EPPLER 557 AIRFOIL (e557-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 557 AIRFOIL (e557-il) Reynolds number: 500,000 Max Cl/Cd: 95.15 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e557-il-500000-n5.txt Download as CSV file: xf-e557-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 557 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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.6669 0.12152 0.11840 -0.0454 1.0000 0.0047
-16.750 -0.6883 0.11305 0.10980 -0.0494 1.0000 0.0046
-16.500 -0.7088 0.10502 0.10164 -0.0532 1.0000 0.0047
-16.250 -0.7265 0.09790 0.09440 -0.0565 1.0000 0.0046
-16.000 -0.7411 0.09152 0.08790 -0.0595 1.0000 0.0046
-15.750 -0.7537 0.08578 0.08205 -0.0622 1.0000 0.0046
-15.500 -0.7651 0.08046 0.07663 -0.0646 1.0000 0.0046
-15.250 -0.7755 0.07550 0.07157 -0.0667 1.0000 0.0047
-15.000 -0.7825 0.07126 0.06723 -0.0684 1.0000 0.0047
-14.750 -0.7894 0.06721 0.06309 -0.0699 1.0000 0.0048
-14.500 -0.7959 0.06340 0.05919 -0.0712 1.0000 0.0049
-14.250 -0.8030 0.05975 0.05544 -0.0722 1.0000 0.0048
-14.000 -0.8077 0.05653 0.05214 -0.0729 1.0000 0.0049
-13.750 -0.8120 0.05357 0.04910 -0.0734 1.0000 0.0050
-13.500 -0.8188 0.05061 0.04607 -0.0735 1.0000 0.0050
-13.250 -0.8230 0.04816 0.04355 -0.0733 1.0000 0.0050
-13.000 -0.8302 0.04560 0.04093 -0.0728 1.0000 0.0051
-12.750 -0.8299 0.04310 0.03835 -0.0736 0.9994 0.0051
-12.500 -0.8159 0.04045 0.03559 -0.0769 0.9973 0.0053
-12.250 -0.8010 0.03788 0.03293 -0.0804 0.9947 0.0053
-12.000 -0.7860 0.03557 0.03053 -0.0833 0.9919 0.0054
-11.750 -0.7727 0.03310 0.02797 -0.0862 0.9876 0.0056
-11.500 -0.7554 0.03074 0.02553 -0.0898 0.9840 0.0057
-11.250 -0.7451 0.02884 0.02358 -0.0909 0.9766 0.0060
-11.000 -0.7333 0.02696 0.02163 -0.0924 0.9691 0.0060
-10.750 -0.7143 0.02502 0.01961 -0.0951 0.9627 0.0063
-10.500 -0.6934 0.02330 0.01781 -0.0976 0.9558 0.0066
-10.250 -0.6669 0.02155 0.01597 -0.1011 0.9504 0.0068
-10.000 -0.6355 0.02013 0.01444 -0.1048 0.9474 0.0073
-9.750 -0.6129 0.01903 0.01326 -0.1059 0.9394 0.0077
-9.500 -0.5812 0.01801 0.01219 -0.1084 0.9355 0.0083
-9.250 -0.5471 0.01717 0.01128 -0.1110 0.9321 0.0093
-9.000 -0.5180 0.01639 0.01045 -0.1126 0.9253 0.0102
-8.750 -0.4816 0.01567 0.00968 -0.1154 0.9211 0.0119
-8.500 -0.4417 0.01493 0.00890 -0.1189 0.9176 0.0141
-8.250 -0.4072 0.01431 0.00825 -0.1212 0.9102 0.0166
-8.000 -0.3651 0.01371 0.00761 -0.1250 0.9050 0.0201
-7.750 -0.3256 0.01316 0.00702 -0.1282 0.8982 0.0248
-7.500 -0.2876 0.01265 0.00649 -0.1310 0.8898 0.0307
-7.000 -0.2168 0.01174 0.00553 -0.1354 0.8707 0.0491
-6.750 -0.1862 0.01134 0.00513 -0.1366 0.8596 0.0628
