EPPLER 559 AIRFOIL (e559-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 559 AIRFOIL (e559-il) Reynolds number: 500,000 Max Cl/Cd: 103.11 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e559-il-500000.txt Download as CSV file: xf-e559-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.6447 0.12609 0.12313 -0.0435 1.0000 0.0170
-17.000 -0.6793 0.11501 0.11187 -0.0494 1.0000 0.0170
-16.750 -0.7015 0.10699 0.10370 -0.0536 1.0000 0.0169
-16.500 -0.7195 0.09997 0.09656 -0.0574 1.0000 0.0170
-16.250 -0.7340 0.09386 0.09032 -0.0606 1.0000 0.0170
-16.000 -0.7463 0.08828 0.08462 -0.0635 1.0000 0.0171
-15.750 -0.7574 0.08299 0.07921 -0.0664 1.0000 0.0173
-15.500 -0.7658 0.07839 0.07451 -0.0686 1.0000 0.0173
-15.250 -0.7751 0.07374 0.06975 -0.0711 1.0000 0.0174
-15.000 -0.7813 0.06993 0.06585 -0.0726 1.0000 0.0175
-14.750 -0.7845 0.06721 0.06313 -0.0726 1.0000 0.0180
-14.500 -0.7865 0.06426 0.06017 -0.0735 1.0000 0.0183
-14.250 -0.7904 0.06126 0.05711 -0.0742 1.0000 0.0184
-14.000 -0.7950 0.05826 0.05408 -0.0750 1.0000 0.0186
-13.750 -0.8000 0.05527 0.05105 -0.0758 1.0000 0.0189
-13.500 -0.8057 0.05236 0.04809 -0.0763 1.0000 0.0191
-13.250 -0.8118 0.04950 0.04518 -0.0768 1.0000 0.0193
-13.000 -0.8201 0.04662 0.04225 -0.0769 1.0000 0.0195
-12.750 -0.8290 0.04386 0.03944 -0.0768 1.0000 0.0198
-12.500 -0.8397 0.04124 0.03677 -0.0761 1.0000 0.0199
-12.250 -0.8544 0.03866 0.03413 -0.0750 1.0000 0.0201
-12.000 -0.8775 0.03628 0.03172 -0.0725 1.0000 0.0201
-11.750 -0.8823 0.03335 0.02869 -0.0743 0.9981 0.0204
-11.500 -0.8482 0.03014 0.02531 -0.0830 0.9942 0.0209
-11.250 -0.8205 0.02700 0.02204 -0.0893 0.9888 0.0216
-11.000 -0.7878 0.02496 0.01994 -0.0941 0.9850 0.0224
-10.750 -0.7513 0.02351 0.01841 -0.0984 0.9829 0.0233
-10.500 -0.7237 0.02226 0.01708 -0.1001 0.9769 0.0242
-10.250 -0.6883 0.02132 0.01603 -0.1029 0.9739 0.0251
-10.000 -0.6530 0.01957 0.01423 -0.1068 0.9715 0.0266
-9.750 -0.6265 0.01858 0.01319 -0.1076 0.9645 0.0277
-9.500 -0.5908 0.01769 0.01222 -0.1100 0.9613 0.0291
-9.250 -0.5536 0.01662 0.01109 -0.1129 0.9591 0.0310
-9.000 -0.5274 0.01581 0.01024 -0.1132 0.9511 0.0331
-8.750 -0.4913 0.01499 0.00936 -0.1154 0.9477 0.0361
-8.500 -0.4601 0.01419 0.00854 -0.1165 0.9418 0.0408
-8.250 -0.4284 0.01319 0.00761 -0.1179 0.9358 0.0538
-8.000 -0.3922 0.01218 0.00675 -0.1202 0.9322 0.0813
-7.750 -0.3612 0.01160 0.00622 -0.1211 0.9232 0.1009
-7.500 -0.3204 0.01102 0.00569 -0.1240 0.9182 0.1198
-7.250 -0.2806 0.01059 0.00529 -0.1265 0.9099 0.1371
