SD7043 (9.1%) (sd7043-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7043 (9.1%) (sd7043-il) Reynolds number: 100,000 Max Cl/Cd: 60.67 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7043-il-100000.txt Download as CSV file: xf-sd7043-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SD7043 (9.1%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3382 0.10477 0.09975 -0.0326 1.0000 0.0858
-8.750 -0.3498 0.10345 0.09855 -0.0357 1.0000 0.0879
-8.500 -0.3668 0.10246 0.09771 -0.0381 1.0000 0.0885
-8.250 -0.3378 0.09616 0.09137 -0.0339 1.0000 0.0924
-8.000 -0.3344 0.09371 0.08897 -0.0328 1.0000 0.0957
-7.750 -0.3398 0.09170 0.08706 -0.0323 1.0000 0.0987
-7.500 -0.3588 0.09070 0.08619 -0.0312 1.0000 0.1011
-7.250 -0.3824 0.09009 0.08573 -0.0293 1.0000 0.1019
-7.000 -0.4074 0.08879 0.08453 -0.0333 1.0000 0.1028
-6.750 -0.4141 0.08510 0.08092 -0.0332 1.0000 0.1038
-6.500 -0.4029 0.08255 0.07841 -0.0249 1.0000 0.1064
-6.250 -0.4042 0.08043 0.07634 -0.0229 1.0000 0.1093
-6.000 -0.4086 0.07798 0.07393 -0.0236 1.0000 0.1131
-5.750 -0.4141 0.07301 0.06888 -0.0347 1.0000 0.1187
-5.500 -0.4104 0.07089 0.06687 -0.0289 1.0000 0.1210
-5.250 -0.4053 0.06861 0.06459 -0.0275 1.0000 0.1251
-5.000 -0.3946 0.06367 0.05952 -0.0351 1.0000 0.1346
-4.750 -0.3876 0.06160 0.05751 -0.0321 1.0000 0.1386
-4.500 -0.3717 0.05752 0.05329 -0.0368 1.0000 0.1506
-4.250 -0.3541 0.05423 0.04986 -0.0398 1.0000 0.1646
-4.000 -0.3383 0.05165 0.04723 -0.0405 1.0000 0.1798
-3.750 -0.2581 0.03594 0.02957 -0.0571 1.0000 0.0900
-3.500 -0.2220 0.03146 0.02426 -0.0587 1.0000 0.0742
-3.250 -0.1882 0.02835 0.02076 -0.0606 0.9985 0.0721
-3.000 -0.1428 0.02668 0.01838 -0.0637 0.9937 0.0748
-2.750 -0.1022 0.02431 0.01575 -0.0663 0.9886 0.0771
-2.500 -0.0589 0.02324 0.01454 -0.0693 0.9836 0.0840
-2.250 -0.0213 0.02217 0.01333 -0.0711 0.9767 0.0912
-2.000 0.0223 0.02134 0.01257 -0.0741 0.9714 0.1064
-1.750 0.0579 0.02045 0.01190 -0.0757 0.9634 0.1386
-1.500 0.0984 0.01847 0.01169 -0.0787 0.9587 0.5009
-1.250 0.1202 0.01791 0.01203 -0.0763 0.9499 0.7613
-1.000 0.1663 0.01766 0.01186 -0.0789 0.9429 1.0000
-0.750 0.2011 0.01790 0.01180 -0.0806 0.9321 1.0000
-0.500 0.2408 0.01817 0.01182 -0.0831 0.9228 1.0000
-0.250 0.2852 0.01838 0.01181 -0.0863 0.9145 1.0000
0.000 0.3198 0.01858 0.01184 -0.0877 0.9034 1.0000
0.250 0.3641 0.01868 0.01180 -0.0906 0.8952 1.0000
0.500 0.4041 0.01872 0.01173 -0.0927 0.8851 1.0000
0.750 0.4403 0.01879 0.01171 -0.0941 0.8740 1.0000
1.000 0.4908 0.01854 0.01138 -0.0975 0.8677 1.0000
1.250 0.5224 0.01851 0.01131 -0.0977 0.8550 1.0000
1.500 0.5554 0.01841 0.01117 -0.0980 0.8430 1.0000
