I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: I.S.A. 571 (isa571-il) Reynolds number: 50,000 Max Cl/Cd: 35.38 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa571-il-50000.txt Download as CSV file: xf-isa571-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4294 0.10691 0.10019 -0.0163 1.0000 0.1508
-8.250 -0.4124 0.10132 0.09460 -0.0145 1.0000 0.1569
-8.000 -0.4171 0.09926 0.09265 -0.0147 1.0000 0.1631
-7.750 -0.4317 0.09884 0.09239 -0.0213 1.0000 0.1660
-7.500 -0.4134 0.09311 0.08665 -0.0153 1.0000 0.1769
-7.250 -0.4131 0.08997 0.08361 -0.0163 1.0000 0.1837
-7.000 -0.4149 0.08808 0.08177 -0.0201 1.0000 0.1944
-6.750 -0.4068 0.08416 0.07791 -0.0174 1.0000 0.2072
-6.500 -0.4010 0.08076 0.07458 -0.0165 1.0000 0.2199
-6.250 -0.3960 0.07758 0.07146 -0.0164 1.0000 0.2340
-6.000 -0.3927 0.07518 0.06906 -0.0203 1.0000 0.2528
-5.750 -0.3850 0.07128 0.06523 -0.0168 1.0000 0.2694
-5.500 -0.3789 0.06861 0.06258 -0.0168 1.0000 0.2970
-5.250 -0.0271 0.04348 0.03642 -0.0205 1.0000 1.0000
-5.000 -0.0168 0.04139 0.03435 -0.0213 1.0000 1.0000
-4.750 -0.0067 0.03938 0.03239 -0.0220 1.0000 1.0000
-4.500 -0.0417 0.04023 0.03342 -0.0118 1.0000 0.9771
-4.250 -0.0983 0.04201 0.03550 0.0022 1.0000 0.9324
-4.000 -0.1526 0.04311 0.03689 0.0140 1.0000 0.8861
-3.750 -0.2004 0.04343 0.03748 0.0233 1.0000 0.8449
-3.250 -0.1239 0.03463 0.02587 -0.0471 1.0000 0.1930
-3.000 -0.0930 0.03195 0.02280 -0.0478 1.0000 0.1868
-2.750 -0.0591 0.03000 0.02011 -0.0486 1.0000 0.1809
-2.500 -0.0294 0.02814 0.01789 -0.0487 1.0000 0.1814
-2.250 -0.0020 0.02665 0.01620 -0.0487 1.0000 0.1900
-2.000 0.0268 0.02546 0.01466 -0.0486 1.0000 0.1921
-1.750 0.0545 0.02442 0.01341 -0.0483 1.0000 0.1974
-1.500 0.0812 0.02363 0.01251 -0.0480 1.0000 0.2113
-1.250 0.1092 0.02296 0.01171 -0.0477 1.0000 0.2227
-1.000 0.1365 0.02232 0.01104 -0.0475 1.0000 0.2383
-0.750 0.1643 0.02158 0.01053 -0.0478 1.0000 0.2706
-0.500 0.1804 0.01874 0.01025 -0.0455 1.0000 1.0000
-0.250 0.2044 0.01928 0.00997 -0.0446 1.0000 1.0000
0.000 0.2249 0.01990 0.01030 -0.0444 1.0000 1.0000
0.250 0.2438 0.02067 0.01088 -0.0444 1.0000 1.0000
0.500 0.2609 0.02163 0.01173 -0.0446 1.0000 1.0000
0.750 0.3197 0.02271 0.01265 -0.0525 0.9796 1.0000
1.000 0.3940 0.02328 0.01311 -0.0623 0.9465 1.0000
1.250 0.4606 0.02332 0.01312 -0.0697 0.9110 1.0000
1.500 0.5255 0.02291 0.01275 -0.0758 0.8766 1.0000
1.750 0.5848 0.02220 0.01206 -0.0800 0.8450 1.0000
2.000 0.6295 0.02176 0.01165 -0.0815 0.8100 1.0000
2.250 0.6714 0.02144 0.01127 -0.0824 0.7777 1.0000
2.500 0.7077 0.02135 0.01108 -0.0823 0.7462 1.0000
2.750 0.7385 0.02152 0.01112 -0.0814 0.7145 1.0000
3.000 0.7659 0.02192 0.01146 -0.0803 0.6841 1.0000
3.250 0.7933 0.02242 0.01184 -0.0793 0.6574 1.0000
3.500 0.8181 0.02314 0.01256 -0.0784 0.6328 1.0000
3.750 0.8439 0.02388 0.01328 -0.0776 0.6110 1.0000
4.000 0.8685 0.02469 0.01417 -0.0768 0.5896 1.0000
4.250 0.8942 0.02546 0.01492 -0.0759 0.5697 1.0000
4.500 0.9170 0.02639 0.01596 -0.0749 0.5481 1.0000
4.750 0.9420 0.02724 0.01683 -0.0740 0.5285 1.0000
5.000 0.9646 0.02830 0.01806 -0.0730 0.5079 1.0000
5.250 0.9882 0.02920 0.01900 -0.0718 0.4865 1.0000
5.500 1.0102 0.03025 0.02013 -0.0705 0.4648 1.0000
5.750 1.0331 0.03117 0.02109 -0.0692 0.4431 1.0000
6.000 1.0541 0.03226 0.02232 -0.0678 0.4217 1.0000
6.250 1.0754 0.03355 0.02377 -0.0666 0.4028 1.0000
6.500 1.0975 0.03484 0.02518 -0.0654 0.3854 1.0000
6.750 1.1198 0.03618 0.02666 -0.0643 0.3689 1.0000
7.000 1.1407 0.03782 0.02852 -0.0632 0.3538 1.0000
7.250 1.1598 0.03969 0.03072 -0.0619 0.3394 1.0000
7.500 1.1747 0.04135 0.03273 -0.0601 0.3216 1.0000
7.750 1.1949 0.04004 0.03137 -0.0577 0.2903 1.0000
8.000 1.2131 0.03806 0.02929 -0.0550 0.2568 1.0000
8.250 1.2231 0.03684 0.02806 -0.0515 0.2206 1.0000
8.500 1.2236 0.03725 0.02795 -0.0470 0.1703 1.0000
8.750 1.2230 0.03999 0.03051 -0.0432 0.1310 1.0000
9.000 1.2315 0.04272 0.03335 -0.0405 0.1119 1.0000
9.250 1.2451 0.04560 0.03625 -0.0386 0.1012 1.0000
9.500 1.2585 0.04843 0.03917 -0.0368 0.0930 1.0000
9.750 1.2658 0.05205 0.04317 -0.0347 0.0878 1.0000
10.000 1.2707 0.05543 0.04687 -0.0326 0.0833 1.0000
10.250 1.2792 0.05910 0.05068 -0.0311 0.0802 1.0000
10.500 1.2822 0.06390 0.05569 -0.0295 0.0787 1.0000
10.750 1.2705 0.06819 0.06040 -0.0269 0.0785 1.0000
11.000 1.2538 0.07235 0.06488 -0.0243 0.0785 1.0000
11.250 1.2347 0.07683 0.06962 -0.0225 0.0786 1.0000
11.500 1.2137 0.08172 0.07479 -0.0218 0.0789 1.0000
11.750 1.1179 0.09535 0.08900 -0.0319 0.0867 1.0000
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Polar data table (+)
Polar graphs
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