EPPLER 556 AIRFOIL (e556-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 556 AIRFOIL (e556-il) Reynolds number: 200,000 Max Cl/Cd: 70.21 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e556-il-200000-n5.txt Download as CSV file: xf-e556-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.6014 0.10523 0.10095 -0.0517 1.0000 0.0095
-14.750 -0.6301 0.09505 0.09058 -0.0572 1.0000 0.0094
-14.500 -0.6534 0.08682 0.08217 -0.0615 1.0000 0.0094
-14.250 -0.6701 0.08037 0.07556 -0.0647 1.0000 0.0092
-14.000 -0.6844 0.07474 0.06976 -0.0673 1.0000 0.0094
-13.750 -0.6962 0.06984 0.06471 -0.0693 1.0000 0.0094
-13.500 -0.7046 0.06574 0.06045 -0.0707 1.0000 0.0093
-13.250 -0.7118 0.06205 0.05663 -0.0718 1.0000 0.0094
-13.000 -0.7196 0.05850 0.05293 -0.0725 1.0000 0.0096
-12.750 -0.7247 0.05546 0.04975 -0.0727 1.0000 0.0097
-12.500 -0.7295 0.05257 0.04673 -0.0727 1.0000 0.0099
-12.250 -0.7313 0.05020 0.04425 -0.0723 1.0000 0.0100
-12.000 -0.7331 0.04795 0.04191 -0.0717 1.0000 0.0100
-11.750 -0.7352 0.04580 0.03963 -0.0708 1.0000 0.0103
-11.500 -0.7368 0.04389 0.03764 -0.0696 1.0000 0.0105
-11.250 -0.7399 0.04207 0.03580 -0.0683 1.0000 0.0106
-11.000 -0.7446 0.04035 0.03407 -0.0666 1.0000 0.0109
-10.750 -0.7503 0.03884 0.03254 -0.0646 1.0000 0.0112
-10.500 -0.7591 0.03740 0.03107 -0.0618 1.0000 0.0113
-10.250 -0.7422 0.03567 0.02926 -0.0640 0.9965 0.0121
-10.000 -0.7214 0.03388 0.02734 -0.0666 0.9913 0.0127
-9.750 -0.7006 0.03212 0.02544 -0.0691 0.9852 0.0133
-9.500 -0.6821 0.03008 0.02335 -0.0717 0.9771 0.0140
-9.250 -0.6589 0.02822 0.02143 -0.0747 0.9698 0.0147
-9.000 -0.6323 0.02640 0.01950 -0.0781 0.9632 0.0159
-8.750 -0.6088 0.02487 0.01783 -0.0800 0.9555 0.0170
-8.500 -0.5796 0.02346 0.01638 -0.0828 0.9502 0.0192
-8.250 -0.5534 0.02226 0.01509 -0.0845 0.9435 0.0219
-8.000 -0.5240 0.02112 0.01389 -0.0865 0.9378 0.0257
-7.750 -0.4906 0.01991 0.01263 -0.0893 0.9343 0.0310
-7.500 -0.4647 0.01898 0.01168 -0.0903 0.9262 0.0377
-7.000 -0.3963 0.01703 0.00979 -0.0953 0.9174 0.0665
-6.750 -0.3665 0.01611 0.00896 -0.0969 0.9098 0.0926
-6.500 -0.3291 0.01500 0.00802 -0.1003 0.9055 0.1384
-6.250 -0.2944 0.01362 0.00701 -0.1035 0.8994 0.2233
-6.000 -0.2585 0.01279 0.00662 -0.1063 0.8929 0.3303
-5.750 -0.2180 0.01264 0.00646 -0.1090 0.8883 0.3705
-5.500 -0.1853 0.01261 0.00634 -0.1099 0.8796 0.3930
-5.250 -0.1460 0.01259 0.00617 -0.1122 0.8734 0.4100
