EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 560 AIRFOIL (e560-il) Reynolds number: 200,000 Max Cl/Cd: 75.26 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e560-il-200000-n5.txt Download as CSV file: xf-e560-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 560 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.5489 0.12058 0.11615 -0.0507 1.0000 0.0210
-15.500 -0.5729 0.11193 0.10737 -0.0548 1.0000 0.0210
-15.250 -0.5888 0.10524 0.10056 -0.0579 1.0000 0.0210
-15.000 -0.6038 0.09894 0.09413 -0.0608 1.0000 0.0211
-14.750 -0.6095 0.09474 0.08989 -0.0624 1.0000 0.0213
-14.500 -0.6122 0.09124 0.08638 -0.0636 1.0000 0.0216
-14.250 -0.6162 0.08755 0.08267 -0.0649 1.0000 0.0219
-14.000 -0.6207 0.08386 0.07895 -0.0662 1.0000 0.0221
-13.750 -0.6260 0.08014 0.07520 -0.0674 1.0000 0.0223
-13.500 -0.6311 0.07662 0.07163 -0.0685 1.0000 0.0225
-13.250 -0.6365 0.07322 0.06819 -0.0694 1.0000 0.0226
-13.000 -0.6430 0.06985 0.06479 -0.0702 1.0000 0.0229
-12.750 -0.6501 0.06665 0.06155 -0.0707 1.0000 0.0230
-12.500 -0.6595 0.06345 0.05832 -0.0712 1.0000 0.0232
-12.250 -0.6701 0.06037 0.05520 -0.0713 1.0000 0.0234
-12.000 -0.6824 0.05738 0.05218 -0.0711 1.0000 0.0235
-11.750 -0.6981 0.05438 0.04917 -0.0705 1.0000 0.0236
-11.500 -0.7038 0.05099 0.04573 -0.0725 0.9981 0.0238
-11.250 -0.6943 0.04699 0.04162 -0.0784 0.9926 0.0243
-11.000 -0.6874 0.04305 0.03757 -0.0839 0.9850 0.0246
-10.750 -0.6784 0.03881 0.03321 -0.0900 0.9758 0.0249
-10.500 -0.6620 0.03411 0.02835 -0.0981 0.9664 0.0255
-10.250 -0.6338 0.02980 0.02385 -0.1076 0.9596 0.0262
-10.000 -0.6118 0.02754 0.02145 -0.1109 0.9505 0.0272
-9.750 -0.5835 0.02575 0.01951 -0.1141 0.9442 0.0287
-9.500 -0.5551 0.02423 0.01786 -0.1166 0.9372 0.0306
-9.250 -0.5206 0.02273 0.01628 -0.1200 0.9334 0.0336
-9.000 -0.4955 0.02152 0.01499 -0.1211 0.9242 0.0373
-8.500 -0.4327 0.01923 0.01260 -0.1250 0.9115 0.0536
-8.250 -0.3981 0.01828 0.01162 -0.1271 0.9059 0.0662
-8.000 -0.3647 0.01748 0.01080 -0.1289 0.8990 0.0789
-7.750 -0.3301 0.01677 0.01008 -0.1308 0.8918 0.0923
-7.500 -0.2908 0.01612 0.00940 -0.1335 0.8864 0.1066
-7.250 -0.2561 0.01560 0.00885 -0.1352 0.8773 0.1203
-7.000 -0.2123 0.01508 0.00830 -0.1386 0.8712 0.1368
-6.750 -0.1746 0.01470 0.00789 -0.1408 0.8608 0.1521
-6.500 -0.1316 0.01436 0.00748 -0.1440 0.8516 0.1673
-6.250 -0.0910 0.01407 0.00712 -0.1466 0.8403 0.1799
-6.000 -0.0535 0.01385 0.00678 -0.1486 0.8274 0.1903
