EPPLER 559 AIRFOIL (e559-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 559 AIRFOIL (e559-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.62 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e559-il-1000000-n5.txt Download as CSV file: xf-e559-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 559 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.8269 0.08758 0.08436 -0.0591 1.0000 0.0097
-16.250 -0.8379 0.08274 0.07946 -0.0613 1.0000 0.0098
-16.000 -0.8504 0.07777 0.07443 -0.0635 1.0000 0.0098
-15.750 -0.8639 0.07279 0.06938 -0.0658 1.0000 0.0099
-15.500 -0.8786 0.06781 0.06432 -0.0680 1.0000 0.0099
-15.250 -0.8939 0.06298 0.05942 -0.0701 1.0000 0.0101
-15.000 -0.9147 0.05784 0.05419 -0.0722 1.0000 0.0100
-14.750 -0.9326 0.05331 0.04959 -0.0737 1.0000 0.0102
-14.500 -0.9529 0.04837 0.04457 -0.0758 0.9998 0.0102
-14.250 -0.9573 0.04292 0.03900 -0.0818 0.9980 0.0102
-14.000 -0.9569 0.03801 0.03399 -0.0877 0.9956 0.0103
-13.500 -0.9510 0.02916 0.02491 -0.0986 0.9888 0.0106
-13.250 -0.9311 0.02481 0.02041 -0.1073 0.9852 0.0108
-13.000 -0.9008 0.02274 0.01823 -0.1126 0.9834 0.0111
-12.750 -0.8830 0.02150 0.01691 -0.1133 0.9794 0.0113
-12.500 -0.8597 0.02036 0.01570 -0.1146 0.9756 0.0115
-12.250 -0.8318 0.01924 0.01452 -0.1166 0.9730 0.0120
-12.000 -0.8009 0.01838 0.01362 -0.1186 0.9713 0.0125
-11.750 -0.7866 0.01769 0.01289 -0.1169 0.9634 0.0128
-11.250 -0.7387 0.01640 0.01150 -0.1170 0.9505 0.0135
-11.000 -0.7100 0.01579 0.01084 -0.1178 0.9450 0.0139
-10.750 -0.6814 0.01523 0.01023 -0.1185 0.9372 0.0142
-10.500 -0.6443 0.01450 0.00945 -0.1210 0.9320 0.0147
-10.250 -0.6035 0.01383 0.00874 -0.1243 0.9245 0.0154
-10.000 -0.5514 0.01323 0.00808 -0.1298 0.9177 0.0163
-9.750 -0.4969 0.01272 0.00748 -0.1358 0.9045 0.0171
-9.500 -0.4557 0.01233 0.00695 -0.1389 0.8812 0.0177
-9.250 -0.4271 0.01201 0.00650 -0.1394 0.8534 0.0188
-9.000 -0.4022 0.01178 0.00614 -0.1390 0.8294 0.0197
-8.750 -0.3778 0.01157 0.00582 -0.1384 0.8073 0.0207
-8.500 -0.3534 0.01135 0.00549 -0.1379 0.7878 0.0221
-8.250 -0.3288 0.01112 0.00517 -0.1374 0.7693 0.0242
-8.000 -0.3040 0.01086 0.00485 -0.1369 0.7521 0.0280
-7.750 -0.2790 0.01053 0.00450 -0.1366 0.7361 0.0371
-7.500 -0.2537 0.01024 0.00418 -0.1363 0.7205 0.0486
-7.250 -0.2278 0.00997 0.00390 -0.1360 0.7062 0.0586
-7.000 -0.2015 0.00973 0.00365 -0.1358 0.6926 0.0692
-6.750 -0.1751 0.00952 0.00342 -0.1356 0.6799 0.0805
-6.500 -0.1485 0.00930 0.00320 -0.1354 0.6670 0.0937
-6.250 -0.1214 0.00911 0.00300 -0.1353 0.6543 0.1071
