SD7043 (9.1%) (sd7043-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7043 (9.1%) (sd7043-il) Reynolds number: 200,000 Max Cl/Cd: 82.84 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7043-il-200000.txt Download as CSV file: xf-sd7043-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3380 0.08805 0.08469 -0.0348 1.0000 0.0449
-7.750 -0.3476 0.08621 0.08293 -0.0332 1.0000 0.0458
-7.500 -0.3652 0.08499 0.08180 -0.0301 1.0000 0.0466
-7.250 -0.3849 0.08413 0.08102 -0.0263 1.0000 0.0466
-7.000 -0.4046 0.08288 0.07986 -0.0235 1.0000 0.0471
-6.750 -0.4179 0.08060 0.07764 -0.0236 1.0000 0.0478
-6.500 -0.3863 0.06826 0.06502 -0.0522 0.9923 0.0501
-6.250 -0.3744 0.06562 0.06256 -0.0483 0.9896 0.0516
-6.000 -0.3496 0.06283 0.05976 -0.0506 0.9858 0.0536
-5.750 -0.3029 0.05477 0.05098 -0.0695 0.9775 0.0617
-5.500 -0.2838 0.04892 0.04535 -0.0714 0.9743 0.0641
-5.250 -0.2513 0.04655 0.04296 -0.0746 0.9715 0.0692
-5.000 -0.2223 0.04122 0.03722 -0.0804 0.9644 0.0778
-4.750 -0.1883 0.03843 0.03432 -0.0836 0.9606 0.0833
-4.500 -0.1364 0.02485 0.01856 -0.0896 0.9585 0.0403
-4.250 -0.1044 0.02247 0.01579 -0.0906 0.9538 0.0404
-4.000 -0.0716 0.02072 0.01394 -0.0921 0.9491 0.0433
-3.750 -0.0324 0.01907 0.01201 -0.0941 0.9461 0.0445
-3.500 0.0092 0.01783 0.01058 -0.0965 0.9438 0.0472
-3.250 0.0402 0.01692 0.00955 -0.0970 0.9380 0.0510
-3.000 0.0764 0.01589 0.00856 -0.0986 0.9336 0.0556
-2.750 0.1163 0.01509 0.00774 -0.1007 0.9304 0.0639
-2.500 0.1570 0.01424 0.00696 -0.1031 0.9278 0.0791
-2.250 0.1820 0.01318 0.00646 -0.1029 0.9191 0.1958
-2.000 0.2171 0.01231 0.00625 -0.1045 0.9149 0.3818
-1.750 0.2445 0.01184 0.00623 -0.1043 0.9079 0.5191
-1.500 0.2714 0.01134 0.00621 -0.1034 0.9013 0.6628
-1.250 0.2958 0.01100 0.00616 -0.1017 0.8951 0.7679
-1.000 0.3162 0.01074 0.00604 -0.0990 0.8866 0.8481
-0.750 0.3570 0.01027 0.00562 -0.1003 0.8827 0.9706
-0.500 0.3859 0.01024 0.00547 -0.1005 0.8726 1.0000
-0.250 0.4155 0.01015 0.00524 -0.1004 0.8652 1.0000
0.000 0.4428 0.01009 0.00507 -0.0999 0.8555 1.0000
0.250 0.4700 0.01005 0.00494 -0.0994 0.8457 1.0000
0.500 0.4987 0.00993 0.00470 -0.0989 0.8376 1.0000
0.750 0.5250 0.00990 0.00461 -0.0983 0.8258 1.0000
1.000 0.5519 0.00987 0.00450 -0.0977 0.8145 1.0000
1.250 0.5793 0.00981 0.00436 -0.0971 0.8034 1.0000
1.500 0.6069 0.00974 0.00422 -0.0965 0.7918 1.0000
1.750 0.6336 0.00972 0.00413 -0.0959 0.7781 1.0000
2.000 0.6604 0.00971 0.00407 -0.0952 0.7635 1.0000
2.250 0.6873 0.00972 0.00401 -0.0946 0.7482 1.0000
2.500 0.7141 0.00975 0.00398 -0.0941 0.7318 1.0000
2.750 0.7404 0.00980 0.00399 -0.0935 0.7130 1.0000
3.000 0.7669 0.00988 0.00400 -0.0928 0.6932 1.0000
3.250 0.7933 0.00998 0.00402 -0.0922 0.6728 1.0000
3.500 0.8191 0.01012 0.00409 -0.0915 0.6489 1.0000
3.750 0.8447 0.01031 0.00417 -0.0909 0.6241 1.0000
