EPPLER 862 STRUT AIRFOIL (e862-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 862 STRUT AIRFOIL (e862-il) Reynolds number: 500,000 Max Cl/Cd: 54.92 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e862-il-500000-n5.txt Download as CSV file: xf-e862-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 862 STRUT AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -1.1751 0.09329 0.08864 0.0019 1.0000 0.1957
-18.250 -1.1758 0.09021 0.08556 0.0012 1.0000 0.1994
-18.000 -1.1762 0.08715 0.08245 0.0004 1.0000 0.2028
-17.750 -1.1806 0.08526 0.08020 0.0018 0.8186 0.2057
-17.500 -1.1819 0.08245 0.07723 0.0015 0.7761 0.2094
-17.250 -1.1839 0.07942 0.07406 0.0010 0.7512 0.2132
-16.750 -1.1837 0.07376 0.06820 0.0000 0.7131 0.2201
-16.500 -1.1847 0.07087 0.06524 -0.0004 0.6977 0.2240
-16.250 -1.1859 0.06794 0.06221 -0.0008 0.6821 0.2280
-16.000 -1.1865 0.06509 0.05927 -0.0012 0.6692 0.2314
-15.750 -1.1876 0.06228 0.05642 -0.0015 0.6563 0.2352
-15.500 -1.1914 0.05916 0.05323 -0.0019 0.6465 0.2394
-15.250 -1.1901 0.05656 0.05052 -0.0022 0.6358 0.2431
-15.000 -1.1931 0.05363 0.04754 -0.0024 0.6264 0.2468
-14.750 -1.1948 0.05085 0.04473 -0.0026 0.6184 0.2508
-14.500 -1.1957 0.04814 0.04193 -0.0027 0.6096 0.2547
-14.000 -1.1955 0.04309 0.03676 -0.0029 0.5944 0.2619
-13.750 -1.1966 0.04051 0.03413 -0.0029 0.5867 0.2658
-13.500 -1.1932 0.03838 0.03190 -0.0029 0.5786 0.2695
-13.250 -1.1885 0.03641 0.02984 -0.0028 0.5719 0.2726
-13.000 -1.1878 0.03417 0.02759 -0.0026 0.5654 0.2761
-12.750 -1.1834 0.03224 0.02560 -0.0024 0.5587 0.2796
-12.500 -1.1752 0.03062 0.02389 -0.0023 0.5524 0.2830
-12.250 -1.1644 0.02918 0.02237 -0.0023 0.5473 0.2859
-12.000 -1.1567 0.02759 0.02075 -0.0021 0.5420 0.2889
-11.750 -1.1474 0.02616 0.01929 -0.0018 0.5366 0.2920
-11.500 -1.1354 0.02493 0.01799 -0.0017 0.5310 0.2952
-11.250 -1.1211 0.02388 0.01686 -0.0015 0.5259 0.2983
-11.000 -1.1047 0.02298 0.01589 -0.0014 0.5213 0.3008
-10.750 -1.0911 0.02198 0.01487 -0.0011 0.5163 0.3034
-10.500 -1.0770 0.02108 0.01393 -0.0006 0.5113 0.3062
-10.250 -1.0612 0.02032 0.01313 -0.0002 0.5067 0.3091
-10.000 -1.0436 0.01970 0.01245 0.0003 0.5028 0.3119
-9.750 -1.0246 0.01916 0.01186 0.0006 0.4995 0.3143
-9.500 -1.0044 0.01870 0.01133 0.0010 0.4958 0.3165
-9.250 -0.9879 0.01815 0.01077 0.0019 0.4921 0.3191
-9.000 -0.9699 0.01770 0.01030 0.0027 0.4883 0.3216
-8.750 -0.9508 0.01733 0.00989 0.0035 0.4845 0.3241
-8.500 -0.9319 0.01704 0.00954 0.0045 0.4807 0.3266
-8.250 -0.9142 0.01680 0.00927 0.0059 0.4781 0.3290
-8.000 -0.8952 0.01661 0.00903 0.0070 0.4752 0.3311
-7.750 -0.8739 0.01640 0.00879 0.0078 0.4722 0.3333
-7.500 -0.8520 0.01618 0.00857 0.0085 0.4692 0.3357
