EPPLER 580 AIRFOIL (e580-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 580 AIRFOIL (e580-il) Reynolds number: 200,000 Max Cl/Cd: 76.08 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e580-il-200000-n5.txt Download as CSV file: xf-e580-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3402 0.09259 0.08900 -0.0701 0.9893 0.0190
-10.750 -0.3522 0.08102 0.07742 -0.0785 0.9862 0.0186
-10.500 -0.3788 0.06820 0.06444 -0.0903 0.9814 0.0183
-10.250 -0.3969 0.06012 0.05616 -0.0985 0.9743 0.0181
-10.000 -0.4133 0.05395 0.04977 -0.1041 0.9651 0.0180
-9.750 -0.4255 0.04902 0.04459 -0.1082 0.9550 0.0180
-9.500 -0.4342 0.04493 0.04023 -0.1109 0.9437 0.0180
-9.250 -0.4318 0.04086 0.03582 -0.1137 0.9335 0.0180
-9.000 -0.4269 0.03775 0.03233 -0.1143 0.9233 0.0185
-8.750 -0.4075 0.03464 0.02874 -0.1167 0.9187 0.0189
-8.500 -0.3937 0.03246 0.02620 -0.1165 0.9097 0.0192
-8.250 -0.3677 0.03018 0.02359 -0.1181 0.9056 0.0192
-8.000 -0.3440 0.02828 0.02143 -0.1187 0.8997 0.0194
-7.750 -0.3190 0.02635 0.01934 -0.1193 0.8938 0.0196
-7.500 -0.2870 0.02473 0.01758 -0.1209 0.8904 0.0199
-7.250 -0.2598 0.02347 0.01621 -0.1215 0.8841 0.0202
-7.000 -0.2296 0.02234 0.01499 -0.1225 0.8784 0.0206
-6.750 -0.1928 0.02121 0.01378 -0.1248 0.8748 0.0211
-6.500 -0.1653 0.02033 0.01282 -0.1252 0.8671 0.0216
-6.250 -0.1312 0.01942 0.01183 -0.1270 0.8613 0.0224
-6.000 -0.0990 0.01868 0.01101 -0.1284 0.8545 0.0236
-5.750 -0.0670 0.01796 0.01022 -0.1298 0.8471 0.0245
-5.500 -0.0348 0.01707 0.00928 -0.1316 0.8396 0.0254
-5.250 -0.0030 0.01639 0.00853 -0.1331 0.8313 0.0264
-5.000 0.0288 0.01583 0.00788 -0.1345 0.8230 0.0277
-4.750 0.0615 0.01533 0.00725 -0.1360 0.8146 0.0294
-4.500 0.0917 0.01488 0.00672 -0.1370 0.8056 0.0318
-4.250 0.1247 0.01447 0.00622 -0.1384 0.7975 0.0372
-4.000 0.1540 0.01392 0.00578 -0.1394 0.7881 0.0620
-3.750 0.1874 0.01297 0.00521 -0.1419 0.7799 0.1718
-3.500 0.2201 0.01169 0.00498 -0.1448 0.7708 0.4410
-3.250 0.2499 0.01186 0.00517 -0.1450 0.7624 0.5022
-3.000 0.2783 0.01226 0.00552 -0.1447 0.7535 0.5412
-2.750 0.3048 0.01276 0.00600 -0.1439 0.7449 0.5657
-2.500 0.3339 0.01293 0.00603 -0.1440 0.7366 0.5764
-2.250 0.3618 0.01293 0.00593 -0.1440 0.7282 0.5792
-2.000 0.3905 0.01295 0.00583 -0.1442 0.7202 0.5815
-1.750 0.4180 0.01296 0.00576 -0.1442 0.7119 0.5842
-1.500 0.4472 0.01298 0.00565 -0.1445 0.7042 0.5871
-1.250 0.4752 0.01298 0.00556 -0.1447 0.6960 0.5901
-1.000 0.5048 0.01301 0.00543 -0.1452 0.6887 0.5935
-0.750 0.5315 0.01303 0.00542 -0.1451 0.6807 0.5954
-0.500 0.5596 0.01308 0.00539 -0.1452 0.6735 0.5973
-0.250 0.5867 0.01312 0.00540 -0.1451 0.6659 0.5997
0.000 0.6147 0.01318 0.00538 -0.1452 0.6588 0.6025
0.250 0.6424 0.01324 0.00538 -0.1453 0.6515 0.6053
0.500 0.6706 0.01330 0.00536 -0.1456 0.6444 0.6080
0.750 0.6981 0.01336 0.00538 -0.1456 0.6375 0.6103
1.000 0.7248 0.01343 0.00544 -0.1455 0.6303 0.6125
1.250 0.7520 0.01353 0.00550 -0.1454 0.6238 0.6149
1.500 0.7786 0.01361 0.00558 -0.1453 0.6165 0.6173
2.000 0.8329 0.01380 0.00571 -0.1454 0.6028 0.6227
