EPPLER 559 AIRFOIL (e559-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 559 AIRFOIL (e559-il) Reynolds number: 200,000 Max Cl/Cd: 70.36 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e559-il-200000.txt Download as CSV file: xf-e559-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6202 0.08428 0.07999 -0.0691 1.0000 0.0351
-13.750 -0.6462 0.07710 0.07270 -0.0730 1.0000 0.0347
-13.500 -0.6725 0.07039 0.06585 -0.0770 1.0000 0.0346
-13.250 -0.6953 0.06465 0.05996 -0.0804 1.0000 0.0346
-13.000 -0.7174 0.05939 0.05454 -0.0832 1.0000 0.0346
-12.750 -0.7362 0.05494 0.04995 -0.0853 1.0000 0.0347
-12.500 -0.7534 0.05110 0.04597 -0.0865 1.0000 0.0348
-12.250 -0.7716 0.04776 0.04249 -0.0871 1.0000 0.0349
-12.000 -0.7878 0.04513 0.03976 -0.0863 1.0000 0.0349
-11.750 -0.8114 0.04303 0.03757 -0.0841 1.0000 0.0350
-11.500 -0.8254 0.04087 0.03523 -0.0831 1.0000 0.0352
-11.250 -0.8260 0.03857 0.03293 -0.0811 1.0000 0.0359
-11.000 -0.8240 0.03699 0.03135 -0.0794 1.0000 0.0365
-10.750 -0.8207 0.03554 0.02987 -0.0777 1.0000 0.0372
-10.500 -0.8160 0.03414 0.02838 -0.0763 1.0000 0.0380
-10.250 -0.8093 0.03277 0.02691 -0.0749 1.0000 0.0388
-10.000 -0.7916 0.03131 0.02531 -0.0753 0.9986 0.0399
-9.750 -0.7535 0.02960 0.02339 -0.0794 0.9939 0.0420
-9.500 -0.7187 0.02807 0.02193 -0.0825 0.9883 0.0443
-9.250 -0.6792 0.02677 0.02053 -0.0862 0.9836 0.0469
-9.000 -0.6451 0.02527 0.01894 -0.0888 0.9770 0.0498
-8.750 -0.6055 0.02395 0.01764 -0.0926 0.9722 0.0542
-8.500 -0.5718 0.02255 0.01621 -0.0952 0.9649 0.0597
-8.250 -0.5314 0.02107 0.01473 -0.0990 0.9602 0.0698
-8.000 -0.4976 0.01958 0.01332 -0.1016 0.9524 0.0914
-7.750 -0.4565 0.01846 0.01229 -0.1052 0.9476 0.1230
-7.500 -0.4210 0.01784 0.01164 -0.1071 0.9400 0.1444
-7.250 -0.3801 0.01732 0.01112 -0.1099 0.9345 0.1638
-7.000 -0.3398 0.01691 0.01066 -0.1124 0.9292 0.1813
-6.750 -0.3031 0.01653 0.01024 -0.1142 0.9215 0.1965
-6.500 -0.2593 0.01620 0.00985 -0.1172 0.9178 0.2138
-6.250 -0.2241 0.01598 0.00960 -0.1184 0.9092 0.2289
-6.000 -0.1810 0.01569 0.00927 -0.1212 0.9040 0.2434
-5.750 -0.1374 0.01535 0.00889 -0.1241 0.8980 0.2561
-5.500 -0.0971 0.01505 0.00847 -0.1263 0.8888 0.2681
-5.250 -0.0551 0.01481 0.00820 -0.1288 0.8800 0.2795
-5.000 -0.0129 0.01453 0.00788 -0.1314 0.8699 0.2899
-4.750 0.0236 0.01434 0.00754 -0.1329 0.8564 0.3005
-4.500 0.0591 0.01420 0.00739 -0.1342 0.8426 0.3094
-4.250 0.0934 0.01405 0.00710 -0.1352 0.8285 0.3188
-4.000 0.1257 0.01399 0.00697 -0.1358 0.8141 0.3273
-3.750 0.1569 0.01390 0.00674 -0.1362 0.7998 0.3360
-3.500 0.1860 0.01389 0.00665 -0.1362 0.7852 0.3442
-3.250 0.2136 0.01383 0.00648 -0.1360 0.7705 0.3525
-3.000 0.2411 0.01382 0.00643 -0.1357 0.7562 0.3603
-2.750 0.2690 0.01379 0.00626 -0.1355 0.7427 0.3688
-2.500 0.2969 0.01379 0.00622 -0.1353 0.7301 0.3765
-2.250 0.3250 0.01380 0.00606 -0.1352 0.7176 0.3852
-2.000 0.3510 0.01377 0.00605 -0.1346 0.7044 0.3927
-1.750 0.3785 0.01381 0.00595 -0.1344 0.6923 0.4018
-1.500 0.4060 0.01380 0.00592 -0.1341 0.6813 0.4093
-1.000 0.4593 0.01383 0.00586 -0.1334 0.6578 0.4265
-0.500 0.5134 0.01389 0.00582 -0.1328 0.6366 0.4442
-0.250 0.5406 0.01396 0.00581 -0.1325 0.6264 0.4543
0.000 0.5678 0.01399 0.00582 -0.1323 0.6168 0.4631
0.250 0.5942 0.01404 0.00586 -0.1319 0.6066 0.4731
0.500 0.6221 0.01413 0.00589 -0.1318 0.5980 0.4835
0.750 0.6478 0.01416 0.00596 -0.1313 0.5879 0.4935
