EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 560 AIRFOIL (e560-il) Reynolds number: 100,000 Max Cl/Cd: 54.55 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e560-il-100000-n5.txt Download as CSV file: xf-e560-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5008 0.08832 0.08269 -0.0627 1.0000 0.0383
-12.250 -0.5290 0.08065 0.07491 -0.0660 1.0000 0.0385
-12.000 -0.5480 0.07528 0.06947 -0.0678 1.0000 0.0388
-11.750 -0.5645 0.07072 0.06485 -0.0690 1.0000 0.0391
-11.500 -0.5795 0.06679 0.06086 -0.0696 1.0000 0.0395
-11.250 -0.5954 0.06312 0.05714 -0.0698 1.0000 0.0401
-11.000 -0.6109 0.05996 0.05396 -0.0693 1.0000 0.0404
-10.750 -0.6287 0.05705 0.05102 -0.0684 1.0000 0.0407
-10.500 -0.6512 0.05428 0.04825 -0.0667 1.0000 0.0409
-10.250 -0.6759 0.05175 0.04572 -0.0648 0.9994 0.0409
-10.000 -0.6619 0.04790 0.04174 -0.0710 0.9911 0.0422
-9.750 -0.6422 0.04365 0.03740 -0.0792 0.9826 0.0439
-9.500 -0.6198 0.03924 0.03282 -0.0876 0.9731 0.0464
-9.250 -0.5957 0.03585 0.02924 -0.0937 0.9635 0.0498
-9.000 -0.5695 0.03298 0.02624 -0.0990 0.9548 0.0551
-8.750 -0.5373 0.03050 0.02366 -0.1042 0.9481 0.0635
-8.500 -0.5095 0.02858 0.02164 -0.1073 0.9391 0.0737
-8.250 -0.4725 0.02696 0.01989 -0.1113 0.9339 0.0875
-8.000 -0.4436 0.02580 0.01863 -0.1132 0.9246 0.1002
-7.750 -0.4053 0.02474 0.01748 -0.1165 0.9195 0.1154
-7.500 -0.3753 0.02401 0.01673 -0.1180 0.9102 0.1318
-7.250 -0.3369 0.02341 0.01607 -0.1208 0.9048 0.1503
-7.000 -0.3057 0.02293 0.01550 -0.1219 0.8959 0.1636
-6.750 -0.2685 0.02235 0.01478 -0.1240 0.8899 0.1757
-6.500 -0.2349 0.02184 0.01408 -0.1253 0.8817 0.1873
-6.250 -0.1988 0.02145 0.01367 -0.1270 0.8745 0.1975
-6.000 -0.1631 0.02104 0.01316 -0.1285 0.8667 0.2082
-5.750 -0.1263 0.02061 0.01254 -0.1303 0.8585 0.2196
-5.500 -0.0894 0.02033 0.01222 -0.1319 0.8503 0.2294
-5.250 -0.0516 0.01998 0.01176 -0.1338 0.8415 0.2394
-5.000 -0.0149 0.01967 0.01127 -0.1355 0.8319 0.2501
-4.750 0.0240 0.01940 0.01095 -0.1374 0.8230 0.2588
-4.500 0.0579 0.01912 0.01050 -0.1386 0.8114 0.2687
-4.250 0.0950 0.01892 0.01024 -0.1402 0.8014 0.2772
-4.000 0.1304 0.01869 0.00985 -0.1415 0.7901 0.2865
-3.750 0.1624 0.01856 0.00966 -0.1422 0.7780 0.2947
-3.500 0.1969 0.01838 0.00934 -0.1433 0.7667 0.3036
-3.250 0.2304 0.01826 0.00912 -0.1442 0.7554 0.3120
-3.000 0.2605 0.01815 0.00891 -0.1446 0.7430 0.3203
-2.750 0.2915 0.01808 0.00876 -0.1451 0.7315 0.3283
-2.500 0.3238 0.01799 0.00852 -0.1458 0.7208 0.3369
-2.250 0.3515 0.01796 0.00846 -0.1456 0.7087 0.3444
-2.000 0.3813 0.01792 0.00828 -0.1459 0.6976 0.3533
-1.750 0.4111 0.01789 0.00820 -0.1461 0.6873 0.3608
-1.500 0.4387 0.01789 0.00810 -0.1460 0.6758 0.3698
-1.250 0.4671 0.01789 0.00808 -0.1460 0.6657 0.3773
-1.000 0.4957 0.01790 0.00797 -0.1460 0.6554 0.3868
-0.750 0.5225 0.01793 0.00801 -0.1457 0.6452 0.3942
-0.250 0.5775 0.01801 0.00799 -0.1454 0.6257 0.4117
0.000 0.6060 0.01807 0.00795 -0.1454 0.6171 0.4219
0.250 0.6318 0.01813 0.00804 -0.1449 0.6075 0.4302
0.500 0.6594 0.01821 0.00806 -0.1448 0.5990 0.4404
0.750 0.6855 0.01829 0.00816 -0.1444 0.5900 0.4499
1.000 0.7126 0.01839 0.00823 -0.1442 0.5820 0.4602
1.250 0.7389 0.01850 0.00834 -0.1438 0.5734 0.4713
