EPPLER 556 AIRFOIL (e556-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 556 AIRFOIL (e556-il) Reynolds number: 500,000 Max Cl/Cd: 90.8 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e556-il-500000-n5.txt Download as CSV file: xf-e556-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -0.5146 0.19988 0.19721 -0.0118 1.0000 0.0058
-17.500 -0.6778 0.13121 0.12814 -0.0368 1.0000 0.0044
-17.250 -0.7045 0.12113 0.11789 -0.0414 1.0000 0.0043
-17.000 -0.7251 0.11277 0.10941 -0.0454 1.0000 0.0044
-16.750 -0.7412 0.10562 0.10213 -0.0488 1.0000 0.0043
-16.500 -0.7558 0.09900 0.09538 -0.0519 1.0000 0.0043
-16.250 -0.7700 0.09267 0.08894 -0.0549 1.0000 0.0044
-16.000 -0.7792 0.08746 0.08362 -0.0573 1.0000 0.0043
-15.750 -0.7896 0.08222 0.07828 -0.0596 1.0000 0.0043
-15.500 -0.7977 0.07753 0.07348 -0.0616 1.0000 0.0043
-15.250 -0.8046 0.07319 0.06904 -0.0634 1.0000 0.0043
-15.000 -0.8126 0.06884 0.06459 -0.0651 1.0000 0.0044
-14.750 -0.8167 0.06519 0.06086 -0.0664 1.0000 0.0044
-14.500 -0.8213 0.06159 0.05718 -0.0676 1.0000 0.0045
-14.250 -0.8245 0.05836 0.05387 -0.0684 1.0000 0.0044
-14.000 -0.8276 0.05526 0.05070 -0.0692 1.0000 0.0046
-13.750 -0.8302 0.05238 0.04774 -0.0697 1.0000 0.0046
-13.500 -0.8331 0.04971 0.04499 -0.0699 1.0000 0.0046
-13.250 -0.8354 0.04725 0.04246 -0.0698 1.0000 0.0046
-13.000 -0.8378 0.04490 0.04006 -0.0696 1.0000 0.0048
-12.750 -0.8413 0.04260 0.03769 -0.0690 1.0000 0.0048
-12.500 -0.8454 0.04041 0.03544 -0.0682 1.0000 0.0049
-12.250 -0.8487 0.03847 0.03345 -0.0671 1.0000 0.0049
-12.000 -0.8492 0.03647 0.03139 -0.0667 0.9996 0.0049
-11.750 -0.8313 0.03422 0.02905 -0.0699 0.9972 0.0051
-11.500 -0.8123 0.03207 0.02680 -0.0732 0.9943 0.0052
-11.250 -0.7950 0.03012 0.02477 -0.0756 0.9903 0.0054
-11.000 -0.7762 0.02811 0.02268 -0.0785 0.9858 0.0055
-10.750 -0.7628 0.02629 0.02077 -0.0801 0.9785 0.0057
-10.500 -0.7430 0.02448 0.01888 -0.0826 0.9720 0.0058
-10.250 -0.7225 0.02240 0.01672 -0.0858 0.9640 0.0061
-10.000 -0.6980 0.02081 0.01504 -0.0886 0.9574 0.0063
-9.750 -0.6715 0.01965 0.01380 -0.0906 0.9517 0.0066
-9.500 -0.6407 0.01861 0.01269 -0.0930 0.9484 0.0071
-9.250 -0.6158 0.01775 0.01176 -0.0939 0.9407 0.0075
-9.000 -0.5834 0.01688 0.01083 -0.0961 0.9365 0.0082
-8.750 -0.5497 0.01608 0.00997 -0.0985 0.9324 0.0091
-8.500 -0.5175 0.01540 0.00924 -0.1004 0.9259 0.0104
-8.250 -0.4794 0.01469 0.00851 -0.1035 0.9214 0.0127
-8.000 -0.4404 0.01406 0.00785 -0.1067 0.9163 0.0164
-7.750 -0.4015 0.01348 0.00725 -0.1098 0.9093 0.0215
-7.500 -0.3608 0.01289 0.00665 -0.1133 0.9027 0.0284
-7.250 -0.3254 0.01239 0.00614 -0.1155 0.8927 0.0366
-7.000 -0.2905 0.01193 0.00566 -0.1176 0.8826 0.0471