-7.250 -0.8286 0.01600 0.00837 0.0090 0.4663 0.3381
-7.000 -0.8040 0.01586 0.00819 0.0092 0.4632 0.3405
-6.750 -0.7786 0.01574 0.00801 0.0094 0.4600 0.3429
-6.500 -0.7520 0.01560 0.00785 0.0094 0.4577 0.3453
-6.250 -0.7248 0.01548 0.00769 0.0093 0.4552 0.3473
-6.000 -0.6982 0.01534 0.00754 0.0092 0.4526 0.3494
-5.750 -0.6717 0.01520 0.00740 0.0092 0.4501 0.3516
-5.500 -0.6447 0.01508 0.00728 0.0092 0.4476 0.3540
-5.250 -0.6171 0.01499 0.00717 0.0090 0.4451 0.3563
-5.000 -0.5891 0.01491 0.00705 0.0088 0.4424 0.3585
-4.750 -0.5608 0.01486 0.00695 0.0085 0.4396 0.3607
-4.500 -0.5318 0.01479 0.00685 0.0081 0.4375 0.3629
-4.250 -0.5025 0.01472 0.00675 0.0077 0.4355 0.3646
-4.000 -0.4741 0.01461 0.00665 0.0074 0.4334 0.3667
-3.750 -0.4455 0.01452 0.00658 0.0071 0.4313 0.3688
-3.500 -0.4166 0.01445 0.00651 0.0068 0.4290 0.3710
-3.250 -0.3874 0.01440 0.00645 0.0064 0.4267 0.3733
-3.000 -0.3580 0.01436 0.00638 0.0059 0.4242 0.3755
-2.750 -0.3286 0.01433 0.00632 0.0055 0.4218 0.3775
-2.500 -0.2990 0.01433 0.00627 0.0051 0.4193 0.3793
-2.250 -0.2689 0.01430 0.00622 0.0045 0.4177 0.3812
-2.000 -0.2391 0.01424 0.00617 0.0040 0.4161 0.3831
-1.750 -0.2095 0.01418 0.00614 0.0036 0.4142 0.3853
-1.500 -0.1798 0.01414 0.00611 0.0031 0.4120 0.3873
-1.250 -0.1499 0.01410 0.00609 0.0026 0.4097 0.3893
-1.000 -0.1200 0.01409 0.00606 0.0021 0.4074 0.3913
-0.750 -0.0901 0.01408 0.00604 0.0016 0.4052 0.3935
-0.500 -0.0601 0.01410 0.00603 0.0011 0.4032 0.3957
-0.250 -0.0302 0.01413 0.00602 0.0006 0.4012 0.3977
0.000 0.0000 0.01416 0.00603 0.0000 0.3994 0.3994
0.250 0.0302 0.01413 0.00602 -0.0005 0.3977 0.4012
0.500 0.0601 0.01410 0.00603 -0.0011 0.3957 0.4032
0.750 0.0901 0.01408 0.00604 -0.0016 0.3935 0.4052
1.000 0.1200 0.01409 0.00606 -0.0021 0.3913 0.4074
1.250 0.1499 0.01410 0.00609 -0.0026 0.3893 0.4097
1.500 0.1798 0.01414 0.00611 -0.0031 0.3873 0.4120
1.750 0.2095 0.01418 0.00614 -0.0036 0.3853 0.4142
2.000 0.2391 0.01424 0.00617 -0.0040 0.3831 0.4161
2.250 0.2689 0.01430 0.00622 -0.0045 0.3812 0.4177
2.500 0.2991 0.01433 0.00627 -0.0051 0.3793 0.4193
2.750 0.3286 0.01433 0.00632 -0.0055 0.3775 0.4217
3.000 0.3581 0.01436 0.00638 -0.0060 0.3755 0.4242
3.250 0.3874 0.01440 0.00645 -0.0064 0.3733 0.4267
3.500 0.4166 0.01445 0.00651 -0.0068 0.3710 0.4290
3.750 0.4455 0.01452 0.00658 -0.0071 0.3688 0.4313
4.000 0.4742 0.01461 0.00665 -0.0075 0.3667 0.4334
4.250 0.5026 0.01472 0.00675 -0.0077 0.3646 0.4355
4.500 0.5319 0.01479 0.00685 -0.0082 0.3629 0.4375
4.750 0.5609 0.01486 0.00695 -0.0085 0.3607 0.4396
5.000 0.5892 0.01491 0.00705 -0.0088 0.3585 0.4424
5.250 0.6172 0.01499 0.00717 -0.0090 0.3563 0.4451
5.500 0.6448 0.01508 0.00728 -0.0092 0.3540 0.4476
