EPPLER 555 AIRFOIL (e555-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 555 AIRFOIL (e555-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.71 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e555-il-1000000.txt Download as CSV file: xf-e555-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 555 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7006 0.11734 0.11511 -0.0382 1.0000 0.0059
-16.500 -0.7301 0.10677 0.10438 -0.0437 1.0000 0.0058
-16.250 -0.7622 0.09650 0.09393 -0.0489 1.0000 0.0057
-16.000 -0.7768 0.08997 0.08728 -0.0523 1.0000 0.0057
-15.750 -0.7919 0.08371 0.08089 -0.0554 1.0000 0.0057
-15.500 -0.8080 0.07755 0.07459 -0.0582 1.0000 0.0056
-15.250 -0.8194 0.07243 0.06935 -0.0605 1.0000 0.0056
-15.000 -0.8340 0.06711 0.06388 -0.0626 1.0000 0.0055
-14.750 -0.8448 0.06256 0.05919 -0.0642 1.0000 0.0055
-14.500 -0.8501 0.05894 0.05546 -0.0654 1.0000 0.0055
-14.250 -0.8560 0.05537 0.05178 -0.0663 1.0000 0.0055
-14.000 -0.8604 0.05217 0.04847 -0.0670 1.0000 0.0055
-13.750 -0.8653 0.04912 0.04532 -0.0673 1.0000 0.0055
-13.500 -0.8646 0.04679 0.04291 -0.0675 1.0000 0.0055
-13.250 -0.8672 0.04422 0.04025 -0.0674 1.0000 0.0056
-13.000 -0.8657 0.04215 0.03811 -0.0673 1.0000 0.0056
-12.750 -0.8686 0.03980 0.03566 -0.0665 1.0000 0.0056
-12.500 -0.8681 0.03786 0.03365 -0.0658 1.0000 0.0056
-12.250 -0.8690 0.03594 0.03165 -0.0647 1.0000 0.0056
-12.000 -0.8692 0.03421 0.02987 -0.0635 1.0000 0.0057
-11.750 -0.8728 0.03243 0.02803 -0.0617 1.0000 0.0057
-11.500 -0.8768 0.03090 0.02644 -0.0595 1.0000 0.0057
-11.250 -0.8720 0.02924 0.02472 -0.0592 0.9993 0.0057
-11.000 -0.8498 0.02724 0.02264 -0.0624 0.9967 0.0057
-10.750 -0.8255 0.02533 0.02064 -0.0660 0.9940 0.0057
-10.500 -0.8062 0.02343 0.01866 -0.0687 0.9891 0.0058
-10.250 -0.7771 0.02149 0.01663 -0.0731 0.9855 0.0058
-10.000 -0.7428 0.01970 0.01475 -0.0782 0.9834 0.0059
-9.750 -0.7209 0.01841 0.01339 -0.0793 0.9764 0.0059
-9.500 -0.6895 0.01729 0.01220 -0.0819 0.9736 0.0060
-9.250 -0.6625 0.01637 0.01122 -0.0831 0.9687 0.0061
-9.000 -0.6343 0.01533 0.01011 -0.0847 0.9637 0.0063
-8.750 -0.6029 0.01416 0.00887 -0.0870 0.9607 0.0067
-8.500 -0.5757 0.01347 0.00814 -0.0877 0.9544 0.0069
-8.250 -0.5431 0.01284 0.00747 -0.0893 0.9498 0.0076
-8.000 -0.5056 0.01218 0.00675 -0.0920 0.9470 0.0086
-7.750 -0.4704 0.01154 0.00609 -0.0943 0.9410 0.0112
-7.500 -0.4300 0.01087 0.00545 -0.0977 0.9358 0.0186
-7.250 -0.3858 0.01028 0.00491 -0.1018 0.9311 0.0316
-7.000 -0.3495 0.00979 0.00447 -0.1042 0.9205 0.0469
-6.750 -0.3141 0.00928 0.00404 -0.1064 0.9091 0.0705