-7.000 -0.2334 0.01022 0.00492 -0.1306 0.9025 0.1548
-6.750 -0.1912 0.00993 0.00461 -0.1336 0.8900 0.1697
-6.500 -0.1510 0.00971 0.00434 -0.1361 0.8749 0.1838
-6.250 -0.1156 0.00956 0.00413 -0.1376 0.8577 0.1973
-6.000 -0.0839 0.00947 0.00395 -0.1383 0.8395 0.2085
-5.750 -0.0543 0.00945 0.00381 -0.1385 0.8216 0.2190
-5.500 -0.0263 0.00938 0.00369 -0.1384 0.8042 0.2289
-5.250 0.0012 0.00936 0.00357 -0.1382 0.7875 0.2382
-5.000 0.0285 0.00936 0.00349 -0.1379 0.7716 0.2477
-4.750 0.0555 0.00933 0.00340 -0.1376 0.7563 0.2564
-4.500 0.0826 0.00935 0.00331 -0.1373 0.7414 0.2646
-4.250 0.1094 0.00932 0.00323 -0.1370 0.7272 0.2721
-4.000 0.1365 0.00934 0.00316 -0.1366 0.7138 0.2797
-3.500 0.1905 0.00934 0.00303 -0.1360 0.6871 0.2943
-3.250 0.2177 0.00935 0.00296 -0.1357 0.6747 0.3010
-3.000 0.2448 0.00935 0.00293 -0.1354 0.6630 0.3084
-2.750 0.2719 0.00941 0.00288 -0.1351 0.6510 0.3154
-2.500 0.2991 0.00938 0.00285 -0.1349 0.6393 0.3227
-2.250 0.3263 0.00944 0.00283 -0.1346 0.6283 0.3300
-2.000 0.3534 0.00945 0.00280 -0.1343 0.6175 0.3369
-1.750 0.3808 0.00948 0.00280 -0.1341 0.6069 0.3444
-1.500 0.4080 0.00954 0.00279 -0.1338 0.5967 0.3513
-1.250 0.4352 0.00955 0.00280 -0.1336 0.5863 0.3585
-1.000 0.4626 0.00963 0.00280 -0.1333 0.5769 0.3661
-0.750 0.4896 0.00965 0.00282 -0.1331 0.5673 0.3732
-0.500 0.5170 0.00970 0.00284 -0.1329 0.5581 0.3809
-0.250 0.5438 0.00977 0.00286 -0.1326 0.5488 0.3883
0.000 0.5714 0.00981 0.00291 -0.1324 0.5401 0.3963
0.500 0.6257 0.00992 0.00299 -0.1319 0.5233 0.4122
1.000 0.6798 0.01006 0.00311 -0.1314 0.5072 0.4289
1.250 0.7065 0.01017 0.00317 -0.1311 0.4997 0.4379
1.500 0.7338 0.01022 0.00326 -0.1309 0.4924 0.4474
1.750 0.7605 0.01031 0.00333 -0.1306 0.4848 0.4567
2.000 0.7874 0.01039 0.00343 -0.1304 0.4780 0.4671
2.250 0.8143 0.01046 0.00352 -0.1301 0.4711 0.4779
2.500 0.8406 0.01060 0.00363 -0.1298 0.4648 0.4898
2.750 0.8678 0.01064 0.00375 -0.1296 0.4583 0.5026
3.000 0.8941 0.01074 0.00387 -0.1292 0.4517 0.5169
3.250 0.9207 0.01085 0.00401 -0.1289 0.4458 0.5329
3.500 0.9474 0.01091 0.00415 -0.1287 0.4399 0.5511
3.750 0.9733 0.01104 0.00429 -0.1283 0.4341 0.5723
4.000 0.9997 0.01111 0.00446 -0.1280 0.4284 0.5979
4.250 1.0259 0.01118 0.00463 -0.1276 0.4226 0.6284
4.500 1.0512 0.01130 0.00482 -0.1271 0.4172 0.6651
4.750 1.0767 0.01134 0.00503 -0.1266 0.4120 0.7123
5.000 1.1009 0.01135 0.00523 -0.1258 0.4065 0.7721
5.250 1.1197 0.01135 0.00542 -0.1237 0.4015 0.8575
5.500 1.1407 0.01131 0.00552 -0.1221 0.3966 1.0000