5.750 0.6719 0.01520 0.00740 -0.0093 0.3516 0.4501
6.000 0.6983 0.01534 0.00754 -0.0093 0.3493 0.4526
6.250 0.7250 0.01548 0.00769 -0.0093 0.3473 0.4552
6.500 0.7523 0.01560 0.00785 -0.0094 0.3453 0.4577
6.750 0.7788 0.01574 0.00801 -0.0094 0.3429 0.4600
7.000 0.8043 0.01585 0.00818 -0.0093 0.3405 0.4633
7.250 0.8290 0.01600 0.00837 -0.0090 0.3381 0.4663
7.500 0.8524 0.01618 0.00857 -0.0086 0.3356 0.4692
7.750 0.8744 0.01640 0.00879 -0.0079 0.3333 0.4722
8.000 0.8959 0.01661 0.00903 -0.0072 0.3312 0.4752
8.250 0.9151 0.01680 0.00926 -0.0060 0.3290 0.4781
8.500 0.9328 0.01703 0.00954 -0.0047 0.3266 0.4808
8.750 0.9517 0.01733 0.00988 -0.0037 0.3241 0.4845
9.000 0.9707 0.01769 0.01029 -0.0029 0.3216 0.4884
9.250 0.9888 0.01814 0.01076 -0.0020 0.3191 0.4922
9.500 1.0054 0.01869 0.01132 -0.0012 0.3165 0.4958
9.750 1.0256 0.01915 0.01184 -0.0008 0.3143 0.4995
10.000 1.0448 0.01968 0.01243 -0.0004 0.3118 0.5028
10.250 1.0624 0.02031 0.01311 0.0000 0.3091 0.5068
10.500 1.0783 0.02105 0.01391 0.0004 0.3062 0.5114
10.750 1.0926 0.02195 0.01484 0.0009 0.3034 0.5164
11.000 1.1063 0.02295 0.01586 0.0012 0.3007 0.5214
11.250 1.1227 0.02384 0.01683 0.0013 0.2982 0.5260
11.500 1.1372 0.02488 0.01795 0.0014 0.2952 0.5312
11.750 1.1493 0.02611 0.01924 0.0016 0.2920 0.5367
12.000 1.1588 0.02754 0.02070 0.0018 0.2889 0.5422
12.250 1.1666 0.02913 0.02231 0.0020 0.2859 0.5474
12.500 1.1776 0.03055 0.02382 0.0020 0.2830 0.5525
12.750 1.1860 0.03217 0.02553 0.0021 0.2796 0.5589
13.000 1.1904 0.03411 0.02752 0.0022 0.2761 0.5656
13.250 1.1911 0.03634 0.02978 0.0025 0.2726 0.5721
13.500 1.1962 0.03830 0.03181 0.0025 0.2694 0.5789
13.750 1.1996 0.04043 0.03404 0.0025 0.2658 0.5869
14.000 1.1986 0.04300 0.03667 0.0025 0.2619 0.5947
14.500 1.1990 0.04804 0.04183 0.0023 0.2547 0.6100
14.750 1.1983 0.05074 0.04461 0.0021 0.2508 0.6187
15.250 1.1936 0.05646 0.05043 0.0017 0.2430 0.6363
15.500 1.1950 0.05906 0.05313 0.0014 0.2394 0.6470
15.750 1.1913 0.06218 0.05631 0.0011 0.2352 0.6568
16.000 1.1902 0.06499 0.05917 0.0008 0.2314 0.6698
16.250 1.1899 0.06783 0.06210 0.0004 0.2280 0.6829
16.500 1.1886 0.07077 0.06514 -0.0001 0.2240 0.6984
16.750 1.1880 0.07362 0.06807 -0.0005 0.2201 0.7140
17.250 1.1879 0.07933 0.07397 -0.0015 0.2132 0.7522
17.500 1.1861 0.08234 0.07713 -0.0020 0.2094 0.7778
17.750 1.1846 0.08516 0.08011 -0.0023 0.2057 0.8227
18.000 1.1802 0.08708 0.08237 -0.0010 0.2028 1.0000
18.250 1.1801 0.09012 0.08545 -0.0017 0.1994 1.0000
18.500 1.1792 0.09322 0.08857 -0.0025 0.1957 1.0000
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Polar data table (+)
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