EPPLER 559 AIRFOIL (e559-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 559 AIRFOIL (e559-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.56 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e559-il-1000000.txt Download as CSV file: xf-e559-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8039 0.08675 0.08362 -0.0594 1.0000 0.0125
-16.000 -0.8092 0.08276 0.07958 -0.0611 1.0000 0.0126
-15.750 -0.8155 0.07862 0.07539 -0.0629 1.0000 0.0128
-15.500 -0.8209 0.07481 0.07153 -0.0644 1.0000 0.0128
-15.250 -0.8285 0.07073 0.06740 -0.0661 1.0000 0.0130
-15.000 -0.8368 0.06675 0.06336 -0.0677 1.0000 0.0131
-14.750 -0.8440 0.06295 0.05951 -0.0691 1.0000 0.0133
-14.500 -0.8534 0.05917 0.05566 -0.0704 1.0000 0.0134
-14.250 -0.8675 0.05519 0.05163 -0.0716 1.0000 0.0134
-14.000 -0.8810 0.05137 0.04775 -0.0725 1.0000 0.0135
-13.750 -0.8982 0.04743 0.04374 -0.0733 1.0000 0.0136
-13.500 -0.9167 0.04365 0.03990 -0.0735 1.0000 0.0136
-13.250 -0.9405 0.03991 0.03610 -0.0730 1.0000 0.0136
-13.000 -0.9528 0.03591 0.03201 -0.0753 0.9986 0.0137
-12.750 -0.9366 0.03187 0.02786 -0.0825 0.9947 0.0140
-12.500 -0.9108 0.02792 0.02377 -0.0908 0.9913 0.0142
-12.250 -0.8829 0.02344 0.01909 -0.1007 0.9865 0.0147
-12.000 -0.8512 0.02159 0.01716 -0.1051 0.9845 0.0152
-11.750 -0.8167 0.02051 0.01603 -0.1084 0.9833 0.0158
-11.500 -0.7912 0.01958 0.01505 -0.1093 0.9792 0.0163
-11.250 -0.7607 0.01869 0.01409 -0.1111 0.9761 0.0169
-11.000 -0.7270 0.01796 0.01330 -0.1132 0.9740 0.0173
-10.750 -0.6933 0.01676 0.01201 -0.1159 0.9724 0.0180
-10.500 -0.6669 0.01583 0.01103 -0.1167 0.9679 0.0187
-10.250 -0.6376 0.01513 0.01029 -0.1176 0.9636 0.0194
-10.000 -0.6037 0.01451 0.00963 -0.1193 0.9611 0.0202
-9.750 -0.5683 0.01396 0.00903 -0.1212 0.9592 0.0209
-9.500 -0.5469 0.01325 0.00827 -0.1204 0.9501 0.0219
-9.250 -0.5145 0.01258 0.00757 -0.1217 0.9463 0.0231
-9.000 -0.4873 0.01210 0.00704 -0.1218 0.9374 0.0242
-8.750 -0.4494 0.01155 0.00644 -0.1240 0.9329 0.0259
-8.500 -0.4106 0.01097 0.00585 -0.1266 0.9252 0.0288
-8.250 -0.3618 0.01031 0.00521 -0.1313 0.9186 0.0377
-8.000 -0.3137 0.00953 0.00454 -0.1362 0.9068 0.0632
-7.750 -0.2726 0.00904 0.00408 -0.1393 0.8884 0.0844
-7.500 -0.2401 0.00878 0.00377 -0.1404 0.8661 0.0999
-7.250 -0.2124 0.00858 0.00353 -0.1404 0.8438 0.1133
-7.000 -0.1859 0.00842 0.00332 -0.1401 0.8233 0.1264
-6.750 -0.1598 0.00828 0.00314 -0.1398 0.8046 0.1393
-6.500 -0.1336 0.00815 0.00297 -0.1394 0.7868 0.1523
-6.250 -0.1074 0.00805 0.00283 -0.1390 0.7698 0.1643