-6.500 -0.1554 0.01091 0.00473 -0.1377 0.8490 0.0812
-6.000 -0.0967 0.01005 0.00396 -0.1395 0.8269 0.1364
-5.750 -0.0679 0.00947 0.00351 -0.1404 0.8163 0.1886
-5.500 -0.0389 0.00873 0.00304 -0.1416 0.8058 0.2766
-5.250 -0.0104 0.00847 0.00289 -0.1421 0.7950 0.3283
-5.000 0.0182 0.00840 0.00280 -0.1423 0.7850 0.3509
-4.750 0.0465 0.00838 0.00272 -0.1424 0.7746 0.3650
-4.500 0.0748 0.00838 0.00265 -0.1424 0.7645 0.3760
-4.250 0.1030 0.00838 0.00260 -0.1424 0.7548 0.3844
-4.000 0.1310 0.00841 0.00254 -0.1424 0.7444 0.3937
-3.750 0.1592 0.00846 0.00254 -0.1424 0.7349 0.4065
-3.500 0.1870 0.00850 0.00255 -0.1424 0.7249 0.4147
-3.250 0.2150 0.00852 0.00249 -0.1424 0.7155 0.4182
-3.000 0.2427 0.00855 0.00243 -0.1423 0.7059 0.4211
-2.750 0.2707 0.00858 0.00237 -0.1423 0.6959 0.4238
-2.500 0.2983 0.00859 0.00234 -0.1422 0.6866 0.4265
-2.250 0.3259 0.00862 0.00232 -0.1421 0.6767 0.4291
-2.000 0.3538 0.00864 0.00230 -0.1420 0.6675 0.4317
-1.500 0.4090 0.00873 0.00226 -0.1419 0.6488 0.4374
-1.250 0.4365 0.00879 0.00225 -0.1417 0.6399 0.4402
-1.000 0.4642 0.00882 0.00226 -0.1417 0.6306 0.4428
-0.750 0.4916 0.00887 0.00228 -0.1416 0.6219 0.4454
-0.500 0.5190 0.00892 0.00230 -0.1415 0.6126 0.4481
-0.250 0.5465 0.00898 0.00233 -0.1414 0.6042 0.4509
0.000 0.5737 0.00905 0.00235 -0.1412 0.5949 0.4540
0.250 0.6011 0.00913 0.00239 -0.1411 0.5861 0.4569
0.500 0.6281 0.00920 0.00244 -0.1409 0.5773 0.4598
0.750 0.6555 0.00926 0.00249 -0.1408 0.5683 0.4626
1.000 0.6821 0.00935 0.00256 -0.1406 0.5593 0.4656
1.250 0.7095 0.00943 0.00262 -0.1404 0.5502 0.4687
1.500 0.7361 0.00954 0.00269 -0.1402 0.5413 0.4717
1.750 0.7630 0.00963 0.00277 -0.1400 0.5319 0.4747
2.000 0.7895 0.00972 0.00287 -0.1397 0.5229 0.4780
2.250 0.8159 0.00983 0.00297 -0.1394 0.5132 0.4816
2.500 0.8424 0.00994 0.00308 -0.1392 0.5035 0.4851
2.750 0.8681 0.01009 0.00319 -0.1388 0.4936 0.4884
3.000 0.8943 0.01021 0.00330 -0.1385 0.4830 0.4915
3.250 0.9201 0.01034 0.00344 -0.1381 0.4727 0.4949
3.500 0.9452 0.01051 0.00359 -0.1376 0.4620 0.4989
3.750 0.9710 0.01065 0.00373 -0.1372 0.4509 0.5032
4.000 0.9962 0.01082 0.00389 -0.1367 0.4405 0.5072
4.250 1.0207 0.01100 0.00406 -0.1361 0.4295 0.5110
4.500 1.0459 0.01116 0.00424 -0.1356 0.4183 0.5152
4.750 1.0705 0.01135 0.00443 -0.1350 0.4074 0.5196
5.000 1.0943 0.01157 0.00463 -0.1343 0.3959 0.5240
5.250 1.1181 0.01178 0.00484 -0.1336 0.3835 0.5288
5.500 1.1418 0.01200 0.00507 -0.1329 0.3711 0.5342
5.750 1.1646 0.01226 0.00531 -0.1320 0.3577 0.5396
6.000 1.1870 0.01252 0.00557 -0.1311 0.3447 0.5446
6.250 1.2087 0.01281 0.00585 -0.1300 0.3309 0.5502
6.500 1.2291 0.01312 0.00614 -0.1287 0.3164 0.5562
