EPPLER 580 AIRFOIL (e580-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 580 AIRFOIL (e580-il) Reynolds number: 200,000 Max Cl/Cd: 76.09 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e580-il-200000.txt Download as CSV file: xf-e580-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 580 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3814 0.07792 0.07460 -0.0885 0.9712 0.0699
-8.750 -0.4031 0.07286 0.06926 -0.0972 0.9548 0.0702
-8.500 -0.3906 0.06531 0.06186 -0.0986 0.9512 0.0722
-8.250 -0.3609 0.06279 0.05941 -0.0993 0.9488 0.0744
-8.000 -0.3534 0.05867 0.05517 -0.1034 0.9395 0.0769
-7.750 -0.3655 0.05445 0.05004 -0.1114 0.9245 0.0844
-7.500 -0.3382 0.04918 0.04502 -0.1130 0.9220 0.0868
-7.250 -0.3071 0.04620 0.04200 -0.1161 0.9194 0.0916
-7.000 -0.2947 0.04311 0.03860 -0.1179 0.9097 0.1016
-6.750 -0.2583 0.03124 0.02499 -0.1198 0.9064 0.0445
-6.500 -0.2204 0.02772 0.02105 -0.1222 0.9047 0.0415
-6.250 -0.1957 0.02569 0.01868 -0.1216 0.8971 0.0401
-6.000 -0.1598 0.02394 0.01676 -0.1230 0.8938 0.0398
-5.750 -0.1209 0.02240 0.01512 -0.1249 0.8917 0.0402
-5.500 -0.0796 0.02104 0.01373 -0.1274 0.8901 0.0412
-5.250 -0.0516 0.02026 0.01293 -0.1276 0.8829 0.0435
-5.000 -0.0137 0.01925 0.01188 -0.1296 0.8788 0.0453
-4.750 0.0283 0.01820 0.01078 -0.1324 0.8759 0.0469
-4.500 0.0641 0.01694 0.00954 -0.1349 0.8703 0.0506
-4.250 0.0995 0.01617 0.00871 -0.1368 0.8634 0.0562
-4.000 0.1512 0.01294 0.00696 -0.1453 0.8599 0.3804
-3.750 0.1807 0.01330 0.00762 -0.1450 0.8510 0.5245
-3.500 0.2170 0.01373 0.00797 -0.1457 0.8450 0.5540
-3.250 0.2440 0.01422 0.00840 -0.1448 0.8359 0.5728
-3.000 0.2744 0.01500 0.00918 -0.1437 0.8291 0.5959
-2.750 0.2915 0.01605 0.01034 -0.1395 0.8192 0.6146
-2.500 0.3206 0.01660 0.01083 -0.1383 0.8126 0.6289
-2.250 0.3441 0.01665 0.01082 -0.1372 0.8026 0.6337
-2.000 0.3814 0.01637 0.01033 -0.1398 0.7956 0.6400
-1.750 0.4074 0.01626 0.01014 -0.1395 0.7861 0.6431
-1.500 0.4366 0.01620 0.00999 -0.1397 0.7785 0.6457
-1.250 0.4645 0.01612 0.00983 -0.1398 0.7698 0.6491
-1.000 0.4955 0.01600 0.00958 -0.1408 0.7619 0.6530
-0.750 0.5277 0.01583 0.00927 -0.1423 0.7537 0.6573
-0.500 0.5546 0.01579 0.00919 -0.1421 0.7459 0.6595
-0.250 0.5827 0.01575 0.00909 -0.1422 0.7381 0.6619
0.000 0.6109 0.01573 0.00901 -0.1425 0.7304 0.6648
0.250 0.6406 0.01569 0.00888 -0.1432 0.7227 0.6686
0.500 0.6721 0.01564 0.00873 -0.1445 0.7152 0.6724
0.750 0.6991 0.01561 0.00867 -0.1444 0.7075 0.6745
1.000 0.7268 0.01564 0.00867 -0.1444 0.7005 0.6770
1.250 0.7535 0.01567 0.00868 -0.1444 0.6926 0.6800
1.500 0.7835 0.01570 0.00864 -0.1450 0.6859 0.6833
1.750 0.8114 0.01572 0.00863 -0.1454 0.6779 0.6866
2.000 0.8424 0.01574 0.00857 -0.1463 0.6715 0.6894
2.250 0.8660 0.01579 0.00868 -0.1456 0.6632 0.6920
2.500 0.8965 0.01586 0.00868 -0.1462 0.6570 0.6951
2.750 0.9206 0.01594 0.00882 -0.1457 0.6486 0.6982
3.000 0.9520 0.01600 0.00879 -0.1467 0.6421 0.7016
