-11.250 -0.7504 0.05132 0.04602 -0.0749 1.0000 0.0212
-11.000 -0.7699 0.04949 0.04410 -0.0716 1.0000 0.0211
-10.750 -0.7886 0.04765 0.04217 -0.0684 1.0000 0.0211
-10.500 -0.7982 0.04535 0.03975 -0.0659 1.0000 0.0210
-10.250 -0.8085 0.04331 0.03751 -0.0633 1.0000 0.0211
-10.000 -0.8120 0.04122 0.03523 -0.0610 1.0000 0.0211
-9.750 -0.8110 0.03923 0.03304 -0.0590 1.0000 0.0211
-9.500 -0.8076 0.03702 0.03062 -0.0572 1.0000 0.0213
-9.250 -0.7804 0.03426 0.02773 -0.0588 0.9970 0.0218
-9.000 -0.7470 0.03262 0.02605 -0.0616 0.9932 0.0230
-8.750 -0.7136 0.03131 0.02459 -0.0644 0.9882 0.0251
-8.500 -0.6787 0.02957 0.02263 -0.0667 0.9847 0.0266
-8.250 -0.6509 0.02795 0.02107 -0.0677 0.9792 0.0280
-8.000 -0.6161 0.02662 0.01972 -0.0701 0.9750 0.0302
-7.750 -0.5868 0.02507 0.01812 -0.0717 0.9689 0.0335
-7.500 -0.5507 0.02393 0.01696 -0.0747 0.9641 0.0392
-7.250 -0.5176 0.02228 0.01533 -0.0776 0.9586 0.0479
-7.000 -0.4838 0.02053 0.01366 -0.0810 0.9526 0.0624
-6.750 -0.4422 0.01890 0.01215 -0.0857 0.9494 0.0909
-6.500 -0.4088 0.01669 0.01046 -0.0897 0.9430 0.1765
-6.250 -0.3691 0.01526 0.00991 -0.0942 0.9385 0.3688
-6.000 -0.3256 0.01547 0.01001 -0.0970 0.9352 0.4071
-5.750 -0.2923 0.01571 0.01010 -0.0978 0.9279 0.4267
-5.500 -0.2532 0.01597 0.01026 -0.0996 0.9231 0.4426
-5.250 -0.2102 0.01622 0.01043 -0.1020 0.9204 0.4574
-5.000 -0.1787 0.01653 0.01081 -0.1020 0.9135 0.4663
-4.750 -0.1397 0.01652 0.01070 -0.1038 0.9088 0.4762
-4.500 -0.0963 0.01665 0.01081 -0.1063 0.9060 0.4856
-4.250 -0.0520 0.01690 0.01107 -0.1087 0.9036 0.4960
-4.000 -0.0218 0.01687 0.01090 -0.1092 0.8941 0.5057
-3.750 0.0198 0.01659 0.01062 -0.1115 0.8900 0.5092
-3.500 0.0533 0.01640 0.01037 -0.1125 0.8820 0.5127
-3.250 0.0925 0.01606 0.00992 -0.1148 0.8755 0.5171
-3.000 0.1286 0.01569 0.00936 -0.1168 0.8672 0.5222
-2.750 0.1639 0.01542 0.00906 -0.1181 0.8592 0.5247
-2.500 0.1944 0.01528 0.00887 -0.1186 0.8493 0.5277
-2.250 0.2308 0.01508 0.00858 -0.1202 0.8414 0.5317
-2.000 0.2595 0.01490 0.00829 -0.1205 0.8302 0.5358
-1.750 0.2914 0.01470 0.00796 -0.1214 0.8206 0.5392
-1.500 0.3220 0.01458 0.00781 -0.1218 0.8108 0.5420
-1.250 0.3492 0.01452 0.00773 -0.1216 0.7996 0.5454
-1.000 0.3798 0.01443 0.00756 -0.1221 0.7899 0.5493
-0.750 0.4099 0.01432 0.00732 -0.1227 0.7795 0.5535
-0.500 0.4370 0.01424 0.00721 -0.1225 0.7686 0.5564
-0.250 0.4660 0.01421 0.00715 -0.1226 0.7590 0.5596
0.000 0.4936 0.01419 0.00710 -0.1225 0.7483 0.5636
0.250 0.5214 0.01417 0.00702 -0.1226 0.7377 0.5679
0.500 0.5513 0.01412 0.00688 -0.1230 0.7283 0.5717
0.750 0.5775 0.01411 0.00689 -0.1226 0.7174 0.5747
1.000 0.6044 0.01413 0.00691 -0.1224 0.7070 0.5785
1.250 0.6342 0.01416 0.00685 -0.1227 0.6977 0.5834
1.500 0.6603 0.01417 0.00685 -0.1224 0.6864 0.5878
1.750 0.6868 0.01420 0.00690 -0.1221 0.6762 0.5913
2.000 0.7153 0.01425 0.00691 -0.1221 0.6666 0.5955
2.250 0.7412 0.01430 0.00697 -0.1218 0.6553 0.6003
2.500 0.7682 0.01435 0.00701 -0.1216 0.6450 0.6049
2.750 0.7956 0.01442 0.00708 -0.1214 0.6352 0.6093
3.000 0.8209 0.01449 0.00719 -0.1210 0.6237 0.6146
3.250 0.8478 0.01458 0.00725 -0.1208 0.6130 0.6199
3.500 0.8748 0.01466 0.00733 -0.1205 0.6029 0.6243
3.750 0.8993 0.01474 0.00747 -0.1199 0.5909 0.6298