-6.000 -0.0942 0.00893 0.00283 -0.1352 0.6429 0.1214
-5.750 -0.0670 0.00879 0.00268 -0.1351 0.6316 0.1339
-5.500 -0.0394 0.00869 0.00255 -0.1350 0.6198 0.1448
-5.250 -0.0117 0.00858 0.00243 -0.1350 0.6091 0.1570
-4.750 0.0438 0.00840 0.00223 -0.1349 0.5885 0.1802
-4.500 0.0717 0.00835 0.00215 -0.1348 0.5784 0.1896
-4.250 0.0996 0.00830 0.00208 -0.1347 0.5684 0.2010
-4.000 0.1277 0.00823 0.00202 -0.1347 0.5599 0.2131
-3.750 0.1557 0.00823 0.00197 -0.1346 0.5503 0.2197
-3.500 0.1839 0.00820 0.00192 -0.1346 0.5411 0.2279
-3.000 0.2401 0.00818 0.00185 -0.1345 0.5241 0.2411
-2.500 0.2964 0.00820 0.00180 -0.1343 0.5074 0.2534
-2.000 0.3526 0.00823 0.00178 -0.1342 0.4916 0.2669
-1.750 0.3806 0.00825 0.00178 -0.1341 0.4839 0.2741
-1.500 0.4087 0.00827 0.00178 -0.1341 0.4768 0.2802
-1.250 0.4367 0.00830 0.00179 -0.1340 0.4687 0.2868
-1.000 0.4647 0.00833 0.00181 -0.1339 0.4622 0.2934
-0.750 0.4929 0.00837 0.00182 -0.1338 0.4557 0.2988
-0.250 0.5487 0.00845 0.00188 -0.1337 0.4424 0.3126
0.000 0.5765 0.00851 0.00191 -0.1335 0.4354 0.3179
0.250 0.6043 0.00855 0.00195 -0.1334 0.4300 0.3254
0.500 0.6323 0.00859 0.00199 -0.1333 0.4243 0.3318
0.750 0.6598 0.00866 0.00205 -0.1332 0.4178 0.3380
1.000 0.6876 0.00871 0.00210 -0.1331 0.4123 0.3450
1.250 0.7153 0.00877 0.00215 -0.1330 0.4068 0.3513
1.500 0.7427 0.00884 0.00223 -0.1328 0.4014 0.3586
1.750 0.7703 0.00891 0.00229 -0.1326 0.3967 0.3651
2.000 0.7979 0.00897 0.00236 -0.1325 0.3912 0.3724
2.250 0.8250 0.00906 0.00245 -0.1323 0.3855 0.3799
2.500 0.8523 0.00914 0.00253 -0.1321 0.3812 0.3859
2.750 0.8798 0.00920 0.00262 -0.1320 0.3769 0.3940
3.250 0.9335 0.00940 0.00282 -0.1315 0.3666 0.4095
3.500 0.9608 0.00947 0.00291 -0.1313 0.3626 0.4171
3.750 0.9877 0.00955 0.00302 -0.1310 0.3579 0.4264
4.000 1.0140 0.00967 0.00314 -0.1307 0.3528 0.4355
4.250 1.0407 0.00976 0.00326 -0.1304 0.3485 0.4450
4.500 1.0674 0.00985 0.00338 -0.1302 0.3440 0.4552
4.750 1.0935 0.00997 0.00352 -0.1298 0.3386 0.4674
5.000 1.1194 0.01009 0.00367 -0.1294 0.3338 0.4799
5.250 1.1458 0.01018 0.00381 -0.1291 0.3293 0.4927
5.500 1.1716 0.01030 0.00396 -0.1287 0.3242 0.5087
5.750 1.1967 0.01045 0.00414 -0.1282 0.3188 0.5266
6.000 1.2227 0.01055 0.00430 -0.1279 0.3144 0.5453
6.250 1.2480 0.01067 0.00448 -0.1274 0.3088 0.5689
6.500 1.2724 0.01083 0.00469 -0.1268 0.3031 0.5950
6.750 1.2977 0.01094 0.00487 -0.1263 0.2980 0.6237
7.000 1.3220 0.01108 0.00509 -0.1257 0.2919 0.6594
7.250 1.3458 0.01122 0.00533 -0.1250 0.2856 0.7021
