EPPLER 556 AIRFOIL (e556-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 556 AIRFOIL (e556-il) Reynolds number: 500,000 Max Cl/Cd: 97.95 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e556-il-500000.txt Download as CSV file: xf-e556-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.5339 0.13134 0.12880 -0.0378 1.0000 0.0106
-15.250 -0.5621 0.11972 0.11713 -0.0426 1.0000 0.0101
-15.000 -0.6138 0.10287 0.10009 -0.0514 1.0000 0.0098
-14.750 -0.6417 0.09298 0.09004 -0.0568 1.0000 0.0096
-14.500 -0.6718 0.08356 0.08044 -0.0620 1.0000 0.0095
-14.250 -0.6930 0.07649 0.07320 -0.0657 1.0000 0.0093
-14.000 -0.7172 0.06946 0.06598 -0.0691 1.0000 0.0092
-13.750 -0.7375 0.06358 0.05989 -0.0716 1.0000 0.0091
-13.500 -0.7567 0.05835 0.05444 -0.0733 1.0000 0.0089
-13.250 -0.7720 0.05398 0.04987 -0.0743 1.0000 0.0087
-13.000 -0.7794 0.05082 0.04660 -0.0746 1.0000 0.0089
-12.750 -0.7888 0.04753 0.04314 -0.0744 1.0000 0.0088
-12.500 -0.7943 0.04489 0.04039 -0.0739 1.0000 0.0088
-12.250 -0.7981 0.04260 0.03798 -0.0730 1.0000 0.0088
-12.000 -0.8020 0.04050 0.03577 -0.0717 1.0000 0.0087
-11.750 -0.8064 0.03861 0.03382 -0.0702 1.0000 0.0089
-11.500 -0.8120 0.03690 0.03203 -0.0680 1.0000 0.0089
-11.250 -0.8196 0.03540 0.03047 -0.0654 1.0000 0.0089
-11.000 -0.8322 0.03400 0.02902 -0.0620 1.0000 0.0089
-10.750 -0.8106 0.03206 0.02697 -0.0649 0.9969 0.0092
-10.500 -0.7864 0.03026 0.02506 -0.0680 0.9934 0.0093
-10.250 -0.7644 0.02846 0.02317 -0.0707 0.9881 0.0097
-10.000 -0.7342 0.02665 0.02126 -0.0748 0.9849 0.0099
-9.750 -0.7085 0.02485 0.01935 -0.0778 0.9789 0.0102
-9.500 -0.6765 0.02273 0.01712 -0.0825 0.9750 0.0107
-9.250 -0.6504 0.02096 0.01529 -0.0854 0.9689 0.0112
-9.000 -0.6181 0.01975 0.01405 -0.0882 0.9650 0.0120
-8.750 -0.5824 0.01870 0.01290 -0.0914 0.9627 0.0131
-8.500 -0.5552 0.01736 0.01152 -0.0932 0.9566 0.0144
-8.250 -0.5214 0.01649 0.01060 -0.0955 0.9529 0.0161
-8.000 -0.4854 0.01545 0.00953 -0.0983 0.9505 0.0193
-7.750 -0.4481 0.01454 0.00861 -0.1012 0.9487 0.0259
-7.500 -0.4201 0.01367 0.00777 -0.1022 0.9419 0.0348
-7.250 -0.3841 0.01291 0.00705 -0.1046 0.9383 0.0477
-7.000 -0.3451 0.01207 0.00631 -0.1078 0.9357 0.0699
-6.750 -0.3064 0.01119 0.00559 -0.1110 0.9319 0.1083
-6.500 -0.2718 0.01009 0.00481 -0.1137 0.9250 0.1793
-6.250 -0.2299 0.00863 0.00399 -0.1184 0.9208 0.3354
-6.000 -0.1939 0.00846 0.00386 -0.1203 0.9131 0.3720
-5.750 -0.1548 0.00839 0.00372 -0.1226 0.9059 0.3905