1.000 0.6755 0.01428 0.00600 -0.1311 0.5795 0.5054
1.250 0.7014 0.01431 0.00611 -0.1307 0.5704 0.5164
1.500 0.7288 0.01442 0.00619 -0.1305 0.5626 0.5285
1.750 0.7549 0.01449 0.00630 -0.1301 0.5538 0.5418
2.000 0.7824 0.01463 0.00640 -0.1299 0.5464 0.5565
2.250 0.8080 0.01469 0.00656 -0.1294 0.5381 0.5714
2.750 0.8608 0.01490 0.00688 -0.1287 0.5233 0.6073
3.000 0.8876 0.01500 0.00702 -0.1284 0.5166 0.6287
3.250 0.9128 0.01511 0.00726 -0.1279 0.5095 0.6538
3.500 0.9379 0.01519 0.00745 -0.1272 0.5028 0.6847
3.750 0.9634 0.01531 0.00767 -0.1266 0.4968 0.7249
4.000 0.9839 0.01532 0.00791 -0.1249 0.4898 0.7779
4.250 1.0005 0.01524 0.00801 -0.1221 0.4843 0.8640
4.500 1.0276 0.01531 0.00814 -0.1218 0.4784 1.0000
4.750 1.0545 0.01556 0.00838 -0.1217 0.4717 1.0000
5.000 1.0835 0.01587 0.00856 -0.1221 0.4660 1.0000
5.250 1.1088 0.01617 0.00890 -0.1217 0.4597 1.0000
5.500 1.1352 0.01644 0.00916 -0.1215 0.4537 1.0000
5.750 1.1644 0.01682 0.00941 -0.1218 0.4484 1.0000
6.000 1.1871 0.01709 0.00979 -0.1209 0.4420 1.0000
6.250 1.2132 0.01737 0.01006 -0.1207 0.4363 1.0000
6.500 1.2408 0.01776 0.01038 -0.1207 0.4309 1.0000
6.750 1.2631 0.01805 0.01078 -0.1198 0.4246 1.0000
7.000 1.2890 0.01835 0.01105 -0.1194 0.4190 1.0000
7.250 1.3148 0.01874 0.01144 -0.1192 0.4136 1.0000
7.500 1.3365 0.01905 0.01185 -0.1181 0.4073 1.0000
7.750 1.3622 0.01936 0.01213 -0.1178 0.4018 1.0000
8.000 1.3854 0.01976 0.01258 -0.1171 0.3960 1.0000
8.250 1.4067 0.02007 0.01297 -0.1160 0.3897 1.0000
8.500 1.4328 0.02041 0.01325 -0.1158 0.3840 1.0000
8.750 1.4514 0.02079 0.01376 -0.1142 0.3777 1.0000
9.000 1.4726 0.02108 0.01408 -0.1131 0.3712 1.0000
9.250 1.4956 0.02147 0.01447 -0.1124 0.3651 1.0000
9.500 1.5115 0.02180 0.01493 -0.1104 0.3582 1.0000
9.750 1.5339 0.02212 0.01520 -0.1095 0.3519 1.0000
10.000 1.5477 0.02252 0.01576 -0.1072 0.3449 1.0000
10.250 1.5642 0.02283 0.01610 -0.1054 0.3381 1.0000
10.500 1.5794 0.02325 0.01658 -0.1034 0.3313 1.0000
10.750 1.5886 0.02361 0.01703 -0.1003 0.3242 1.0000
11.000 1.6030 0.02404 0.01745 -0.0982 0.3174 1.0000
11.250 1.6082 0.02453 0.01810 -0.0947 0.3099 1.0000
11.500 1.6213 0.02503 0.01854 -0.0925 0.3028 1.0000
11.750 1.6238 0.02569 0.01940 -0.0889 0.2949 1.0000
12.000 1.6332 0.02634 0.01999 -0.0865 0.2874 1.0000
12.250 1.6346 0.02721 0.02106 -0.0831 0.2790 1.0000
12.500 1.6399 0.02813 0.02196 -0.0805 0.2709 1.0000
12.750 1.6410 0.02926 0.02323 -0.0776 0.2618 1.0000
13.000 1.6429 0.03053 0.02456 -0.0752 0.2531 1.0000
13.250 1.6427 0.03202 0.02608 -0.0727 0.2438 1.0000
13.500 1.6420 0.03372 0.02789 -0.0706 0.2339 1.0000
13.750 1.6393 0.03569 0.02988 -0.0686 0.2246 1.0000
14.000 1.6351 0.03795 0.03219 -0.0668 0.2144 1.0000
14.250 1.6304 0.04045 0.03477 -0.0654 0.2041 1.0000
14.500 1.6234 0.04332 0.03766 -0.0642 0.1944 1.0000
14.750 1.6145 0.04657 0.04091 -0.0632 0.1845 1.0000
15.000 1.6066 0.04995 0.04437 -0.0626 0.1746 1.0000
15.250 1.5963 0.05374 0.04819 -0.0623 0.1656 1.0000
15.500 1.5849 0.05785 0.05230 -0.0623 0.1568 1.0000
15.750 1.5751 0.06199 0.05653 -0.0625 0.1479 1.0000
16.000 1.5623 0.06660 0.06111 -0.0630 0.1404 1.0000
16.250 1.5523 0.07111 0.06571 -0.0637 0.1322 1.0000
16.500 1.5408 0.07590 0.07051 -0.0646 0.1252 1.0000
16.750 1.5297 0.08082 0.07548 -0.0657 0.1179 1.0000
17.000 1.5196 0.08568 0.08038 -0.0669 0.1115 1.0000
17.250 1.5092 0.09072 0.08546 -0.0684 0.1051 1.0000
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