6.750 1.2487 0.01344 0.00645 -0.1273 0.3015 0.5623
7.000 1.2677 0.01379 0.00678 -0.1257 0.2857 0.5694
7.250 1.2859 0.01419 0.00716 -0.1241 0.2686 0.5764
7.500 1.3033 0.01464 0.00757 -0.1223 0.2505 0.5838
7.750 1.3199 0.01513 0.00802 -0.1205 0.2325 0.5913
8.000 1.3362 0.01565 0.00851 -0.1186 0.2154 0.5992
8.250 1.3515 0.01621 0.00903 -0.1166 0.1989 0.6080
8.500 1.3666 0.01678 0.00958 -0.1146 0.1837 0.6179
8.750 1.3809 0.01739 0.01017 -0.1126 0.1689 0.6281
9.000 1.3947 0.01802 0.01080 -0.1105 0.1551 0.6394
9.250 1.4084 0.01866 0.01146 -0.1085 0.1432 0.6509
9.500 1.4214 0.01935 0.01215 -0.1064 0.1320 0.6631
9.750 1.4332 0.02011 0.01292 -0.1042 0.1213 0.6768
10.000 1.4445 0.02091 0.01374 -0.1020 0.1105 0.6930
10.250 1.4557 0.02173 0.01461 -0.0999 0.1007 0.7110
10.500 1.4660 0.02261 0.01555 -0.0978 0.0922 0.7326
11.000 1.4851 0.02450 0.01760 -0.0936 0.0777 0.7905
11.250 1.4914 0.02550 0.01875 -0.0911 0.0719 0.8453
11.500 1.4954 0.02635 0.01975 -0.0881 0.0669 1.0000
11.750 1.5027 0.02769 0.02110 -0.0862 0.0616 1.0000
12.000 1.5112 0.02900 0.02244 -0.0847 0.0567 1.0000
12.250 1.5176 0.03052 0.02398 -0.0830 0.0524 1.0000
12.500 1.5250 0.03202 0.02552 -0.0816 0.0484 1.0000
13.000 1.5365 0.03547 0.02904 -0.0789 0.0413 1.0000
13.250 1.5403 0.03747 0.03107 -0.0777 0.0380 1.0000
13.500 1.5453 0.03942 0.03309 -0.0767 0.0353 1.0000
13.750 1.5485 0.04163 0.03534 -0.0758 0.0325 1.0000
14.000 1.5516 0.04394 0.03770 -0.0750 0.0303 1.0000
14.250 1.5548 0.04629 0.04012 -0.0743 0.0281 1.0000
14.500 1.5558 0.04898 0.04286 -0.0738 0.0261 1.0000
14.750 1.5584 0.05158 0.04554 -0.0735 0.0245 1.0000
15.000 1.5595 0.05443 0.04846 -0.0732 0.0228 1.0000
15.250 1.5589 0.05758 0.05168 -0.0732 0.0215 1.0000
15.500 1.5599 0.06061 0.05481 -0.0732 0.0202 1.0000
15.750 1.5597 0.06391 0.05819 -0.0735 0.0189 1.0000
16.000 1.5576 0.06754 0.06189 -0.0739 0.0179 1.0000
16.250 1.5562 0.07116 0.06561 -0.0744 0.0169 1.0000
16.500 1.5548 0.07488 0.06942 -0.0751 0.0160 1.0000
16.750 1.5521 0.07888 0.07351 -0.0760 0.0151 1.0000
17.000 1.5477 0.08321 0.07792 -0.0771 0.0144 1.0000
17.250 1.5448 0.08740 0.08222 -0.0783 0.0137 1.0000
17.500 1.5413 0.09176 0.08669 -0.0796 0.0130 1.0000
17.750 1.5367 0.09637 0.09139 -0.0811 0.0124 1.0000
18.000 1.5310 0.10122 0.09635 -0.0829 0.0118 1.0000
18.250 1.5250 0.10621 0.10143 -0.0848 0.0114 1.0000
18.500 1.5205 0.11097 0.10632 -0.0867 0.0109 1.0000
18.750 1.5153 0.11592 0.11137 -0.0888 0.0104 1.0000
19.000 1.5094 0.12103 0.11659 -0.0912 0.0100 1.0000
19.250 1.5029 0.12630 0.12195 -0.0937 0.0096 1.0000
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