-6.750 -0.2571 0.01145 0.00520 -0.1194 0.8716 0.0637
-6.500 -0.2275 0.01091 0.00474 -0.1205 0.8595 0.0913
-6.250 -0.1989 0.01033 0.00426 -0.1214 0.8474 0.1304
-6.000 -0.1707 0.00971 0.00378 -0.1223 0.8360 0.1809
-5.750 -0.1429 0.00893 0.00324 -0.1233 0.8245 0.2604
-5.500 -0.1151 0.00851 0.00298 -0.1238 0.8130 0.3228
-5.250 -0.0866 0.00839 0.00287 -0.1240 0.8021 0.3515
-5.000 -0.0582 0.00834 0.00279 -0.1242 0.7916 0.3723
-4.750 -0.0300 0.00833 0.00272 -0.1242 0.7806 0.3862
-4.500 -0.0017 0.00834 0.00264 -0.1243 0.7702 0.3950
-4.250 0.0263 0.00835 0.00260 -0.1243 0.7599 0.4043
-4.000 0.0544 0.00839 0.00259 -0.1243 0.7492 0.4162
-3.750 0.0826 0.00845 0.00256 -0.1243 0.7392 0.4255
-3.500 0.1103 0.00846 0.00249 -0.1242 0.7290 0.4285
-3.250 0.1382 0.00845 0.00244 -0.1242 0.7186 0.4310
-3.000 0.1660 0.00847 0.00238 -0.1241 0.7087 0.4338
-2.750 0.1938 0.00850 0.00233 -0.1240 0.6986 0.4368
-2.500 0.2217 0.00852 0.00228 -0.1240 0.6882 0.4394
-2.250 0.2495 0.00856 0.00223 -0.1240 0.6783 0.4417
-2.000 0.2770 0.00857 0.00220 -0.1239 0.6681 0.4440
-1.750 0.3048 0.00859 0.00219 -0.1238 0.6584 0.4467
-1.500 0.3324 0.00864 0.00218 -0.1237 0.6488 0.4495
-1.250 0.3601 0.00867 0.00217 -0.1237 0.6389 0.4522
-1.000 0.3878 0.00872 0.00217 -0.1236 0.6296 0.4548
-0.750 0.4153 0.00879 0.00216 -0.1235 0.6201 0.4572
-0.500 0.4430 0.00881 0.00218 -0.1235 0.6107 0.4597
-0.250 0.4703 0.00887 0.00220 -0.1233 0.6016 0.4625
0.000 0.4980 0.00892 0.00224 -0.1233 0.5920 0.4654
0.250 0.5253 0.00899 0.00227 -0.1232 0.5829 0.4682
0.500 0.5526 0.00907 0.00231 -0.1230 0.5735 0.4710
0.750 0.5801 0.00914 0.00234 -0.1229 0.5643 0.4735
1.000 0.6070 0.00922 0.00240 -0.1227 0.5549 0.4761
1.250 0.6344 0.00928 0.00247 -0.1227 0.5454 0.4791
1.500 0.6614 0.00937 0.00254 -0.1225 0.5360 0.4823
1.750 0.6883 0.00947 0.00262 -0.1223 0.5263 0.4856
2.000 0.7153 0.00957 0.00270 -0.1221 0.5166 0.4885
2.250 0.7417 0.00968 0.00279 -0.1218 0.5066 0.4912
2.500 0.7683 0.00978 0.00289 -0.1216 0.4956 0.4941
2.750 0.7948 0.00990 0.00300 -0.1214 0.4848 0.4975
3.000 0.8208 0.01003 0.00312 -0.1210 0.4738 0.5012
3.250 0.8467 0.01019 0.00324 -0.1206 0.4623 0.5048
3.500 0.8729 0.01031 0.00338 -0.1203 0.4511 0.5081
3.750 0.8987 0.01046 0.00352 -0.1200 0.4404 0.5115
4.000 0.9240 0.01063 0.00368 -0.1195 0.4291 0.5153
4.250 0.9495 0.01079 0.00384 -0.1191 0.4171 0.5191
4.500 0.9747 0.01097 0.00401 -0.1187 0.4047 0.5229
4.750 0.9995 0.01116 0.00420 -0.1181 0.3921 0.5272
5.000 1.0240 0.01137 0.00440 -0.1176 0.3794 0.5318
5.250 1.0481 0.01160 0.00461 -0.1169 0.3669 0.5364
5.500 1.0721 0.01183 0.00484 -0.1163 0.3532 0.5406
5.750 1.0959 0.01207 0.00508 -0.1156 0.3395 0.5454
6.000 1.1191 0.01234 0.00533 -0.1148 0.3255 0.5506