-5.750 -0.0171 0.01366 0.00649 -0.1503 0.8143 0.2006
-5.500 0.0175 0.01351 0.00624 -0.1516 0.8006 0.2098
-5.250 0.0506 0.01341 0.00597 -0.1525 0.7870 0.2193
-5.000 0.0811 0.01331 0.00581 -0.1530 0.7728 0.2272
-4.750 0.1107 0.01324 0.00560 -0.1532 0.7589 0.2356
-4.500 0.1397 0.01317 0.00548 -0.1534 0.7456 0.2430
-4.250 0.1687 0.01314 0.00529 -0.1535 0.7328 0.2510
-3.750 0.2249 0.01308 0.00506 -0.1534 0.7077 0.2658
-3.500 0.2525 0.01305 0.00498 -0.1532 0.6956 0.2726
-3.250 0.2803 0.01306 0.00488 -0.1531 0.6841 0.2801
-3.000 0.3078 0.01305 0.00479 -0.1529 0.6725 0.2870
-2.750 0.3350 0.01306 0.00474 -0.1526 0.6613 0.2942
-2.500 0.3625 0.01309 0.00465 -0.1524 0.6506 0.3015
-2.250 0.3895 0.01309 0.00464 -0.1522 0.6398 0.3081
-2.000 0.4168 0.01313 0.00459 -0.1519 0.6297 0.3158
-1.750 0.4438 0.01316 0.00456 -0.1517 0.6197 0.3221
-1.500 0.4708 0.01319 0.00456 -0.1514 0.6095 0.3296
-1.250 0.4979 0.01325 0.00454 -0.1511 0.6003 0.3368
-1.000 0.5248 0.01329 0.00456 -0.1508 0.5907 0.3437
-0.750 0.5518 0.01336 0.00455 -0.1506 0.5817 0.3515
-0.500 0.5785 0.01341 0.00460 -0.1503 0.5726 0.3584
-0.250 0.6054 0.01349 0.00462 -0.1500 0.5642 0.3663
0.000 0.6321 0.01355 0.00467 -0.1497 0.5558 0.3735
0.250 0.6588 0.01364 0.00473 -0.1494 0.5478 0.3817
0.500 0.6854 0.01372 0.00479 -0.1490 0.5394 0.3895
0.750 0.7120 0.01381 0.00487 -0.1487 0.5319 0.3974
1.000 0.7386 0.01390 0.00495 -0.1484 0.5242 0.4060
1.250 0.7650 0.01402 0.00505 -0.1481 0.5172 0.4146
1.500 0.7914 0.01411 0.00515 -0.1477 0.5095 0.4235
1.750 0.8175 0.01423 0.00526 -0.1473 0.5027 0.4328
2.000 0.8440 0.01433 0.00540 -0.1470 0.4960 0.4426
2.250 0.8701 0.01446 0.00553 -0.1466 0.4893 0.4530
2.500 0.8961 0.01459 0.00568 -0.1463 0.4830 0.4635
2.750 0.9221 0.01471 0.00585 -0.1459 0.4762 0.4754
3.000 0.9479 0.01486 0.00601 -0.1454 0.4704 0.4883
3.250 0.9738 0.01500 0.00620 -0.1451 0.4646 0.5017
3.500 0.9992 0.01513 0.00640 -0.1446 0.4583 0.5169
3.750 1.0244 0.01530 0.00659 -0.1440 0.4528 0.5340
4.000 1.0499 0.01544 0.00683 -0.1436 0.4471 0.5531
4.250 1.0750 0.01559 0.00706 -0.1430 0.4414 0.5754
4.500 1.0996 0.01576 0.00730 -0.1424 0.4363 0.6009
4.750 1.1242 0.01590 0.00757 -0.1418 0.4308 0.6316
5.000 1.1480 0.01603 0.00784 -0.1410 0.4253 0.6690
5.250 1.1708 0.01618 0.00810 -0.1400 0.4205 0.7165
5.500 1.1914 0.01626 0.00837 -0.1384 0.4155 0.7811
5.750 1.2042 0.01610 0.00847 -0.1350 0.4106 0.9837
6.000 1.2292 0.01639 0.00874 -0.1345 0.4056 1.0000