-6.500 -0.2822 0.00877 0.00362 -0.1079 0.8960 0.1038
-6.250 -0.2535 0.00818 0.00318 -0.1088 0.8828 0.1553
-6.000 -0.2285 0.00711 0.00253 -0.1094 0.8695 0.2675
-5.750 -0.2023 0.00655 0.00225 -0.1097 0.8570 0.3520
-5.500 -0.1744 0.00644 0.00217 -0.1098 0.8452 0.3816
-5.250 -0.1463 0.00643 0.00211 -0.1098 0.8331 0.3966
-4.750 -0.0905 0.00644 0.00199 -0.1097 0.8086 0.4120
-4.500 -0.0625 0.00646 0.00194 -0.1097 0.7971 0.4203
-4.250 -0.0346 0.00649 0.00191 -0.1096 0.7858 0.4261
-4.000 -0.0066 0.00656 0.00188 -0.1096 0.7743 0.4312
-3.750 0.0213 0.00657 0.00189 -0.1095 0.7633 0.4398
-3.500 0.0494 0.00668 0.00190 -0.1095 0.7525 0.4461
-3.250 0.0772 0.00668 0.00184 -0.1094 0.7413 0.4488
-3.000 0.1052 0.00666 0.00178 -0.1094 0.7307 0.4517
-2.750 0.1330 0.00668 0.00175 -0.1094 0.7201 0.4542
-2.500 0.1610 0.00670 0.00172 -0.1093 0.7095 0.4566
-2.250 0.1892 0.00673 0.00170 -0.1094 0.6993 0.4590
-2.000 0.2170 0.00677 0.00167 -0.1093 0.6892 0.4612
-1.750 0.2452 0.00681 0.00165 -0.1093 0.6789 0.4631
-1.500 0.2731 0.00680 0.00162 -0.1093 0.6693 0.4662
-1.000 0.3290 0.00685 0.00161 -0.1093 0.6492 0.4713
-0.750 0.3569 0.00690 0.00162 -0.1093 0.6396 0.4737
-0.500 0.3848 0.00695 0.00163 -0.1093 0.6292 0.4761
-0.250 0.4129 0.00700 0.00164 -0.1093 0.6197 0.4783
0.000 0.4405 0.00706 0.00165 -0.1092 0.6098 0.4808
0.250 0.4685 0.00707 0.00166 -0.1093 0.5998 0.4840
0.500 0.4963 0.00712 0.00170 -0.1092 0.5900 0.4867
0.750 0.5238 0.00719 0.00173 -0.1091 0.5797 0.4893
1.000 0.5517 0.00725 0.00177 -0.1091 0.5695 0.4919
1.250 0.5792 0.00734 0.00181 -0.1090 0.5593 0.4943
1.500 0.6066 0.00741 0.00186 -0.1089 0.5481 0.4969
1.750 0.6342 0.00746 0.00191 -0.1089 0.5373 0.5004
2.000 0.6615 0.00754 0.00197 -0.1088 0.5265 0.5035
2.250 0.6886 0.00764 0.00204 -0.1086 0.5152 0.5065
2.500 0.7161 0.00773 0.00211 -0.1086 0.5043 0.5094
2.750 0.7432 0.00784 0.00219 -0.1084 0.4933 0.5118
3.000 0.7699 0.00794 0.00227 -0.1082 0.4815 0.5154
3.250 0.7970 0.00803 0.00237 -0.1081 0.4698 0.5190
3.500 0.8239 0.00814 0.00247 -0.1079 0.4585 0.5227
3.750 0.8505 0.00828 0.00258 -0.1077 0.4469 0.5261
4.250 0.9035 0.00853 0.00281 -0.1072 0.4227 0.5334
4.500 0.9299 0.00867 0.00294 -0.1070 0.4111 0.5373
4.750 0.9558 0.00883 0.00308 -0.1066 0.3983 0.5415
5.000 0.9814 0.00902 0.00324 -0.1063 0.3854 0.5453
5.250 1.0071 0.00918 0.00340 -0.1059 0.3720 0.5503
5.500 1.0325 0.00937 0.00357 -0.1055 0.3577 0.5552
5.750 1.0578 0.00957 0.00375 -0.1051 0.3439 0.5599
6.000 1.0827 0.00978 0.00394 -0.1046 0.3296 0.5649
6.250 1.1072 0.01001 0.00415 -0.1040 0.3146 0.5705
6.500 1.1310 0.01028 0.00438 -0.1034 0.2974 0.5763