-5.500 -0.1205 0.00837 0.00364 -0.1238 0.8964 0.4025
-5.000 -0.0528 0.00845 0.00352 -0.1261 0.8764 0.4233
-4.750 -0.0218 0.00849 0.00349 -0.1267 0.8656 0.4310
-4.500 0.0098 0.00855 0.00344 -0.1273 0.8552 0.4374
-4.250 0.0388 0.00859 0.00338 -0.1274 0.8437 0.4436
-4.000 0.0674 0.00873 0.00350 -0.1274 0.8325 0.4522
-3.750 0.0966 0.00883 0.00349 -0.1276 0.8218 0.4593
-3.500 0.1249 0.00881 0.00342 -0.1276 0.8108 0.4623
-3.250 0.1527 0.00880 0.00335 -0.1275 0.7997 0.4652
-3.000 0.1810 0.00881 0.00328 -0.1275 0.7893 0.4681
-2.750 0.2092 0.00882 0.00319 -0.1275 0.7786 0.4710
-2.500 0.2369 0.00884 0.00311 -0.1274 0.7675 0.4738
-2.250 0.2645 0.00878 0.00303 -0.1273 0.7572 0.4765
-2.000 0.2922 0.00879 0.00298 -0.1272 0.7468 0.4790
-1.750 0.3197 0.00880 0.00295 -0.1271 0.7361 0.4817
-1.500 0.3474 0.00883 0.00292 -0.1270 0.7262 0.4848
-1.250 0.3752 0.00888 0.00289 -0.1269 0.7159 0.4879
-1.000 0.4027 0.00888 0.00285 -0.1269 0.7057 0.4907
-0.750 0.4301 0.00889 0.00282 -0.1267 0.6961 0.4933
-0.500 0.4574 0.00891 0.00283 -0.1266 0.6858 0.4961
-0.250 0.4849 0.00895 0.00284 -0.1265 0.6760 0.4991
0.250 0.5398 0.00907 0.00286 -0.1262 0.6560 0.5055
0.500 0.5669 0.00908 0.00286 -0.1261 0.6465 0.5086
0.750 0.5939 0.00913 0.00289 -0.1259 0.6365 0.5115
1.000 0.6211 0.00918 0.00294 -0.1257 0.6264 0.5147
1.250 0.6482 0.00927 0.00298 -0.1255 0.6168 0.5180
1.500 0.6752 0.00935 0.00302 -0.1253 0.6064 0.5214
1.750 0.7021 0.00939 0.00308 -0.1251 0.5966 0.5250
2.000 0.7286 0.00948 0.00315 -0.1248 0.5867 0.5284
2.250 0.7553 0.00955 0.00323 -0.1246 0.5760 0.5321
2.500 0.7820 0.00965 0.00331 -0.1243 0.5656 0.5358
2.750 0.8081 0.00977 0.00338 -0.1240 0.5551 0.5394
3.000 0.8344 0.00983 0.00348 -0.1237 0.5439 0.5431
3.250 0.8606 0.00993 0.00360 -0.1233 0.5332 0.5473
3.500 0.8864 0.01008 0.00371 -0.1229 0.5227 0.5519
3.750 0.9124 0.01018 0.00382 -0.1226 0.5116 0.5561
4.000 0.9382 0.01029 0.00396 -0.1222 0.5006 0.5603
4.250 0.9636 0.01044 0.00411 -0.1217 0.4896 0.5650
4.500 0.9887 0.01061 0.00425 -0.1212 0.4779 0.5699
4.750 1.0141 0.01072 0.00441 -0.1208 0.4661 0.5748
5.000 1.0391 0.01088 0.00459 -0.1203 0.4545 0.5804
5.250 1.0637 0.01108 0.00476 -0.1197 0.4430 0.5863
5.500 1.0877 0.01126 0.00496 -0.1190 0.4306 0.5918
5.750 1.1123 0.01143 0.00517 -0.1184 0.4181 0.5982
6.000 1.1363 0.01163 0.00538 -0.1177 0.4054 0.6047
6.250 1.1597 0.01184 0.00562 -0.1170 0.3922 0.6116