-6.000 -0.0807 0.00797 0.00270 -0.1387 0.7541 0.1759
-5.750 -0.0539 0.00791 0.00259 -0.1384 0.7391 0.1861
-5.500 -0.0270 0.00783 0.00249 -0.1381 0.7242 0.1962
-5.250 0.0001 0.00780 0.00240 -0.1378 0.7102 0.2055
-5.000 0.0272 0.00776 0.00232 -0.1376 0.6970 0.2153
-4.500 0.0820 0.00771 0.00218 -0.1371 0.6706 0.2323
-4.250 0.1096 0.00768 0.00212 -0.1370 0.6586 0.2415
-4.000 0.1371 0.00770 0.00208 -0.1368 0.6470 0.2497
-3.750 0.1648 0.00767 0.00202 -0.1366 0.6351 0.2575
-3.500 0.1927 0.00768 0.00198 -0.1365 0.6238 0.2645
-3.250 0.2203 0.00768 0.00194 -0.1363 0.6129 0.2710
-3.000 0.2482 0.00769 0.00191 -0.1362 0.6023 0.2784
-2.750 0.2762 0.00771 0.00189 -0.1361 0.5923 0.2843
-2.500 0.3037 0.00772 0.00187 -0.1359 0.5817 0.2917
-2.250 0.3319 0.00774 0.00186 -0.1358 0.5717 0.2982
-2.000 0.3597 0.00776 0.00185 -0.1357 0.5625 0.3055
-1.750 0.3877 0.00779 0.00185 -0.1356 0.5530 0.3125
-1.500 0.4156 0.00782 0.00184 -0.1355 0.5440 0.3187
-1.250 0.4433 0.00785 0.00186 -0.1353 0.5343 0.3264
-1.000 0.4713 0.00790 0.00187 -0.1352 0.5261 0.3323
-0.750 0.4990 0.00793 0.00189 -0.1351 0.5175 0.3396
-0.500 0.5270 0.00798 0.00191 -0.1350 0.5094 0.3469
-0.250 0.5546 0.00803 0.00194 -0.1348 0.5007 0.3536
0.000 0.5825 0.00807 0.00198 -0.1347 0.4931 0.3607
0.250 0.6102 0.00814 0.00201 -0.1346 0.4854 0.3673
0.500 0.6379 0.00818 0.00206 -0.1345 0.4783 0.3753
0.750 0.6656 0.00825 0.00211 -0.1343 0.4707 0.3823
1.000 0.6929 0.00832 0.00216 -0.1341 0.4634 0.3898
1.250 0.7208 0.00837 0.00222 -0.1340 0.4569 0.3978
1.500 0.7479 0.00846 0.00229 -0.1338 0.4500 0.4054
1.750 0.7757 0.00851 0.00235 -0.1337 0.4441 0.4137
2.000 0.8031 0.00858 0.00243 -0.1335 0.4373 0.4220
2.250 0.8300 0.00868 0.00251 -0.1333 0.4309 0.4313
2.500 0.8577 0.00873 0.00259 -0.1332 0.4255 0.4401
2.750 0.8847 0.00882 0.00268 -0.1329 0.4195 0.4503
3.000 0.9116 0.00890 0.00278 -0.1327 0.4139 0.4612
3.250 0.9390 0.00897 0.00287 -0.1325 0.4083 0.4726
3.500 0.9656 0.00907 0.00299 -0.1322 0.4026 0.4853
3.750 0.9924 0.00916 0.00311 -0.1320 0.3975 0.5001
4.000 1.0196 0.00921 0.00322 -0.1318 0.3924 0.5165
4.250 1.0459 0.00932 0.00335 -0.1315 0.3867 0.5343
4.500 1.0722 0.00942 0.00349 -0.1311 0.3817 0.5554
4.750 1.0992 0.00947 0.00362 -0.1310 0.3768 0.5805
5.000 1.1252 0.00956 0.00378 -0.1306 0.3714 0.6093
5.500 1.1775 0.00970 0.00411 -0.1299 0.3617 0.6844
5.750 1.2030 0.00976 0.00429 -0.1295 0.3565 0.7353
6.000 1.2264 0.00985 0.00451 -0.1286 0.3508 0.7979
6.250 1.2455 0.00971 0.00466 -0.1266 0.3470 0.9063
6.500 1.2699 0.00976 0.00478 -0.1258 0.3419 1.0000
