I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: I.S.A. 571 (isa571-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.5 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa571-il-1000000-n5.txt Download as CSV file: xf-isa571-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 571
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4196 0.09044 0.08889 -0.0193 1.0000 0.0037
-8.750 -0.4282 0.08764 0.08611 -0.0182 1.0000 0.0037
-8.250 -0.4382 0.01883 0.01542 -0.0835 0.9868 0.0039
-8.000 -0.4132 0.01599 0.01218 -0.0842 0.9847 0.0041
-7.750 -0.3849 0.01455 0.01051 -0.0849 0.9828 0.0043
-7.500 -0.3537 0.01354 0.00935 -0.0859 0.9811 0.0044
-7.250 -0.3204 0.01272 0.00838 -0.0873 0.9796 0.0047
-7.000 -0.2867 0.01199 0.00752 -0.0888 0.9780 0.0049
-6.750 -0.2573 0.01136 0.00678 -0.0891 0.9741 0.0052
-6.500 -0.2277 0.01081 0.00613 -0.0895 0.9696 0.0056
-6.250 -0.1960 0.01035 0.00558 -0.0903 0.9661 0.0059
-6.000 -0.1698 0.00976 0.00488 -0.0899 0.9596 0.0064
-5.750 -0.1401 0.00927 0.00432 -0.0903 0.9549 0.0071
-5.500 -0.1119 0.00891 0.00390 -0.0903 0.9491 0.0076
-5.250 -0.0828 0.00857 0.00350 -0.0904 0.9409 0.0084
-5.000 -0.0543 0.00830 0.00315 -0.0904 0.9288 0.0090
-4.750 -0.0260 0.00796 0.00273 -0.0903 0.9136 0.0110
-4.500 0.0018 0.00772 0.00241 -0.0902 0.8970 0.0132
-4.250 0.0292 0.00754 0.00217 -0.0899 0.8762 0.0184
-4.000 0.0558 0.00751 0.00209 -0.0895 0.8459 0.0266
-3.750 0.0815 0.00763 0.00201 -0.0888 0.8014 0.0297
-3.500 0.1061 0.00780 0.00192 -0.0880 0.7407 0.0320
-3.250 0.1311 0.00802 0.00191 -0.0873 0.6811 0.0339
-3.000 0.1573 0.00818 0.00190 -0.0869 0.6389 0.0358
-2.750 0.1842 0.00828 0.00186 -0.0867 0.6088 0.0374
-2.500 0.2113 0.00838 0.00183 -0.0865 0.5803 0.0383
-2.250 0.2384 0.00842 0.00175 -0.0863 0.5505 0.0388
-2.000 0.2654 0.00834 0.00151 -0.0861 0.5189 0.0405
-1.750 0.2922 0.00839 0.00142 -0.0859 0.4813 0.0420
-1.500 0.3190 0.00851 0.00137 -0.0857 0.4441 0.0434
-1.250 0.3459 0.00861 0.00133 -0.0856 0.4133 0.0446
-0.750 0.4003 0.00879 0.00129 -0.0853 0.3652 0.0470
-0.500 0.4279 0.00884 0.00128 -0.0853 0.3527 0.0481
-0.250 0.4555 0.00889 0.00127 -0.0852 0.3415 0.0489
0.000 0.4832 0.00893 0.00127 -0.0852 0.3315 0.0509
0.250 0.5108 0.00897 0.00128 -0.0851 0.3222 0.0554
0.500 0.5384 0.00902 0.00131 -0.0851 0.3123 0.0607
0.750 0.5661 0.00902 0.00138 -0.0851 0.3047 0.0946
1.000 0.5936 0.00910 0.00143 -0.0851 0.2967 0.1003
1.250 0.6212 0.00914 0.00148 -0.0851 0.2891 0.1061
1.500 0.6486 0.00922 0.00154 -0.0850 0.2810 0.1096
1.750 0.6762 0.00929 0.00160 -0.0850 0.2733 0.1125
2.000 0.7035 0.00937 0.00167 -0.0850 0.2638 0.1182
2.250 0.7307 0.00947 0.00176 -0.0849 0.2529 0.1256
2.750 0.7784 0.00799 0.00214 -0.0839 0.2225 1.0000
3.000 0.8045 0.00829 0.00230 -0.0837 0.1954 1.0000
