S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.3 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s7055-il-1000000-n5.txt Download as CSV file: xf-s7055-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S7055 (10.5%) Flat-Bottomed
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7796 0.02973 0.02727 -0.0817 0.9563 0.0042
-11.250 -0.7691 0.02697 0.02420 -0.0815 0.9363 0.0043
-11.000 -0.7558 0.02529 0.02231 -0.0805 0.9217 0.0044
-10.750 -0.7394 0.02403 0.02088 -0.0796 0.9106 0.0045
-10.500 -0.7220 0.02282 0.01949 -0.0787 0.9007 0.0047
-10.250 -0.7032 0.02170 0.01821 -0.0779 0.8925 0.0048
-10.000 -0.6836 0.02069 0.01702 -0.0772 0.8848 0.0050
-9.750 -0.6635 0.01959 0.01576 -0.0764 0.8772 0.0052
-9.500 -0.6429 0.01858 0.01456 -0.0757 0.8702 0.0054
-9.250 -0.6208 0.01771 0.01352 -0.0751 0.8630 0.0056
-9.000 -0.5974 0.01713 0.01280 -0.0746 0.8562 0.0058
-8.750 -0.5729 0.01662 0.01218 -0.0742 0.8496 0.0060
-8.500 -0.5491 0.01599 0.01141 -0.0737 0.8433 0.0061
-8.250 -0.5251 0.01531 0.01060 -0.0732 0.8373 0.0062
-8.000 -0.5035 0.01415 0.00923 -0.0725 0.8310 0.0066
-7.750 -0.4789 0.01355 0.00852 -0.0720 0.8254 0.0069
-7.500 -0.4535 0.01307 0.00795 -0.0717 0.8192 0.0071
-7.250 -0.4280 0.01265 0.00742 -0.0713 0.8135 0.0074
-7.000 -0.4021 0.01224 0.00693 -0.0711 0.8073 0.0078
-6.750 -0.3761 0.01187 0.00647 -0.0707 0.8009 0.0082
-6.500 -0.3499 0.01151 0.00603 -0.0705 0.7946 0.0085
-6.250 -0.3238 0.01116 0.00559 -0.0702 0.7875 0.0088
-6.000 -0.2974 0.01083 0.00517 -0.0699 0.7801 0.0090
-5.750 -0.2711 0.01053 0.00477 -0.0696 0.7719 0.0092
-5.500 -0.2450 0.01012 0.00427 -0.0693 0.7637 0.0095
-5.250 -0.2188 0.00975 0.00381 -0.0689 0.7560 0.0100
-5.000 -0.1922 0.00947 0.00347 -0.0687 0.7476 0.0106
-4.750 -0.1654 0.00923 0.00318 -0.0684 0.7401 0.0113
-4.500 -0.1384 0.00903 0.00293 -0.0682 0.7319 0.0122
-4.250 -0.1113 0.00885 0.00268 -0.0680 0.7243 0.0130
-4.000 -0.0844 0.00866 0.00244 -0.0678 0.7160 0.0152
-3.750 -0.0571 0.00849 0.00227 -0.0677 0.7079 0.0179
-3.500 -0.0301 0.00836 0.00213 -0.0675 0.6995 0.0230
-3.250 -0.0026 0.00827 0.00199 -0.0674 0.6905 0.0256
-3.000 0.0248 0.00817 0.00185 -0.0673 0.6815 0.0284
-2.750 0.0520 0.00808 0.00173 -0.0671 0.6721 0.0316
-2.500 0.0795 0.00800 0.00162 -0.0670 0.6623 0.0343
-2.250 0.1070 0.00794 0.00151 -0.0669 0.6534 0.0366
-2.000 0.1342 0.00786 0.00141 -0.0667 0.6441 0.0420
-1.750 0.1617 0.00779 0.00133 -0.0667 0.6348 0.0481
-1.500 0.1889 0.00771 0.00125 -0.0665 0.6261 0.0591
-1.250 0.2161 0.00764 0.00118 -0.0664 0.6170 0.0735
-1.000 0.2433 0.00754 0.00113 -0.0663 0.6077 0.0981
-0.250 0.3233 0.00714 0.00102 -0.0658 0.5780 0.2370
0.000 0.3497 0.00701 0.00101 -0.0656 0.5676 0.2986
0.250 0.3757 0.00687 0.00102 -0.0653 0.5565 0.3663
0.500 0.3997 0.00651 0.00104 -0.0648 0.5457 0.5139
1.000 0.4421 0.00571 0.00115 -0.0620 0.5258 0.8322
1.250 0.4764 0.00558 0.00126 -0.0632 0.5151 0.9492
1.500 0.5225 0.00570 0.00131 -0.0672 0.5028 0.9734
1.750 0.5558 0.00580 0.00136 -0.0685 0.4908 0.9809
2.000 0.5892 0.00593 0.00141 -0.0698 0.4768 0.9857
2.250 0.6212 0.00607 0.00147 -0.0708 0.4619 0.9905
2.500 0.6527 0.00620 0.00154 -0.0717 0.4491 0.9944
2.750 0.6913 0.00633 0.00161 -0.0743 0.4355 0.9991
3.000 0.7204 0.00646 0.00168 -0.0746 0.4243 1.0000
3.250 0.7446 0.00660 0.00177 -0.0740 0.4127 1.0000