6.250 1.1418 0.01263 0.00560 -0.1139 0.3105 0.5559
6.500 1.1636 0.01295 0.00591 -0.1129 0.2937 0.5618
6.750 1.1847 0.01331 0.00623 -0.1118 0.2767 0.5680
7.000 1.2053 0.01368 0.00658 -0.1107 0.2597 0.5737
7.250 1.2246 0.01408 0.00694 -0.1092 0.2410 0.5801
7.500 1.2421 0.01452 0.00734 -0.1075 0.2225 0.5867
7.750 1.2586 0.01499 0.00777 -0.1056 0.2044 0.5939
8.000 1.2747 0.01551 0.00824 -0.1037 0.1877 0.6020
8.250 1.2904 0.01605 0.00875 -0.1018 0.1717 0.6102
8.750 1.3209 0.01718 0.00984 -0.0978 0.1421 0.6280
9.250 1.3502 0.01835 0.01102 -0.0939 0.1187 0.6485
9.500 1.3643 0.01897 0.01167 -0.0920 0.1085 0.6606
9.750 1.3772 0.01965 0.01237 -0.0899 0.0991 0.6738
10.000 1.3887 0.02041 0.01316 -0.0877 0.0897 0.6882
10.250 1.4012 0.02113 0.01393 -0.0857 0.0817 0.7040
10.500 1.4122 0.02195 0.01480 -0.0836 0.0744 0.7214
10.750 1.4216 0.02288 0.01577 -0.0814 0.0669 0.7418
11.000 1.4325 0.02371 0.01671 -0.0795 0.0616 0.7686
11.250 1.4402 0.02472 0.01782 -0.0773 0.0561 0.8050
11.500 1.4444 0.02538 0.01877 -0.0741 0.0524 0.9340
11.750 1.4514 0.02658 0.01999 -0.0721 0.0478 1.0000
12.000 1.4601 0.02783 0.02128 -0.0705 0.0442 1.0000
12.250 1.4676 0.02922 0.02270 -0.0690 0.0404 1.0000
12.500 1.4742 0.03074 0.02425 -0.0675 0.0371 1.0000
12.750 1.4815 0.03226 0.02582 -0.0662 0.0344 1.0000
13.000 1.4862 0.03406 0.02765 -0.0649 0.0316 1.0000
13.250 1.4920 0.03584 0.02948 -0.0638 0.0293 1.0000
13.500 1.4970 0.03774 0.03144 -0.0628 0.0272 1.0000
13.750 1.4995 0.03995 0.03371 -0.0619 0.0251 1.0000
14.000 1.5039 0.04208 0.03591 -0.0612 0.0237 1.0000
14.250 1.5075 0.04435 0.03825 -0.0606 0.0223 1.0000
14.500 1.5090 0.04692 0.04088 -0.0601 0.0208 1.0000
14.750 1.5098 0.04966 0.04369 -0.0598 0.0195 1.0000
15.000 1.5120 0.05234 0.04647 -0.0596 0.0185 1.0000
15.250 1.5126 0.05529 0.04949 -0.0596 0.0173 1.0000
15.500 1.5117 0.05851 0.05279 -0.0598 0.0163 1.0000
15.750 1.5105 0.06190 0.05625 -0.0601 0.0153 1.0000
16.000 1.5104 0.06522 0.05968 -0.0606 0.0145 1.0000
16.250 1.5087 0.06886 0.06341 -0.0613 0.0137 1.0000
16.500 1.5055 0.07279 0.06743 -0.0621 0.0129 1.0000
16.750 1.5010 0.07703 0.07176 -0.0632 0.0122 1.0000
17.000 1.4988 0.08102 0.07586 -0.0643 0.0116 1.0000
17.250 1.4953 0.08530 0.08024 -0.0657 0.0111 1.0000
17.500 1.4906 0.08983 0.08487 -0.0672 0.0106 1.0000
17.750 1.4851 0.09458 0.08973 -0.0689 0.0101 1.0000
18.000 1.4786 0.09961 0.09485 -0.0708 0.0097 1.0000
18.250 1.4720 0.10471 0.10006 -0.0729 0.0093 1.0000
18.500 1.4666 0.10969 0.10515 -0.0751 0.0090 1.0000
18.750 1.4604 0.11484 0.11042 -0.0774 0.0087 1.0000
19.000 1.4538 0.12013 0.11582 -0.0799 0.0083 1.0000
19.250 1.4468 0.12555 0.12135 -0.0826 0.0080 1.0000
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