4.000 0.9252 0.01486 0.00759 -0.1195 0.5795 0.6360
4.250 0.9507 0.01497 0.00773 -0.1190 0.5687 0.6414
4.500 0.9763 0.01509 0.00786 -0.1185 0.5573 0.6482
4.750 1.0004 0.01520 0.00804 -0.1178 0.5454 0.6541
5.000 1.0251 0.01535 0.00823 -0.1172 0.5339 0.6607
5.250 1.0506 0.01551 0.00838 -0.1168 0.5225 0.6683
5.500 1.0737 0.01564 0.00858 -0.1158 0.5102 0.6756
5.750 1.0970 0.01580 0.00881 -0.1150 0.4976 0.6842
6.000 1.1198 0.01597 0.00905 -0.1140 0.4852 0.6924
6.250 1.1428 0.01616 0.00927 -0.1131 0.4727 0.7015
6.500 1.1652 0.01637 0.00952 -0.1121 0.4601 0.7117
6.750 1.1861 0.01655 0.00979 -0.1108 0.4467 0.7221
7.000 1.2065 0.01676 0.01008 -0.1094 0.4327 0.7342
7.250 1.2264 0.01699 0.01039 -0.1079 0.4184 0.7477
7.500 1.2451 0.01723 0.01072 -0.1063 0.4035 0.7624
7.750 1.2625 0.01749 0.01106 -0.1044 0.3883 0.7788
8.000 1.2782 0.01775 0.01142 -0.1021 0.3727 0.7980
8.250 1.2923 0.01804 0.01179 -0.0996 0.3568 0.8230
8.500 1.3019 0.01829 0.01214 -0.0962 0.3407 0.8580
8.750 1.3044 0.01833 0.01232 -0.0913 0.3260 1.0000
9.000 1.3188 0.01896 0.01287 -0.0895 0.3072 1.0000
9.250 1.3312 0.01962 0.01348 -0.0873 0.2875 1.0000
9.500 1.3417 0.02037 0.01417 -0.0849 0.2673 1.0000
9.750 1.3496 0.02126 0.01498 -0.0822 0.2478 1.0000
10.000 1.3564 0.02226 0.01591 -0.0795 0.2292 1.0000
10.250 1.3632 0.02334 0.01695 -0.0769 0.2108 1.0000
10.500 1.3686 0.02454 0.01811 -0.0744 0.1942 1.0000
10.750 1.3733 0.02587 0.01939 -0.0719 0.1789 1.0000
11.000 1.3775 0.02730 0.02079 -0.0696 0.1650 1.0000
11.250 1.3809 0.02887 0.02233 -0.0674 0.1524 1.0000
11.500 1.3831 0.03060 0.02403 -0.0653 0.1408 1.0000
11.750 1.3843 0.03250 0.02590 -0.0634 0.1303 1.0000
12.000 1.3882 0.03430 0.02775 -0.0619 0.1199 1.0000
12.250 1.3898 0.03638 0.02986 -0.0604 0.1110 1.0000
12.500 1.3878 0.03883 0.03226 -0.0589 0.1033 1.0000
12.750 1.3915 0.04092 0.03446 -0.0579 0.0953 1.0000
13.000 1.3887 0.04368 0.03718 -0.0568 0.0890 1.0000
13.250 1.3914 0.04603 0.03965 -0.0561 0.0824 1.0000
13.500 1.3874 0.04912 0.04268 -0.0553 0.0774 1.0000
13.750 1.3901 0.05167 0.04539 -0.0550 0.0720 1.0000
14.000 1.3874 0.05483 0.04854 -0.0547 0.0677 1.0000
14.250 1.3875 0.05782 0.05163 -0.0544 0.0636 1.0000
14.500 1.3878 0.06088 0.05479 -0.0545 0.0598 1.0000
14.750 1.3850 0.06433 0.05819 -0.0545 0.0564 1.0000
15.000 1.3857 0.06752 0.06155 -0.0547 0.0534 1.0000
15.250 1.3856 0.07088 0.06502 -0.0552 0.0504 1.0000
15.500 1.3843 0.07442 0.06859 -0.0558 0.0480 1.0000
15.750 1.3847 0.07774 0.07194 -0.0559 0.0454 1.0000
16.000 1.3838 0.08146 0.07584 -0.0568 0.0432 1.0000
16.250 1.3830 0.08519 0.07967 -0.0578 0.0411 1.0000
16.500 1.3821 0.08892 0.08342 -0.0588 0.0392 1.0000
16.750 1.3837 0.09222 0.08676 -0.0592 0.0372 1.0000
17.000 1.3806 0.09657 0.09132 -0.0607 0.0358 1.0000
17.250 1.3781 0.10081 0.09570 -0.0623 0.0343 1.0000
17.500 1.3769 0.10481 0.09977 -0.0638 0.0328 1.0000
17.750 1.3785 0.10821 0.10317 -0.0649 0.0313 1.0000
18.000 1.3757 0.11254 0.10765 -0.0664 0.0302 1.0000
18.250 1.3695 0.11769 0.11301 -0.0689 0.0293 1.0000
18.500 1.3634 0.12286 0.11836 -0.0715 0.0283 1.0000
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Polar data table (+)
Polar graphs
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