SD8040 (10%) (sd8040-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD8040 (10%) (sd8040-il) Reynolds number: 50,000 Max Cl/Cd: 32.6 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd8040-il-50000.txt Download as CSV file: xf-sd8040-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SD8040 (10%)
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4093 0.11802 0.11089 -0.0182 1.0000 0.2127
-9.250 -0.3809 0.11213 0.10495 -0.0164 1.0000 0.2216
-9.000 -0.4081 0.11285 0.10585 -0.0193 1.0000 0.2281
-8.750 -0.3733 0.10615 0.09909 -0.0170 1.0000 0.2378
-8.500 -0.3886 0.10486 0.09795 -0.0185 1.0000 0.2453
-8.250 -0.3714 0.10084 0.09393 -0.0173 1.0000 0.2571
-8.000 -0.3648 0.09746 0.09060 -0.0168 1.0000 0.2663
-7.750 -0.3915 0.09761 0.09096 -0.0175 1.0000 0.2763
-7.500 -0.3751 0.09360 0.08697 -0.0159 1.0000 0.2914
-7.250 -0.3624 0.09001 0.08342 -0.0144 1.0000 0.3056
-7.000 -0.3572 0.08709 0.08058 -0.0129 1.0000 0.3198
-6.750 -0.3559 0.08449 0.07807 -0.0112 1.0000 0.3337
-6.250 -0.3679 0.08041 0.07425 -0.0063 1.0000 0.3617
-5.750 -0.3776 0.07624 0.07032 -0.0003 1.0000 0.3940
-5.000 -0.4090 0.05039 0.04311 -0.0382 1.0000 0.1483
-4.750 -0.3921 0.04506 0.03721 -0.0394 1.0000 0.1344
-4.500 -0.3744 0.04171 0.03363 -0.0390 1.0000 0.1304
-4.250 -0.3547 0.03839 0.02992 -0.0389 1.0000 0.1279
-4.000 -0.3332 0.03558 0.02662 -0.0387 1.0000 0.1289
-3.750 -0.3100 0.03314 0.02362 -0.0384 1.0000 0.1316
-3.500 -0.2858 0.03086 0.02085 -0.0379 1.0000 0.1345
-3.250 -0.2638 0.02922 0.01917 -0.0372 1.0000 0.1432
-3.000 -0.2395 0.02759 0.01730 -0.0365 1.0000 0.1540
-2.750 -0.2161 0.02626 0.01589 -0.0357 1.0000 0.1711
-2.500 -0.1924 0.02499 0.01459 -0.0348 1.0000 0.1985
-2.250 -0.1697 0.02375 0.01353 -0.0338 1.0000 0.2455
-2.000 -0.1456 0.02197 0.01260 -0.0330 1.0000 0.3678
-1.750 -0.1424 0.01969 0.01260 -0.0256 1.0000 0.7394
-1.500 -0.1073 0.01922 0.01191 -0.0264 1.0000 1.0000
-1.250 -0.0870 0.01951 0.01173 -0.0263 1.0000 1.0000
-1.000 -0.0673 0.01986 0.01172 -0.0261 1.0000 1.0000
-0.750 -0.0480 0.02027 0.01183 -0.0259 1.0000 1.0000
-0.500 -0.0292 0.02075 0.01204 -0.0257 1.0000 1.0000
-0.250 -0.0106 0.02128 0.01233 -0.0256 1.0000 1.0000
0.000 0.0076 0.02187 0.01272 -0.0254 1.0000 1.0000
0.250 0.0254 0.02252 0.01320 -0.0254 1.0000 1.0000
0.500 0.0814 0.02395 0.01438 -0.0322 0.9835 1.0000
0.750 0.1333 0.02514 0.01539 -0.0381 0.9641 1.0000
1.000 0.1876 0.02631 0.01640 -0.0440 0.9456 1.0000
1.250 0.2324 0.02720 0.01719 -0.0481 0.9253 1.0000
1.500 0.2770 0.02799 0.01791 -0.0518 0.9049 1.0000
1.750 0.3246 0.02869 0.01856 -0.0556 0.8851 1.0000
2.000 0.3755 0.02922 0.01907 -0.0597 0.8661 1.0000
2.250 0.4091 0.02971 0.01956 -0.0609 0.8442 1.0000
2.500 0.4524 0.03000 0.01987 -0.0632 0.8237 1.0000
2.750 0.5035 0.02998 0.01991 -0.0662 0.8046 1.0000
3.000 0.5515 0.02976 0.01975 -0.0682 0.7858 1.0000
3.250 0.5809 0.02994 0.01997 -0.0677 0.7633 1.0000
3.500 0.6226 0.02953 0.01965 -0.0682 0.7435 1.0000
3.750 0.6661 0.02886 0.01904 -0.0684 0.7245 1.0000
4.000 0.6946 0.02884 0.01909 -0.0671 0.7016 1.0000
4.250 0.7298 0.02839 0.01869 -0.0662 0.6801 1.0000
4.500 0.7664 0.02780 0.01811 -0.0652 0.6588 1.0000
4.750 0.7916 0.02793 0.01830 -0.0634 0.6336 1.0000
5.000 0.8234 0.02765 0.01800 -0.0620 0.6102 1.0000
5.250 0.8490 0.02782 0.01817 -0.0603 0.5843 1.0000
5.500 0.8744 0.02808 0.01841 -0.0586 0.5586 1.0000
5.750 0.9032 0.02815 0.01841 -0.0571 0.5336 1.0000
6.000 0.9245 0.02880 0.01909 -0.0554 0.5067 1.0000
6.250 0.9490 0.02930 0.01953 -0.0539 0.4812 1.0000
6.500 0.9734 0.02986 0.02005 -0.0524 0.4559 1.0000
6.750 0.9940 0.03075 0.02096 -0.0507 0.4303 1.0000
7.000 1.0202 0.03136 0.02140 -0.0495 0.4067 1.0000
7.250 1.0375 0.03257 0.02276 -0.0478 0.3824 1.0000
7.500 1.0625 0.03340 0.02344 -0.0466 0.3601 1.0000
7.750 1.0792 0.03482 0.02501 -0.0449 0.3382 1.0000
8.000 1.0993 0.03606 0.02627 -0.0435 0.3174 1.0000
8.250 1.1230 0.03721 0.02730 -0.0424 0.2977 1.0000
8.500 1.1383 0.03892 0.02917 -0.0407 0.2795 1.0000
8.750 1.1539 0.04073 0.03114 -0.0391 0.2625 1.0000
9.000 1.1692 0.04258 0.03311 -0.0375 0.2465 1.0000
9.250 1.1842 0.04461 0.03527 -0.0359 0.2320 1.0000
9.500 1.1992 0.04663 0.03739 -0.0344 0.2183 1.0000
9.750 1.2168 0.04868 0.03945 -0.0332 0.2055 1.0000
10.000 1.2154 0.05186 0.04309 -0.0307 0.1965 1.0000
10.250 1.2206 0.05497 0.04642 -0.0289 0.1882 1.0000
10.500 1.2439 0.05692 0.04826 -0.0282 0.1770 1.0000
10.750 1.2205 0.06172 0.05362 -0.0251 0.1748 1.0000
11.000 1.1933 0.06683 0.05911 -0.0226 0.1737 1.0000
11.250 1.1593 0.07218 0.06466 -0.0204 0.1740 1.0000
11.500 1.1204 0.07869 0.07131 -0.0201 0.1753 1.0000
11.750 1.0829 0.08669 0.07938 -0.0222 0.1767 1.0000
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Polar data table (+)
Polar graphs
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