3.500 0.7688 0.00674 0.00187 -0.0733 0.4012 1.0000
3.750 0.7929 0.00690 0.00198 -0.0726 0.3874 1.0000
4.000 0.8169 0.00708 0.00210 -0.0719 0.3735 1.0000
4.250 0.8408 0.00726 0.00222 -0.0712 0.3598 1.0000
4.500 0.8647 0.00745 0.00236 -0.0705 0.3457 1.0000
4.750 0.8885 0.00764 0.00251 -0.0698 0.3324 1.0000
5.000 0.9122 0.00785 0.00267 -0.0691 0.3178 1.0000
5.250 0.9356 0.00808 0.00284 -0.0683 0.3020 1.0000
5.500 0.9587 0.00833 0.00303 -0.0675 0.2848 1.0000
5.750 0.9814 0.00862 0.00324 -0.0667 0.2666 1.0000
6.000 1.0041 0.00890 0.00346 -0.0658 0.2509 1.0000
6.250 1.0266 0.00919 0.00369 -0.0650 0.2336 1.0000
6.500 1.0494 0.00947 0.00392 -0.0642 0.2196 1.0000
6.750 1.0696 0.00994 0.00425 -0.0630 0.1913 1.0000
7.000 1.0872 0.01058 0.00468 -0.0614 0.1534 1.0000
7.250 1.1043 0.01125 0.00514 -0.0598 0.1171 1.0000
7.500 1.1238 0.01174 0.00553 -0.0585 0.0968 1.0000
7.750 1.1423 0.01228 0.00596 -0.0571 0.0773 1.0000
8.000 1.1614 0.01277 0.00638 -0.0558 0.0623 1.0000
8.250 1.1775 0.01343 0.00693 -0.0541 0.0423 1.0000
8.500 1.1948 0.01399 0.00742 -0.0525 0.0296 1.0000
8.750 1.2106 0.01460 0.00797 -0.0507 0.0187 1.0000
9.000 1.2262 0.01519 0.00852 -0.0488 0.0116 1.0000
9.250 1.2373 0.01590 0.00920 -0.0462 0.0044 1.0000
9.500 1.2508 0.01639 0.00971 -0.0439 0.0035 1.0000
9.750 1.2640 0.01691 0.01027 -0.0417 0.0029 1.0000
10.000 1.2776 0.01744 0.01086 -0.0397 0.0026 1.0000
10.250 1.2910 0.01801 0.01148 -0.0377 0.0024 1.0000
10.500 1.3031 0.01869 0.01220 -0.0356 0.0022 1.0000
10.750 1.3149 0.01941 0.01299 -0.0337 0.0021 1.0000
11.000 1.3261 0.02022 0.01385 -0.0317 0.0020 1.0000
11.250 1.3371 0.02106 0.01476 -0.0299 0.0019 1.0000
11.500 1.3472 0.02200 0.01577 -0.0281 0.0018 1.0000
11.750 1.3563 0.02304 0.01688 -0.0263 0.0018 1.0000
12.000 1.3675 0.02398 0.01788 -0.0249 0.0018 1.0000
12.250 1.3776 0.02503 0.01901 -0.0235 0.0017 1.0000
12.500 1.3848 0.02635 0.02041 -0.0219 0.0017 1.0000
12.750 1.3914 0.02776 0.02190 -0.0205 0.0017 1.0000
13.000 1.3982 0.02921 0.02343 -0.0192 0.0016 1.0000
13.250 1.4034 0.03086 0.02517 -0.0180 0.0016 1.0000
13.500 1.4095 0.03247 0.02685 -0.0169 0.0015 1.0000
13.750 1.4132 0.03438 0.02885 -0.0159 0.0015 1.0000
14.000 1.4176 0.03628 0.03083 -0.0152 0.0014 1.0000
14.250 1.4177 0.03867 0.03334 -0.0144 0.0014 1.0000
14.500 1.4186 0.04108 0.03584 -0.0138 0.0014 1.0000
14.750 1.4202 0.04349 0.03833 -0.0135 0.0013 1.0000
15.000 1.4193 0.04628 0.04122 -0.0132 0.0013 1.0000
15.250 1.4174 0.04930 0.04436 -0.0132 0.0013 1.0000
15.500 1.4118 0.05289 0.04807 -0.0135 0.0014 1.0000
15.750 1.4091 0.05624 0.05152 -0.0139 0.0013 1.0000
16.000 1.4054 0.05984 0.05522 -0.0145 0.0012 1.0000
16.250 1.3999 0.06380 0.05929 -0.0153 0.0012 1.0000
16.500 1.3927 0.06810 0.06369 -0.0163 0.0012 1.0000
16.750 1.3859 0.07249 0.06819 -0.0176 0.0012 1.0000
17.000 1.3767 0.07739 0.07321 -0.0191 0.0012 1.0000
17.250 1.3681 0.08228 0.07820 -0.0208 0.0011 1.0000
17.500 1.3537 0.08828 0.08434 -0.0230 0.0012 1.0000
17.750 1.3452 0.09346 0.08962 -0.0250 0.0011 1.0000
18.000 1.3321 0.09954 0.09582 -0.0275 0.0011 1.0000
18.250 1.3206 0.10550 0.10190 -0.0301 0.0011 1.0000
18.500 1.3069 0.11202 0.10854 -0.0331 0.0011 1.0000
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Polar data table (+)
Polar graphs
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