1.750 0.5910 0.01818 0.01091 -0.0986 0.8322 1.0000
2.000 0.6299 0.01773 0.01044 -0.0993 0.8228 1.0000
2.250 0.6597 0.01751 0.01021 -0.0987 0.8092 1.0000
2.500 0.6896 0.01724 0.00995 -0.0981 0.7953 1.0000
2.750 0.7194 0.01694 0.00964 -0.0973 0.7810 1.0000
3.000 0.7488 0.01662 0.00932 -0.0964 0.7659 1.0000
3.250 0.7781 0.01630 0.00899 -0.0955 0.7499 1.0000
3.500 0.8071 0.01599 0.00867 -0.0945 0.7329 1.0000
3.750 0.8326 0.01589 0.00857 -0.0933 0.7116 1.0000
4.000 0.8602 0.01570 0.00834 -0.0922 0.6902 1.0000
4.250 0.8859 0.01564 0.00828 -0.0909 0.6654 1.0000
4.500 0.9119 0.01563 0.00819 -0.0897 0.6389 1.0000
4.750 0.9368 0.01572 0.00820 -0.0885 0.6092 1.0000
5.000 0.9608 0.01592 0.00830 -0.0872 0.5767 1.0000
5.250 0.9841 0.01622 0.00849 -0.0858 0.5420 1.0000
5.500 1.0066 0.01663 0.00874 -0.0844 0.5056 1.0000
5.750 1.0280 0.01714 0.00909 -0.0830 0.4673 1.0000
6.000 1.0488 0.01776 0.00955 -0.0816 0.4296 1.0000
6.250 1.0690 0.01847 0.01008 -0.0802 0.3925 1.0000
6.500 1.0889 0.01929 0.01067 -0.0789 0.3588 1.0000
6.750 1.1086 0.02016 0.01137 -0.0776 0.3268 1.0000
7.000 1.1282 0.02108 0.01215 -0.0763 0.2979 1.0000
7.250 1.1478 0.02203 0.01300 -0.0751 0.2716 1.0000
7.500 1.1674 0.02303 0.01393 -0.0739 0.2477 1.0000
7.750 1.1871 0.02409 0.01486 -0.0728 0.2272 1.0000
8.000 1.2068 0.02521 0.01593 -0.0717 0.2084 1.0000
8.250 1.2265 0.02635 0.01708 -0.0706 0.1913 1.0000
8.500 1.2461 0.02755 0.01827 -0.0695 0.1760 1.0000
8.750 1.2662 0.02884 0.01956 -0.0686 0.1626 1.0000
9.000 1.2871 0.03027 0.02096 -0.0677 0.1509 1.0000
9.250 1.3082 0.03167 0.02229 -0.0670 0.1401 1.0000
9.500 1.3262 0.03310 0.02399 -0.0657 0.1307 1.0000
9.750 1.3479 0.03492 0.02583 -0.0650 0.1229 1.0000
10.000 1.3660 0.03637 0.02741 -0.0639 0.1154 1.0000
10.250 1.3854 0.03851 0.02973 -0.0630 0.1093 1.0000
10.500 1.4014 0.04034 0.03182 -0.0616 0.1038 1.0000
10.750 1.4224 0.04274 0.03417 -0.0613 0.0985 1.0000
11.000 1.4297 0.04491 0.03685 -0.0588 0.0945 1.0000
11.250 1.4415 0.04717 0.03937 -0.0572 0.0908 1.0000
11.500 1.4626 0.05026 0.04237 -0.0573 0.0866 1.0000
11.750 1.4566 0.05286 0.04554 -0.0538 0.0846 1.0000
12.000 1.4492 0.05587 0.04901 -0.0505 0.0826 1.0000
12.250 1.4386 0.05902 0.05252 -0.0472 0.0812 1.0000
12.500 1.4249 0.06230 0.05610 -0.0441 0.0801 1.0000
12.750 1.4100 0.06579 0.05985 -0.0416 0.0791 1.0000
13.000 1.3950 0.06953 0.06382 -0.0399 0.0781 1.0000
13.250 1.4184 0.07266 0.06678 -0.0402 0.0744 1.0000
13.500 1.3929 0.07739 0.07176 -0.0389 0.0742 1.0000
13.750 1.3656 0.08268 0.07732 -0.0386 0.0742 1.0000
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Polar data table (+)
Polar graphs
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