3.250 0.9771 0.01608 0.00893 -0.1464 0.6338 0.7048
3.500 1.0053 0.01615 0.00897 -0.1465 0.6270 0.7076
3.750 1.0292 0.01627 0.00916 -0.1459 0.6189 0.7109
4.000 1.0582 0.01635 0.00922 -0.1464 0.6117 0.7145
4.250 1.0837 0.01648 0.00938 -0.1462 0.6033 0.7182
4.500 1.1120 0.01656 0.00944 -0.1464 0.5959 0.7213
4.750 1.1347 0.01669 0.00966 -0.1456 0.5874 0.7246
5.000 1.1628 0.01681 0.00976 -0.1458 0.5799 0.7286
5.250 1.1862 0.01696 0.00999 -0.1451 0.5708 0.7330
5.500 1.2150 0.01708 0.01006 -0.1455 0.5631 0.7366
5.750 1.2352 0.01720 0.01033 -0.1442 0.5534 0.7401
6.000 1.2604 0.01735 0.01049 -0.1438 0.5448 0.7444
6.250 1.2843 0.01749 0.01066 -0.1433 0.5352 0.7495
6.500 1.3056 0.01764 0.01090 -0.1421 0.5255 0.7538
6.750 1.3307 0.01779 0.01105 -0.1417 0.5164 0.7586
7.000 1.3499 0.01796 0.01133 -0.1403 0.5055 0.7640
7.250 1.3705 0.01814 0.01158 -0.1391 0.4952 0.7689
7.500 1.3923 0.01832 0.01177 -0.1381 0.4850 0.7744
7.750 1.4103 0.01854 0.01208 -0.1365 0.4734 0.7812
8.000 1.4266 0.01875 0.01240 -0.1344 0.4620 0.7873
8.250 1.4443 0.01901 0.01271 -0.1328 0.4505 0.7952
8.500 1.4601 0.01927 0.01300 -0.1307 0.4388 0.8025
8.750 1.4724 0.01956 0.01337 -0.1281 0.4264 0.8116
9.000 1.4831 0.01989 0.01381 -0.1251 0.4139 0.8208
9.250 1.4942 0.02029 0.01428 -0.1224 0.4012 0.8321
9.500 1.5037 0.02073 0.01479 -0.1194 0.3880 0.8462
9.750 1.5113 0.02121 0.01533 -0.1162 0.3745 0.8644
10.000 1.5152 0.02168 0.01589 -0.1123 0.3609 0.8953
10.250 1.5180 0.02220 0.01648 -0.1086 0.3464 1.0000
10.500 1.5269 0.02315 0.01742 -0.1065 0.3296 1.0000
10.750 1.5332 0.02423 0.01847 -0.1041 0.3125 1.0000
11.000 1.5370 0.02546 0.01968 -0.1015 0.2947 1.0000
11.250 1.5389 0.02688 0.02105 -0.0988 0.2768 1.0000
11.500 1.5394 0.02849 0.02261 -0.0961 0.2594 1.0000
11.750 1.5398 0.03023 0.02432 -0.0937 0.2424 1.0000
12.000 1.5394 0.03216 0.02622 -0.0914 0.2244 1.0000
12.250 1.5379 0.03428 0.02834 -0.0893 0.2074 1.0000
12.500 1.5355 0.03661 0.03063 -0.0874 0.1912 1.0000
12.750 1.5324 0.03915 0.03314 -0.0857 0.1758 1.0000
13.000 1.5293 0.04182 0.03580 -0.0843 0.1615 1.0000
13.250 1.5261 0.04465 0.03861 -0.0830 0.1481 1.0000
13.500 1.5229 0.04760 0.04157 -0.0820 0.1358 1.0000
13.750 1.5196 0.05069 0.04467 -0.0812 0.1246 1.0000
14.000 1.5151 0.05404 0.04802 -0.0806 0.1143 1.0000
14.250 1.5105 0.05753 0.05152 -0.0802 0.1043 1.0000
14.500 1.5075 0.06096 0.05500 -0.0800 0.0941 1.0000
14.750 1.5028 0.06469 0.05876 -0.0799 0.0843 1.0000
15.000 1.4965 0.06876 0.06286 -0.0800 0.0747 1.0000
15.250 1.4882 0.07323 0.06734 -0.0804 0.0647 1.0000
15.500 1.4774 0.07817 0.07228 -0.0810 0.0546 1.0000
15.750 1.4640 0.08366 0.07776 -0.0819 0.0452 1.0000
16.000 1.4483 0.08966 0.08376 -0.0832 0.0383 1.0000
16.250 1.4369 0.09519 0.08937 -0.0844 0.0329 1.0000
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Polar data table (+)
Polar graphs
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