6.750 1.1541 0.01058 0.00463 -0.1026 0.2791 0.5826
7.000 1.1769 0.01090 0.00491 -0.1018 0.2606 0.5896
7.250 1.1988 0.01127 0.00521 -0.1008 0.2389 0.5963
7.500 1.2191 0.01172 0.00557 -0.0996 0.2159 0.6038
7.750 1.2396 0.01214 0.00592 -0.0984 0.1955 0.6115
8.000 1.2594 0.01257 0.00631 -0.0971 0.1765 0.6201
8.250 1.2790 0.01301 0.00670 -0.0958 0.1603 0.6291
8.500 1.2975 0.01348 0.00712 -0.0943 0.1442 0.6396
9.250 1.3452 0.01486 0.00843 -0.0883 0.1039 0.6749
9.500 1.3607 0.01534 0.00891 -0.0863 0.0935 0.6889
9.750 1.3758 0.01583 0.00942 -0.0843 0.0838 0.7043
10.000 1.3900 0.01636 0.00996 -0.0822 0.0754 0.7219
10.500 1.4167 0.01748 0.01117 -0.0779 0.0605 0.7684
10.750 1.4286 0.01807 0.01184 -0.0756 0.0540 0.8021
11.000 1.4380 0.01865 0.01256 -0.0728 0.0486 0.8604
11.250 1.4445 0.01910 0.01319 -0.0695 0.0438 1.0000
11.500 1.4541 0.01997 0.01404 -0.0673 0.0388 1.0000
11.750 1.4645 0.02083 0.01490 -0.0652 0.0347 1.0000
12.000 1.4741 0.02176 0.01585 -0.0632 0.0314 1.0000
12.250 1.4823 0.02282 0.01690 -0.0611 0.0279 1.0000
12.500 1.4914 0.02387 0.01798 -0.0593 0.0254 1.0000
12.750 1.4992 0.02505 0.01918 -0.0575 0.0232 1.0000
13.000 1.5067 0.02631 0.02048 -0.0558 0.0213 1.0000
13.250 1.5144 0.02761 0.02181 -0.0543 0.0198 1.0000
13.500 1.5191 0.02919 0.02342 -0.0526 0.0181 1.0000
13.750 1.5262 0.03066 0.02495 -0.0514 0.0169 1.0000
14.000 1.5317 0.03232 0.02666 -0.0501 0.0157 1.0000
14.250 1.5344 0.03429 0.02867 -0.0489 0.0145 1.0000
14.500 1.5400 0.03609 0.03055 -0.0480 0.0138 1.0000
14.750 1.5441 0.03810 0.03262 -0.0472 0.0129 1.0000
15.000 1.5461 0.04037 0.03495 -0.0465 0.0122 1.0000
15.250 1.5459 0.04299 0.03762 -0.0459 0.0114 1.0000
15.500 1.5495 0.04531 0.04002 -0.0456 0.0109 1.0000
15.750 1.5512 0.04789 0.04268 -0.0454 0.0104 1.0000
16.000 1.5513 0.05076 0.04562 -0.0453 0.0099 1.0000
16.250 1.5493 0.05400 0.04894 -0.0455 0.0094 1.0000
16.500 1.5459 0.05752 0.05255 -0.0458 0.0089 1.0000
16.750 1.5458 0.06073 0.05585 -0.0463 0.0086 1.0000
17.000 1.5445 0.06420 0.05941 -0.0470 0.0083 1.0000
17.250 1.5412 0.06804 0.06334 -0.0479 0.0080 1.0000
17.500 1.5368 0.07216 0.06754 -0.0490 0.0076 1.0000
17.750 1.5304 0.07666 0.07213 -0.0504 0.0073 1.0000
18.000 1.5216 0.08169 0.07726 -0.0521 0.0070 1.0000
18.250 1.5146 0.08658 0.08225 -0.0539 0.0068 1.0000
18.500 1.5085 0.09139 0.08718 -0.0557 0.0066 1.0000
18.750 1.5021 0.09636 0.09225 -0.0578 0.0064 1.0000
19.000 1.4949 0.10155 0.09755 -0.0600 0.0062 1.0000
19.250 1.4859 0.10713 0.10324 -0.0626 0.0061 1.0000
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