6.250 1.2534 0.01670 0.00902 -0.1340 0.4008 1.0000
6.500 1.2772 0.01697 0.00934 -0.1333 0.3952 1.0000
6.750 1.3003 0.01728 0.00964 -0.1325 0.3901 1.0000
7.000 1.3232 0.01762 0.00995 -0.1317 0.3855 1.0000
7.250 1.3455 0.01791 0.01031 -0.1308 0.3799 1.0000
7.500 1.3665 0.01823 0.01066 -0.1296 0.3746 1.0000
7.750 1.3872 0.01860 0.01099 -0.1284 0.3699 1.0000
8.000 1.4073 0.01891 0.01140 -0.1271 0.3642 1.0000
8.250 1.4265 0.01927 0.01179 -0.1257 0.3586 1.0000
8.500 1.4453 0.01968 0.01218 -0.1243 0.3535 1.0000
8.750 1.4639 0.02004 0.01265 -0.1228 0.3474 1.0000
9.000 1.4810 0.02046 0.01309 -0.1211 0.3415 1.0000
9.250 1.4980 0.02091 0.01357 -0.1194 0.3358 1.0000
9.500 1.5144 0.02135 0.01410 -0.1176 0.3292 1.0000
9.750 1.5291 0.02188 0.01463 -0.1157 0.3232 1.0000
10.000 1.5446 0.02239 0.01523 -0.1139 0.3166 1.0000
10.250 1.5583 0.02296 0.01585 -0.1119 0.3100 1.0000
10.500 1.5714 0.02359 0.01654 -0.1099 0.3035 1.0000
10.750 1.5838 0.02426 0.01728 -0.1079 0.2962 1.0000
11.000 1.5942 0.02504 0.01809 -0.1057 0.2892 1.0000
11.250 1.6048 0.02585 0.01898 -0.1036 0.2810 1.0000
11.500 1.6129 0.02681 0.01997 -0.1013 0.2732 1.0000
11.750 1.6211 0.02783 0.02106 -0.0992 0.2644 1.0000
12.000 1.6278 0.02899 0.02228 -0.0971 0.2561 1.0000
12.250 1.6326 0.03033 0.02366 -0.0949 0.2470 1.0000
12.500 1.6378 0.03174 0.02513 -0.0930 0.2378 1.0000
12.750 1.6393 0.03347 0.02688 -0.0910 0.2288 1.0000
13.000 1.6414 0.03527 0.02874 -0.0892 0.2187 1.0000
13.250 1.6418 0.03731 0.03083 -0.0876 0.2091 1.0000
13.500 1.6386 0.03976 0.03329 -0.0860 0.1994 1.0000
13.750 1.6364 0.04229 0.03588 -0.0847 0.1893 1.0000
14.000 1.6324 0.04513 0.03875 -0.0836 0.1794 1.0000
14.250 1.6252 0.04843 0.04208 -0.0826 0.1699 1.0000
14.500 1.6185 0.05185 0.04554 -0.0820 0.1603 1.0000
14.750 1.6116 0.05546 0.04919 -0.0816 0.1513 1.0000
15.000 1.6012 0.05963 0.05338 -0.0815 0.1428 1.0000
15.250 1.5931 0.06369 0.05750 -0.0816 0.1342 1.0000
15.500 1.5836 0.06810 0.06195 -0.0819 0.1264 1.0000
15.750 1.5725 0.07284 0.06673 -0.0825 0.1187 1.0000
16.000 1.5639 0.07738 0.07134 -0.0833 0.1115 1.0000
16.250 1.5514 0.08263 0.07662 -0.0843 0.1049 1.0000
16.500 1.5437 0.08728 0.08134 -0.0854 0.0979 1.0000
16.750 1.5318 0.09265 0.08676 -0.0868 0.0921 1.0000
17.000 1.5252 0.09732 0.09150 -0.0881 0.0860 1.0000
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Polar data table (+)
Polar graphs
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