-5.000 -0.1133 0.01261 0.00613 -0.1131 0.8643 0.4206
-4.750 -0.0758 0.01263 0.00605 -0.1149 0.8570 0.4319
-4.500 -0.0446 0.01277 0.00610 -0.1154 0.8469 0.4451
-4.250 -0.0106 0.01283 0.00606 -0.1165 0.8382 0.4541
-4.000 0.0215 0.01273 0.00579 -0.1174 0.8283 0.4582
-3.750 0.0521 0.01265 0.00565 -0.1179 0.8184 0.4608
-3.250 0.1131 0.01253 0.00534 -0.1189 0.7984 0.4671
-3.000 0.1432 0.01248 0.00515 -0.1193 0.7886 0.4706
-2.750 0.1735 0.01242 0.00495 -0.1198 0.7786 0.4738
-2.500 0.2015 0.01238 0.00488 -0.1198 0.7681 0.4761
-2.250 0.2304 0.01236 0.00480 -0.1200 0.7582 0.4789
-2.000 0.2589 0.01235 0.00471 -0.1200 0.7480 0.4821
-1.750 0.2871 0.01234 0.00462 -0.1201 0.7377 0.4852
-1.500 0.3160 0.01233 0.00450 -0.1203 0.7279 0.4885
-1.250 0.3436 0.01233 0.00445 -0.1202 0.7174 0.4912
-1.000 0.3712 0.01234 0.00444 -0.1201 0.7074 0.4940
-0.750 0.3993 0.01237 0.00441 -0.1201 0.6977 0.4971
-0.500 0.4266 0.01239 0.00439 -0.1200 0.6872 0.5004
-0.250 0.4545 0.01242 0.00435 -0.1200 0.6775 0.5037
0.000 0.4821 0.01246 0.00433 -0.1199 0.6677 0.5067
0.250 0.5091 0.01249 0.00437 -0.1197 0.6577 0.5096
0.500 0.5364 0.01255 0.00441 -0.1196 0.6483 0.5129
0.750 0.5635 0.01261 0.00444 -0.1194 0.6383 0.5166
1.000 0.5908 0.01268 0.00447 -0.1193 0.6285 0.5204
1.250 0.6179 0.01275 0.00451 -0.1192 0.6192 0.5234
1.500 0.6444 0.01281 0.00460 -0.1189 0.6090 0.5265
1.750 0.6711 0.01290 0.00468 -0.1187 0.5996 0.5301
2.000 0.6978 0.01300 0.00477 -0.1184 0.5897 0.5344
2.250 0.7245 0.01310 0.00486 -0.1182 0.5797 0.5386
2.500 0.7507 0.01320 0.00497 -0.1179 0.5703 0.5420
2.750 0.7767 0.01330 0.00511 -0.1175 0.5599 0.5457
3.000 0.8029 0.01343 0.00524 -0.1172 0.5499 0.5500
3.250 0.8288 0.01358 0.00536 -0.1169 0.5398 0.5547
3.500 0.8542 0.01369 0.00554 -0.1164 0.5287 0.5586
3.750 0.8795 0.01383 0.00572 -0.1159 0.5178 0.5634
4.000 0.9047 0.01401 0.00587 -0.1154 0.5071 0.5686
4.250 0.9294 0.01416 0.00607 -0.1148 0.4952 0.5731
4.500 0.9540 0.01433 0.00629 -0.1143 0.4838 0.5777
4.750 0.9785 0.01452 0.00650 -0.1136 0.4726 0.5835
5.000 1.0023 0.01473 0.00673 -0.1129 0.4612 0.5891
5.250 1.0261 0.01492 0.00698 -0.1122 0.4489 0.5949
5.500 1.0495 0.01515 0.00723 -0.1114 0.4364 0.6016
5.750 1.0722 0.01538 0.00752 -0.1105 0.4238 0.6073
6.000 1.0945 0.01564 0.00781 -0.1095 0.4110 0.6141
6.250 1.1162 0.01592 0.00812 -0.1085 0.3978 0.6213
6.500 1.1374 0.01620 0.00845 -0.1074 0.3841 0.6290