6.750 1.2941 0.00998 0.00496 -0.1251 0.3361 1.0000
7.000 1.3198 0.01013 0.00512 -0.1247 0.3316 1.0000
7.250 1.3448 0.01030 0.00529 -0.1242 0.3260 1.0000
7.500 1.3679 0.01055 0.00551 -0.1233 0.3197 1.0000
7.750 1.3927 0.01070 0.00568 -0.1228 0.3149 1.0000
8.000 1.4158 0.01090 0.00587 -0.1219 0.3090 1.0000
8.250 1.4370 0.01116 0.00610 -0.1207 0.3025 1.0000
8.500 1.4602 0.01133 0.00630 -0.1198 0.2971 1.0000
8.750 1.4809 0.01160 0.00654 -0.1185 0.2901 1.0000
9.000 1.5025 0.01183 0.00679 -0.1174 0.2840 1.0000
9.250 1.5231 0.01210 0.00705 -0.1161 0.2770 1.0000
9.500 1.5431 0.01240 0.00733 -0.1148 0.2700 1.0000
9.750 1.5630 0.01270 0.00763 -0.1135 0.2615 1.0000
10.000 1.5818 0.01305 0.00796 -0.1119 0.2533 1.0000
10.250 1.5991 0.01345 0.00833 -0.1102 0.2438 1.0000
10.500 1.6172 0.01382 0.00870 -0.1086 0.2343 1.0000
10.750 1.6321 0.01434 0.00916 -0.1066 0.2216 1.0000
11.000 1.6454 0.01493 0.00969 -0.1044 0.2085 1.0000
11.250 1.6571 0.01559 0.01030 -0.1019 0.1943 1.0000
11.500 1.6670 0.01635 0.01098 -0.0993 0.1802 1.0000
11.750 1.6749 0.01721 0.01178 -0.0965 0.1657 1.0000
12.000 1.6818 0.01814 0.01265 -0.0937 0.1527 1.0000
12.250 1.6872 0.01918 0.01364 -0.0908 0.1400 1.0000
12.500 1.6918 0.02031 0.01473 -0.0880 0.1286 1.0000
12.750 1.6959 0.02153 0.01592 -0.0853 0.1176 1.0000
13.000 1.6990 0.02288 0.01723 -0.0828 0.1076 1.0000
13.250 1.7015 0.02435 0.01869 -0.0803 0.0993 1.0000
13.500 1.7026 0.02601 0.02034 -0.0780 0.0914 1.0000
13.750 1.7056 0.02763 0.02198 -0.0761 0.0848 1.0000
14.000 1.7045 0.02967 0.02401 -0.0741 0.0780 1.0000
14.250 1.7045 0.03175 0.02611 -0.0725 0.0719 1.0000
14.500 1.7036 0.03402 0.02840 -0.0710 0.0667 1.0000
14.750 1.7036 0.03635 0.03077 -0.0699 0.0625 1.0000
15.000 1.6999 0.03913 0.03357 -0.0688 0.0577 1.0000
15.250 1.6986 0.04180 0.03629 -0.0681 0.0541 1.0000
15.500 1.6933 0.04502 0.03954 -0.0675 0.0505 1.0000
15.750 1.6912 0.04803 0.04261 -0.0671 0.0475 1.0000
16.000 1.6863 0.05144 0.04608 -0.0669 0.0447 1.0000
16.250 1.6792 0.05526 0.04995 -0.0669 0.0418 1.0000
16.500 1.6755 0.05880 0.05356 -0.0671 0.0395 1.0000
16.750 1.6682 0.06287 0.05770 -0.0675 0.0372 1.0000
17.000 1.6604 0.06714 0.06203 -0.0681 0.0351 1.0000
17.250 1.6553 0.07117 0.06613 -0.0688 0.0333 1.0000
17.500 1.6470 0.07573 0.07076 -0.0698 0.0314 1.0000
17.750 1.6373 0.08059 0.07569 -0.0710 0.0296 1.0000
18.000 1.6318 0.08493 0.08011 -0.0721 0.0281 1.0000
18.250 1.6237 0.08976 0.08500 -0.0735 0.0265 1.0000
18.500 1.6137 0.09494 0.09025 -0.0751 0.0249 1.0000
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