4.000 0.8699 0.01053 0.00428 -0.0901 0.5977 1.0000
4.250 0.8947 0.01080 0.00445 -0.0894 0.5686 1.0000
4.500 0.9191 0.01111 0.00464 -0.0886 0.5380 1.0000
4.750 0.9430 0.01146 0.00487 -0.0877 0.5049 1.0000
5.000 0.9663 0.01186 0.00515 -0.0869 0.4704 1.0000
5.250 0.9890 0.01233 0.00546 -0.0860 0.4353 1.0000
5.500 1.0114 0.01283 0.00581 -0.0850 0.4000 1.0000
5.750 1.0334 0.01338 0.00620 -0.0841 0.3648 1.0000
6.000 1.0550 0.01397 0.00665 -0.0831 0.3316 1.0000
6.250 1.0763 0.01460 0.00713 -0.0822 0.3008 1.0000
6.500 1.0976 0.01524 0.00764 -0.0812 0.2723 1.0000
6.750 1.1188 0.01588 0.00819 -0.0803 0.2469 1.0000
7.000 1.1393 0.01660 0.00879 -0.0793 0.2244 1.0000
7.250 1.1604 0.01725 0.00939 -0.0784 0.2036 1.0000
7.500 1.1806 0.01798 0.01004 -0.0773 0.1853 1.0000
7.750 1.2003 0.01874 0.01074 -0.0763 0.1692 1.0000
8.000 1.2198 0.01954 0.01149 -0.0751 0.1548 1.0000
8.250 1.2390 0.02031 0.01226 -0.0740 0.1415 1.0000
8.500 1.2581 0.02110 0.01306 -0.0728 0.1296 1.0000
8.750 1.2762 0.02199 0.01396 -0.0715 0.1193 1.0000
9.000 1.2928 0.02302 0.01496 -0.0700 0.1104 1.0000
9.250 1.3104 0.02384 0.01583 -0.0687 0.1021 1.0000
9.500 1.3267 0.02493 0.01696 -0.0672 0.0951 1.0000
9.750 1.3424 0.02589 0.01795 -0.0657 0.0891 1.0000
10.000 1.3574 0.02713 0.01924 -0.0640 0.0838 1.0000
10.250 1.3716 0.02805 0.02026 -0.0623 0.0789 1.0000
10.500 1.3874 0.02978 0.02189 -0.0611 0.0743 1.0000
10.750 1.4002 0.03071 0.02305 -0.0591 0.0711 1.0000
11.000 1.4125 0.03178 0.02424 -0.0572 0.0675 1.0000
11.250 1.4252 0.03314 0.02559 -0.0557 0.0643 1.0000
11.500 1.4408 0.03504 0.02764 -0.0546 0.0614 1.0000
11.750 1.4500 0.03637 0.02919 -0.0526 0.0589 1.0000
12.000 1.4588 0.03775 0.03070 -0.0508 0.0564 1.0000
12.250 1.4685 0.03924 0.03222 -0.0492 0.0541 1.0000
12.500 1.4818 0.04205 0.03514 -0.0483 0.0516 1.0000
12.750 1.4839 0.04378 0.03715 -0.0462 0.0502 1.0000
13.000 1.4861 0.04575 0.03934 -0.0443 0.0484 1.0000
13.250 1.4875 0.04782 0.04160 -0.0428 0.0467 1.0000
13.500 1.4901 0.04991 0.04382 -0.0415 0.0452 1.0000
13.750 1.4946 0.05221 0.04617 -0.0405 0.0436 1.0000
14.000 1.4912 0.05655 0.05071 -0.0395 0.0421 1.0000
14.250 1.4815 0.05965 0.05409 -0.0386 0.0415 1.0000
14.500 1.4706 0.06332 0.05804 -0.0382 0.0407 1.0000
14.750 1.4587 0.06747 0.06245 -0.0383 0.0398 1.0000
15.000 1.4456 0.07205 0.06727 -0.0390 0.0391 1.0000
15.250 1.4314 0.07710 0.07255 -0.0403 0.0384 1.0000
15.500 1.4161 0.08257 0.07823 -0.0422 0.0378 1.0000
15.750 1.3979 0.08890 0.08478 -0.0450 0.0374 1.0000
16.000 1.3766 0.09626 0.09237 -0.0487 0.0372 1.0000
16.250 1.3472 0.10583 0.10220 -0.0542 0.0374 1.0000
16.500 1.2861 0.12360 0.12035 -0.0661 0.0393 1.0000
16.750 1.2237 0.14423 0.14117 -0.0802 0.0415 1.0000
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Polar data table (+)
Polar graphs
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