6.750 1.1583 0.01651 0.00881 -0.1062 0.3698 0.6373
7.000 1.1783 0.01684 0.00918 -0.1049 0.3553 0.6460
7.250 1.1974 0.01720 0.00958 -0.1034 0.3401 0.6549
7.500 1.2155 0.01759 0.01000 -0.1018 0.3243 0.6650
7.750 1.2314 0.01801 0.01046 -0.0998 0.3078 0.6756
8.000 1.2460 0.01846 0.01094 -0.0976 0.2915 0.6874
8.250 1.2602 0.01896 0.01147 -0.0954 0.2742 0.7006
8.500 1.2737 0.01952 0.01206 -0.0931 0.2561 0.7151
8.750 1.2857 0.02015 0.01271 -0.0907 0.2381 0.7310
9.000 1.2964 0.02084 0.01343 -0.0882 0.2208 0.7492
9.250 1.3058 0.02159 0.01420 -0.0855 0.2041 0.7717
9.500 1.3140 0.02236 0.01503 -0.0827 0.1891 0.8011
9.750 1.3197 0.02308 0.01585 -0.0794 0.1756 0.8484
10.000 1.3220 0.02374 0.01661 -0.0757 0.1636 1.0000
10.250 1.3309 0.02484 0.01768 -0.0737 0.1504 1.0000
10.500 1.3393 0.02601 0.01885 -0.0718 0.1386 1.0000
10.750 1.3465 0.02730 0.02012 -0.0699 0.1277 1.0000
11.000 1.3538 0.02865 0.02147 -0.0681 0.1175 1.0000
11.250 1.3614 0.03002 0.02287 -0.0665 0.1086 1.0000
11.500 1.3669 0.03161 0.02446 -0.0649 0.1005 1.0000
11.750 1.3726 0.03325 0.02613 -0.0634 0.0925 1.0000
12.000 1.3780 0.03497 0.02790 -0.0621 0.0857 1.0000
12.250 1.3816 0.03692 0.02988 -0.0609 0.0792 1.0000
12.500 1.3862 0.03885 0.03188 -0.0598 0.0734 1.0000
12.750 1.3885 0.04107 0.03413 -0.0588 0.0679 1.0000
13.000 1.3917 0.04329 0.03642 -0.0581 0.0632 1.0000
13.250 1.3938 0.04570 0.03889 -0.0574 0.0586 1.0000
13.500 1.3937 0.04841 0.04166 -0.0569 0.0549 1.0000
13.750 1.3963 0.05094 0.04429 -0.0566 0.0512 1.0000
14.000 1.3957 0.05393 0.04734 -0.0564 0.0480 1.0000
14.250 1.3942 0.05710 0.05059 -0.0564 0.0453 1.0000
14.500 1.3952 0.06009 0.05370 -0.0565 0.0426 1.0000
14.750 1.3937 0.06350 0.05721 -0.0569 0.0401 1.0000
15.000 1.3893 0.06738 0.06116 -0.0575 0.0382 1.0000
15.250 1.3881 0.07094 0.06484 -0.0581 0.0363 1.0000
15.500 1.3865 0.07465 0.06868 -0.0589 0.0344 1.0000
15.750 1.3830 0.07875 0.07288 -0.0599 0.0327 1.0000
16.000 1.3770 0.08331 0.07751 -0.0613 0.0313 1.0000
16.250 1.3724 0.08776 0.08208 -0.0627 0.0300 1.0000
16.500 1.3696 0.09202 0.08648 -0.0641 0.0287 1.0000
16.750 1.3656 0.09654 0.09113 -0.0657 0.0274 1.0000
17.000 1.3603 0.10139 0.09608 -0.0676 0.0263 1.0000
17.250 1.3533 0.10657 0.10135 -0.0698 0.0254 1.0000
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Polar data table (+)
Polar graphs
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