3.250 0.8308 0.00855 0.00248 -0.0835 0.1785 1.0000
3.500 0.8574 0.00877 0.00264 -0.0834 0.1682 1.0000
3.750 0.8843 0.00894 0.00280 -0.0833 0.1622 1.0000
4.000 0.9108 0.00916 0.00298 -0.0831 0.1550 1.0000
4.250 0.9376 0.00934 0.00316 -0.0830 0.1478 1.0000
4.500 0.9638 0.00959 0.00336 -0.0829 0.1368 1.0000
4.750 0.9892 0.00995 0.00360 -0.0826 0.1142 1.0000
5.000 1.0132 0.01048 0.00396 -0.0821 0.0842 1.0000
5.250 1.0389 0.01079 0.00424 -0.0819 0.0760 1.0000
5.500 1.0650 0.01102 0.00448 -0.0817 0.0709 1.0000
5.750 1.0879 0.01168 0.00495 -0.0810 0.0387 1.0000
6.000 1.1108 0.01235 0.00552 -0.0803 0.0137 1.0000
6.250 1.1354 0.01276 0.00595 -0.0799 0.0100 1.0000
6.500 1.1604 0.01310 0.00632 -0.0796 0.0085 1.0000
6.750 1.1850 0.01348 0.00673 -0.0791 0.0074 1.0000
7.000 1.2087 0.01396 0.00724 -0.0786 0.0062 1.0000
7.250 1.2330 0.01434 0.00766 -0.0781 0.0057 1.0000
7.500 1.2570 0.01475 0.00810 -0.0777 0.0051 1.0000
7.750 1.2803 0.01521 0.00862 -0.0771 0.0046 1.0000
8.000 1.3023 0.01583 0.00930 -0.0763 0.0041 1.0000
8.250 1.3250 0.01634 0.00986 -0.0756 0.0039 1.0000
8.500 1.3472 0.01688 0.01047 -0.0749 0.0036 1.0000
8.750 1.3688 0.01746 0.01111 -0.0741 0.0034 1.0000
9.000 1.3899 0.01806 0.01177 -0.0732 0.0032 1.0000
9.250 1.4107 0.01866 0.01243 -0.0723 0.0030 1.0000
9.500 1.4306 0.01931 0.01314 -0.0713 0.0028 1.0000
9.750 1.4468 0.02032 0.01426 -0.0697 0.0025 1.0000
10.000 1.4655 0.02099 0.01501 -0.0685 0.0025 1.0000
10.250 1.4825 0.02179 0.01590 -0.0671 0.0024 1.0000
10.500 1.4980 0.02265 0.01687 -0.0654 0.0023 1.0000
10.750 1.5119 0.02358 0.01790 -0.0636 0.0022 1.0000
11.000 1.5241 0.02455 0.01897 -0.0615 0.0021 1.0000
11.250 1.5325 0.02555 0.02007 -0.0588 0.0020 1.0000
11.500 1.5389 0.02662 0.02124 -0.0558 0.0020 1.0000
11.750 1.5447 0.02776 0.02249 -0.0530 0.0019 1.0000
12.000 1.5491 0.02905 0.02390 -0.0502 0.0019 1.0000
12.250 1.5525 0.03049 0.02544 -0.0477 0.0018 1.0000
12.500 1.5549 0.03208 0.02714 -0.0453 0.0018 1.0000
12.750 1.5564 0.03388 0.02905 -0.0432 0.0017 1.0000
13.000 1.5553 0.03605 0.03135 -0.0414 0.0017 1.0000
13.250 1.5537 0.03850 0.03391 -0.0401 0.0017 1.0000
13.500 1.5491 0.04154 0.03708 -0.0393 0.0016 1.0000
13.750 1.5428 0.04518 0.04087 -0.0394 0.0016 1.0000
14.000 1.5341 0.04957 0.04540 -0.0403 0.0016 1.0000
14.250 1.5235 0.05470 0.05068 -0.0421 0.0016 1.0000
14.500 1.5101 0.06057 0.05671 -0.0444 0.0016 1.0000
14.750 1.4943 0.06705 0.06334 -0.0472 0.0015 1.0000
15.000 1.4767 0.07404 0.07048 -0.0502 0.0015 1.0000
15.250 1.4577 0.08125 0.07782 -0.0532 0.0015 1.0000
15.500 1.4372 0.08869 0.08540 -0.0562 0.0015 1.0000
15.750 1.4173 0.09605 0.09288 -0.0592 0.0015 1.0000
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Polar data table (+)
Polar graphs
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