5.750 1.1666 0.01147 0.00569 -0.1217 0.3911 1.0000
6.000 1.1916 0.01170 0.00588 -0.1212 0.3859 1.0000
6.250 1.2168 0.01193 0.00610 -0.1208 0.3809 1.0000
6.500 1.2421 0.01209 0.00629 -0.1203 0.3755 1.0000
6.750 1.2662 0.01232 0.00650 -0.1196 0.3702 1.0000
7.000 1.2902 0.01258 0.00674 -0.1190 0.3651 1.0000
7.250 1.3146 0.01275 0.00695 -0.1183 0.3599 1.0000
7.500 1.3376 0.01299 0.00719 -0.1175 0.3545 1.0000
7.750 1.3601 0.01327 0.00745 -0.1165 0.3491 1.0000
8.000 1.3827 0.01344 0.00768 -0.1156 0.3437 1.0000
8.250 1.4032 0.01371 0.00793 -0.1143 0.3379 1.0000
8.500 1.4238 0.01398 0.00822 -0.1130 0.3324 1.0000
8.750 1.4449 0.01420 0.00849 -0.1118 0.3264 1.0000
9.000 1.4633 0.01454 0.00879 -0.1102 0.3203 1.0000
9.250 1.4841 0.01478 0.00910 -0.1090 0.3143 1.0000
9.500 1.5030 0.01509 0.00942 -0.1075 0.3079 1.0000
9.750 1.5206 0.01546 0.00980 -0.1058 0.3015 1.0000
10.000 1.5400 0.01576 0.01015 -0.1045 0.2945 1.0000
10.500 1.5744 0.01654 0.01098 -0.1012 0.2804 1.0000
11.000 1.6054 0.01748 0.01195 -0.0975 0.2641 1.0000
11.250 1.6181 0.01809 0.01255 -0.0954 0.2557 1.0000
11.500 1.6321 0.01867 0.01316 -0.0935 0.2461 1.0000
11.750 1.6441 0.01936 0.01386 -0.0914 0.2366 1.0000
12.000 1.6527 0.02024 0.01472 -0.0890 0.2264 1.0000
12.250 1.6615 0.02115 0.01563 -0.0867 0.2144 1.0000
12.500 1.6678 0.02226 0.01672 -0.0844 0.2015 1.0000
12.750 1.6721 0.02354 0.01798 -0.0819 0.1888 1.0000
13.000 1.6744 0.02503 0.01944 -0.0795 0.1767 1.0000
13.250 1.6741 0.02680 0.02118 -0.0771 0.1641 1.0000
13.500 1.6721 0.02880 0.02316 -0.0749 0.1522 1.0000
13.750 1.6683 0.03110 0.02543 -0.0729 0.1407 1.0000
14.000 1.6665 0.03338 0.02772 -0.0712 0.1306 1.0000
14.250 1.6631 0.03594 0.03029 -0.0698 0.1213 1.0000
14.500 1.6576 0.03883 0.03319 -0.0686 0.1134 1.0000
14.750 1.6530 0.04180 0.03619 -0.0677 0.1054 1.0000
15.000 1.6479 0.04496 0.03939 -0.0670 0.0994 1.0000
15.250 1.6411 0.04845 0.04292 -0.0666 0.0928 1.0000
15.500 1.6343 0.05207 0.04659 -0.0664 0.0874 1.0000
15.750 1.6268 0.05593 0.05050 -0.0664 0.0820 1.0000
16.000 1.6179 0.06009 0.05472 -0.0667 0.0775 1.0000
16.250 1.6113 0.06411 0.05880 -0.0671 0.0730 1.0000
16.500 1.5999 0.06887 0.06361 -0.0678 0.0689 1.0000
16.750 1.5933 0.07313 0.06796 -0.0686 0.0653 1.0000
17.000 1.5841 0.07783 0.07272 -0.0696 0.0617 1.0000
17.250 1.5720 0.08309 0.07803 -0.0709 0.0583 1.0000
17.500 1.5666 0.08746 0.08249 -0.0720 0.0552 1.0000
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Polar data table (+)
Polar graphs
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