1.500 0.7658 0.01861 0.00845 -0.1435 0.5659 0.4821
1.750 0.7915 0.01874 0.00861 -0.1431 0.5575 0.4940
2.000 0.8189 0.01888 0.00870 -0.1429 0.5507 0.5073
2.250 0.8436 0.01902 0.00894 -0.1423 0.5426 0.5202
2.500 0.8707 0.01917 0.00907 -0.1421 0.5360 0.5349
2.750 0.8955 0.01934 0.00932 -0.1415 0.5283 0.5505
3.000 0.9215 0.01950 0.00952 -0.1411 0.5216 0.5683
3.250 0.9473 0.01968 0.00974 -0.1407 0.5152 0.5886
3.500 0.9718 0.01987 0.01002 -0.1400 0.5081 0.6114
3.750 0.9978 0.02002 0.01023 -0.1395 0.5023 0.6384
4.000 1.0204 0.02021 0.01058 -0.1385 0.4955 0.6706
4.250 1.0432 0.02035 0.01086 -0.1374 0.4894 0.7113
4.500 1.0648 0.02044 0.01107 -0.1359 0.4843 0.7666
4.750 1.0774 0.02043 0.01134 -0.1326 0.4780 0.8615
5.000 1.1022 0.02059 0.01151 -0.1320 0.4721 1.0000
5.250 1.1296 0.02096 0.01181 -0.1320 0.4669 1.0000
5.500 1.1531 0.02137 0.01225 -0.1315 0.4604 1.0000
5.750 1.1790 0.02173 0.01257 -0.1312 0.4548 1.0000
6.000 1.2045 0.02213 0.01295 -0.1309 0.4496 1.0000
6.250 1.2270 0.02257 0.01346 -0.1302 0.4433 1.0000
6.500 1.2521 0.02296 0.01383 -0.1298 0.4380 1.0000
6.750 1.2760 0.02339 0.01427 -0.1293 0.4328 1.0000
7.000 1.2970 0.02388 0.01485 -0.1283 0.4267 1.0000
7.250 1.3213 0.02428 0.01524 -0.1277 0.4214 1.0000
7.500 1.3435 0.02476 0.01575 -0.1269 0.4161 1.0000
7.750 1.3628 0.02528 0.01639 -0.1257 0.4101 1.0000
8.000 1.3860 0.02570 0.01680 -0.1250 0.4048 1.0000
8.250 1.4058 0.02622 0.01740 -0.1238 0.3993 1.0000
8.500 1.4231 0.02678 0.01807 -0.1222 0.3931 1.0000
8.750 1.4453 0.02720 0.01850 -0.1214 0.3878 1.0000
9.000 1.4605 0.02782 0.01923 -0.1195 0.3819 1.0000
9.250 1.4749 0.02838 0.01988 -0.1175 0.3757 1.0000
9.500 1.4965 0.02878 0.02027 -0.1166 0.3704 1.0000
9.750 1.5032 0.02956 0.02123 -0.1135 0.3639 1.0000
10.000 1.5167 0.03015 0.02189 -0.1114 0.3577 1.0000
10.250 1.5310 0.03075 0.02254 -0.1095 0.3518 1.0000
10.500 1.5367 0.03162 0.02357 -0.1066 0.3449 1.0000
10.750 1.5515 0.03218 0.02415 -0.1048 0.3389 1.0000
11.000 1.5545 0.03326 0.02541 -0.1018 0.3320 1.0000
11.250 1.5621 0.03414 0.02637 -0.0994 0.3253 1.0000
11.500 1.5687 0.03517 0.02749 -0.0970 0.3188 1.0000
11.750 1.5705 0.03648 0.02894 -0.0944 0.3116 1.0000
12.000 1.5781 0.03753 0.03003 -0.0924 0.3049 1.0000
12.250 1.5747 0.03934 0.03203 -0.0898 0.2973 1.0000
12.500 1.5811 0.04056 0.03327 -0.0880 0.2904 1.0000
12.750 1.5739 0.04294 0.03586 -0.0857 0.2823 1.0000
13.000 1.5772 0.04454 0.03746 -0.0841 0.2750 1.0000
13.250 1.5676 0.04747 0.04061 -0.0825 0.2667 1.0000
13.500 1.5673 0.04963 0.04279 -0.0812 0.2590 1.0000
13.750 1.5566 0.05307 0.04640 -0.0801 0.2506 1.0000
14.000 1.5521 0.05597 0.04936 -0.0793 0.2426 1.0000
14.250 1.5415 0.05978 0.05330 -0.0789 0.2340 1.0000
14.500 1.5329 0.06355 0.05715 -0.0787 0.2258 1.0000
14.750 1.5243 0.06745 0.06114 -0.0787 0.2173 1.0000
15.000 1.5117 0.07216 0.06596 -0.0791 0.2089 1.0000
15.250 1.5066 0.07582 0.06961 -0.0794 0.2007 1.0000
15.500 1.4908 0.08140 0.07536 -0.0805 0.1923 1.0000
15.750 1.4840 0.08559 0.07957 -0.0812 0.1842 1.0000
16.000 1.4716 0.09090 0.08497 -0.0825 0.1760 1.0000
16.250 1.4637 0.09555 0.08966 -0.0837 0.1682 1.0000
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