2.250 0.8602 0.01391 0.00577 -0.1454 0.5961 0.6256
2.500 0.8861 0.01401 0.00592 -0.1451 0.5891 0.6278
2.750 0.9123 0.01413 0.00604 -0.1449 0.5822 0.6302
3.000 0.9385 0.01425 0.00617 -0.1447 0.5754 0.6327
3.250 0.9645 0.01438 0.00631 -0.1445 0.5682 0.6355
3.500 0.9908 0.01452 0.00644 -0.1444 0.5615 0.6386
3.750 1.0163 0.01466 0.00660 -0.1441 0.5539 0.6416
4.000 1.0417 0.01481 0.00676 -0.1437 0.5471 0.6441
4.250 1.0661 0.01495 0.00698 -0.1432 0.5390 0.6468
4.500 1.0912 0.01512 0.00715 -0.1429 0.5319 0.6498
4.750 1.1154 0.01528 0.00736 -0.1423 0.5235 0.6529
5.000 1.1400 0.01547 0.00756 -0.1419 0.5159 0.6563
5.250 1.1629 0.01564 0.00781 -0.1411 0.5071 0.6592
5.500 1.1861 0.01584 0.00804 -0.1404 0.4990 0.6625
5.750 1.2085 0.01604 0.00829 -0.1395 0.4897 0.6661
6.000 1.2308 0.01626 0.00857 -0.1386 0.4805 0.6699
6.250 1.2523 0.01650 0.00882 -0.1376 0.4710 0.6734
6.500 1.2727 0.01673 0.00913 -0.1364 0.4604 0.6766
6.750 1.2926 0.01699 0.00944 -0.1351 0.4502 0.6804
7.000 1.3107 0.01728 0.00976 -0.1335 0.4397 0.6849
7.250 1.3281 0.01757 0.01011 -0.1317 0.4283 0.6894
7.500 1.3448 0.01789 0.01050 -0.1299 0.4169 0.6937
7.750 1.3610 0.01828 0.01092 -0.1280 0.4053 0.6986
8.250 1.3912 0.01917 0.01189 -0.1240 0.3805 0.7085
8.500 1.4057 0.01967 0.01244 -0.1220 0.3675 0.7142
8.750 1.4194 0.02023 0.01303 -0.1199 0.3543 0.7203
9.000 1.4319 0.02083 0.01370 -0.1177 0.3410 0.7265
9.250 1.4436 0.02151 0.01441 -0.1155 0.3274 0.7342
9.500 1.4539 0.02226 0.01520 -0.1131 0.3135 0.7417
10.000 1.4706 0.02404 0.01705 -0.1081 0.2835 0.7598
10.250 1.4768 0.02511 0.01814 -0.1055 0.2670 0.7704
10.500 1.4813 0.02632 0.01938 -0.1028 0.2501 0.7830
10.750 1.4845 0.02765 0.02073 -0.1002 0.2334 0.7981
11.000 1.4855 0.02916 0.02226 -0.0974 0.2164 0.8182
11.500 1.4789 0.03223 0.02545 -0.0909 0.1856 1.0000
11.750 1.4801 0.03427 0.02746 -0.0892 0.1690 1.0000
12.000 1.4801 0.03650 0.02964 -0.0875 0.1530 1.0000
12.250 1.4801 0.03884 0.03195 -0.0861 0.1388 1.0000
12.500 1.4799 0.04131 0.03440 -0.0848 0.1255 1.0000
12.750 1.4793 0.04392 0.03701 -0.0837 0.1135 1.0000
13.000 1.4783 0.04667 0.03975 -0.0827 0.1026 1.0000
13.250 1.4775 0.04950 0.04258 -0.0820 0.0919 1.0000
13.500 1.4772 0.05237 0.04548 -0.0814 0.0823 1.0000
13.750 1.4763 0.05540 0.04853 -0.0809 0.0739 1.0000
14.000 1.4745 0.05863 0.05178 -0.0806 0.0664 1.0000
14.250 1.4742 0.06177 0.05498 -0.0805 0.0595 1.0000
14.500 1.4728 0.06514 0.05840 -0.0805 0.0534 1.0000
14.750 1.4696 0.06880 0.06209 -0.0806 0.0471 1.0000
15.000 1.4676 0.07242 0.06578 -0.0808 0.0410 1.0000
15.250 1.4637 0.07638 0.06979 -0.0813 0.0354 1.0000
15.500 1.4587 0.08058 0.07404 -0.0819 0.0304 1.0000
15.750 1.4546 0.08475 0.07828 -0.0826 0.0258 1.0000
16.000 1.4495 0.08915 0.08276 -0.0835 0.0221 1.0000
16.250 1.4435 0.09380 0.08747 -0.0846 0.0192 1.0000
16.500 1.4392 0.09826 0.09205 -0.0858 0.0170 1.0000
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Polar data table (+)
Polar graphs
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