7.500 1.3694 0.01134 0.00556 -0.1242 0.2789 0.7524
7.750 1.3902 0.01147 0.00583 -0.1229 0.2720 0.8202
8.000 1.4055 0.01137 0.00601 -0.1202 0.2662 1.0000
8.250 1.4257 0.01169 0.00627 -0.1189 0.2574 1.0000
8.500 1.4472 0.01193 0.00651 -0.1177 0.2503 1.0000
8.750 1.4663 0.01227 0.00682 -0.1162 0.2414 1.0000
9.000 1.4860 0.01259 0.00711 -0.1148 0.2319 1.0000
9.250 1.5048 0.01296 0.00745 -0.1132 0.2229 1.0000
9.500 1.5219 0.01339 0.00783 -0.1115 0.2122 1.0000
9.750 1.5381 0.01386 0.00825 -0.1095 0.1998 1.0000
10.000 1.5532 0.01438 0.00872 -0.1075 0.1870 1.0000
10.250 1.5670 0.01495 0.00924 -0.1053 0.1744 1.0000
10.500 1.5796 0.01558 0.00981 -0.1030 0.1622 1.0000
10.750 1.5901 0.01631 0.01048 -0.1004 0.1485 1.0000
11.000 1.5993 0.01712 0.01122 -0.0977 0.1353 1.0000
11.250 1.6066 0.01802 0.01206 -0.0949 0.1219 1.0000
11.500 1.6136 0.01897 0.01297 -0.0921 0.1106 1.0000
11.750 1.6193 0.02003 0.01397 -0.0893 0.0997 1.0000
12.000 1.6235 0.02121 0.01512 -0.0865 0.0894 1.0000
12.250 1.6283 0.02243 0.01631 -0.0840 0.0808 1.0000
12.500 1.6333 0.02370 0.01758 -0.0817 0.0736 1.0000
12.750 1.6362 0.02519 0.01906 -0.0794 0.0669 1.0000
13.000 1.6393 0.02676 0.02063 -0.0774 0.0607 1.0000
13.250 1.6425 0.02841 0.02230 -0.0756 0.0557 1.0000
13.500 1.6437 0.03032 0.02422 -0.0738 0.0509 1.0000
13.750 1.6470 0.03217 0.02610 -0.0724 0.0473 1.0000
14.000 1.6477 0.03434 0.02830 -0.0711 0.0435 1.0000
14.250 1.6476 0.03669 0.03069 -0.0700 0.0399 1.0000
14.500 1.6477 0.03914 0.03318 -0.0691 0.0370 1.0000
14.750 1.6476 0.04172 0.03582 -0.0683 0.0349 1.0000
15.000 1.6453 0.04465 0.03879 -0.0678 0.0317 1.0000
15.250 1.6423 0.04776 0.04195 -0.0674 0.0296 1.0000
15.500 1.6413 0.05074 0.04500 -0.0672 0.0279 1.0000
15.750 1.6371 0.05422 0.04853 -0.0672 0.0258 1.0000
16.000 1.6332 0.05777 0.05214 -0.0674 0.0244 1.0000
16.250 1.6298 0.06136 0.05582 -0.0677 0.0230 1.0000
16.500 1.6244 0.06530 0.05982 -0.0682 0.0215 1.0000
16.750 1.6187 0.06940 0.06399 -0.0689 0.0203 1.0000
17.000 1.6141 0.07344 0.06811 -0.0696 0.0191 1.0000
17.250 1.6082 0.07775 0.07249 -0.0706 0.0180 1.0000
17.500 1.6008 0.08236 0.07717 -0.0718 0.0169 1.0000
17.750 1.5957 0.08671 0.08161 -0.0729 0.0160 1.0000
18.000 1.5899 0.09125 0.08622 -0.0743 0.0150 1.0000
18.250 1.5826 0.09608 0.09113 -0.0758 0.0140 1.0000
18.500 1.5770 0.10069 0.09580 -0.0773 0.0131 1.0000
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Polar data table (+)
Polar graphs
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