6.500 1.1826 0.01209 0.00587 -0.1161 0.3783 0.6196
6.750 1.2050 0.01234 0.00614 -0.1152 0.3642 0.6275
7.000 1.2270 0.01263 0.00642 -0.1142 0.3496 0.6364
7.250 1.2483 0.01292 0.00673 -0.1130 0.3337 0.6455
7.500 1.2689 0.01324 0.00706 -0.1118 0.3169 0.6553
8.000 1.3055 0.01399 0.00779 -0.1086 0.2797 0.6789
8.250 1.3210 0.01446 0.00822 -0.1065 0.2596 0.6922
8.500 1.3363 0.01496 0.00870 -0.1044 0.2383 0.7072
8.750 1.3505 0.01552 0.00924 -0.1022 0.2186 0.7240
9.000 1.3640 0.01612 0.00982 -0.0999 0.2005 0.7437
9.250 1.3772 0.01670 0.01042 -0.0976 0.1833 0.7673
9.500 1.3892 0.01730 0.01106 -0.0951 0.1675 0.7987
9.750 1.3985 0.01786 0.01172 -0.0921 0.1534 0.8483
10.000 1.4025 0.01831 0.01230 -0.0881 0.1412 1.0000
10.250 1.4137 0.01915 0.01308 -0.0860 0.1282 1.0000
10.750 1.4345 0.02097 0.01481 -0.0816 0.1053 1.0000
11.000 1.4447 0.02193 0.01576 -0.0796 0.0960 1.0000
11.250 1.4532 0.02302 0.01683 -0.0775 0.0875 1.0000
11.500 1.4606 0.02421 0.01802 -0.0754 0.0795 1.0000
11.750 1.4693 0.02538 0.01921 -0.0735 0.0726 1.0000
12.000 1.4742 0.02685 0.02066 -0.0715 0.0660 1.0000
12.250 1.4821 0.02818 0.02202 -0.0699 0.0605 1.0000
12.500 1.4858 0.02988 0.02373 -0.0681 0.0551 1.0000
12.750 1.4923 0.03143 0.02533 -0.0666 0.0508 1.0000
13.000 1.4923 0.03359 0.02749 -0.0650 0.0462 1.0000
13.250 1.4996 0.03522 0.02920 -0.0639 0.0430 1.0000
13.500 1.5012 0.03743 0.03143 -0.0627 0.0398 1.0000
13.750 1.5020 0.03980 0.03387 -0.0617 0.0370 1.0000
14.000 1.5058 0.04198 0.03613 -0.0609 0.0346 1.0000
14.250 1.5054 0.04467 0.03886 -0.0603 0.0325 1.0000
14.500 1.5017 0.04784 0.04209 -0.0597 0.0304 1.0000
14.750 1.5053 0.05030 0.04466 -0.0595 0.0288 1.0000
15.000 1.5053 0.05327 0.04770 -0.0594 0.0271 1.0000
15.250 1.5007 0.05690 0.05139 -0.0595 0.0256 1.0000
15.500 1.4958 0.06071 0.05528 -0.0598 0.0244 1.0000
15.750 1.4980 0.06371 0.05840 -0.0601 0.0231 1.0000
16.000 1.4969 0.06725 0.06201 -0.0607 0.0218 1.0000
16.250 1.4916 0.07144 0.06628 -0.0616 0.0209 1.0000
16.500 1.4800 0.07671 0.07165 -0.0630 0.0199 1.0000
16.750 1.4794 0.08048 0.07554 -0.0640 0.0191 1.0000
17.000 1.4776 0.08450 0.07966 -0.0652 0.0182 1.0000
17.250 1.4735 0.08895 0.08421 -0.0667 0.0175 1.0000
17.500 1.4669 0.09390 0.08925 -0.0685 0.0168 1.0000
17.750 1.4572 0.09946 0.09490 -0.0706 0.0162 1.0000
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Polar data table (+)
Polar graphs
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