SG6043 (sg6043-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6043 (sg6043-il) Reynolds number: 200,000 Max Cl/Cd: 98.01 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6043-il-200000.txt Download as CSV file: xf-sg6043-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SG6043
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
------ -------- --------- --------- -------- -------- --------
-7.000 -0.1974 0.09204 0.08868 -0.0635 0.9587 0.0413
-6.750 -0.1929 0.08903 0.08569 -0.0693 0.9517 0.0432
-6.500 -0.1808 0.08379 0.08044 -0.0844 0.9400 0.0439
-6.250 -0.1694 0.08038 0.07706 -0.0795 0.9389 0.0447
-6.000 -0.1475 0.07798 0.07465 -0.0792 0.9376 0.0474
-5.750 -0.1444 0.07538 0.07207 -0.0803 0.9282 0.0487
-5.500 -0.0998 0.06666 0.06301 -0.1073 0.9186 0.0526
-5.250 -0.0941 0.06337 0.05989 -0.1034 0.9146 0.0535
-5.000 -0.0745 0.06102 0.05755 -0.1031 0.9120 0.0548
-4.750 -0.0418 0.05737 0.05384 -0.1084 0.9099 0.0576
-4.500 -0.0053 0.05039 0.04637 -0.1212 0.9011 0.0638
-4.250 0.0173 0.04770 0.04379 -0.1219 0.8981 0.0655
-4.000 0.0715 0.04505 0.04054 -0.1305 0.8961 0.0752
-3.750 0.1027 0.03977 0.03534 -0.1344 0.8949 0.0781
-3.500 0.1156 0.03863 0.03423 -0.1329 0.8871 0.0817
-3.250 0.1833 0.02948 0.02353 -0.1423 0.8865 0.0531
-3.000 0.2272 0.02560 0.01894 -0.1454 0.8848 0.0439
-2.750 0.2676 0.02333 0.01635 -0.1479 0.8831 0.0434
-2.500 0.3091 0.02166 0.01438 -0.1504 0.8818 0.0444
-2.250 0.3497 0.02054 0.01326 -0.1529 0.8804 0.0483
-2.000 0.3922 0.01939 0.01199 -0.1553 0.8794 0.0513
-1.750 0.4358 0.01823 0.01086 -0.1582 0.8786 0.0574
-1.500 0.4493 0.01812 0.01079 -0.1555 0.8690 0.0669
-1.250 0.4918 0.01717 0.00999 -0.1583 0.8673 0.1112
-1.000 0.5354 0.01637 0.00947 -0.1615 0.8659 0.1850
-0.750 0.5782 0.01485 0.00934 -0.1650 0.8648 0.6047
-0.500 0.6123 0.01417 0.00904 -0.1652 0.8631 0.7653
-0.250 0.6156 0.01418 0.00926 -0.1596 0.8529 0.8735
0.000 0.6574 0.01371 0.00871 -0.1618 0.8504 1.0000
0.250 0.7012 0.01340 0.00824 -0.1647 0.8482 1.0000
0.500 0.7223 0.01359 0.00836 -0.1633 0.8395 1.0000
0.750 0.7609 0.01336 0.00801 -0.1651 0.8354 1.0000
1.000 0.8033 0.01305 0.00759 -0.1676 0.8323 1.0000
1.250 0.8248 0.01321 0.00771 -0.1663 0.8231 1.0000
1.500 0.8634 0.01296 0.00737 -0.1681 0.8182 1.0000
1.750 0.8912 0.01297 0.00734 -0.1678 0.8103 1.0000
2.000 0.9245 0.01283 0.00714 -0.1686 0.8034 1.0000
2.250 0.9542 0.01279 0.00706 -0.1687 0.7954 1.0000
2.500 0.9855 0.01268 0.00691 -0.1690 0.7871 1.0000
2.750 1.0122 0.01268 0.00689 -0.1685 0.7773 1.0000
3.000 1.0465 0.01252 0.00667 -0.1694 0.7691 1.0000
3.250 1.0694 0.01258 0.00673 -0.1681 0.7575 1.0000
3.500 1.0963 0.01257 0.00671 -0.1677 0.7465 1.0000
3.750 1.1261 0.01250 0.00659 -0.1677 0.7355 1.0000
4.000 1.1510 0.01250 0.00658 -0.1668 0.7222 1.0000
4.250 1.1745 0.01255 0.00662 -0.1656 0.7079 1.0000
4.500 1.1985 0.01259 0.00666 -0.1646 0.6926 1.0000
4.750 1.2226 0.01265 0.00668 -0.1635 0.6758 1.0000
5.000 1.2460 0.01276 0.00674 -0.1624 0.6579 1.0000
5.250 1.2668 0.01293 0.00689 -0.1608 0.6379 1.0000
5.500 1.2878 0.01314 0.00707 -0.1592 0.6169 1.0000
5.750 1.3086 0.01339 0.00724 -0.1576 0.5945 1.0000
6.000 1.3269 0.01370 0.00749 -0.1556 0.5697 1.0000
6.250 1.3443 0.01408 0.00779 -0.1534 0.5432 1.0000
6.500 1.3598 0.01453 0.00812 -0.1510 0.5147 1.0000
6.750 1.3733 0.01505 0.00851 -0.1482 0.4847 1.0000
7.000 1.3838 0.01563 0.00895 -0.1448 0.4535 1.0000
7.250 1.3922 0.01629 0.00948 -0.1412 0.4212 1.0000
7.500 1.3999 0.01704 0.01008 -0.1376 0.3888 1.0000
7.750 1.4071 0.01787 0.01076 -0.1340 0.3568 1.0000
8.000 1.4139 0.01878 0.01152 -0.1305 0.3262 1.0000
8.250 1.4209 0.01975 0.01235 -0.1272 0.2968 1.0000
8.500 1.4285 0.02076 0.01325 -0.1241 0.2693 1.0000
8.750 1.4357 0.02185 0.01422 -0.1211 0.2446 1.0000
9.000 1.4430 0.02299 0.01526 -0.1182 0.2222 1.0000
9.250 1.4499 0.02422 0.01639 -0.1154 0.2033 1.0000
9.500 1.4585 0.02541 0.01754 -0.1129 0.1856 1.0000
9.750 1.4667 0.02667 0.01875 -0.1105 0.1707 1.0000
10.000 1.4742 0.02802 0.02005 -0.1081 0.1580 1.0000
10.250 1.4823 0.02937 0.02137 -0.1058 0.1466 1.0000
10.500 1.4921 0.03066 0.02270 -0.1038 0.1361 1.0000
10.750 1.4999 0.03214 0.02419 -0.1017 0.1272 1.0000
11.000 1.5071 0.03369 0.02571 -0.0997 0.1192 1.0000
11.250 1.5166 0.03512 0.02723 -0.0979 0.1117 1.0000
11.500 1.5226 0.03690 0.02895 -0.0960 0.1052 1.0000
11.750 1.5324 0.03834 0.03053 -0.0944 0.0990 1.0000
12.000 1.5392 0.04009 0.03228 -0.0927 0.0937 1.0000
12.250 1.5477 0.04181 0.03410 -0.0911 0.0887 1.0000
12.500 1.5554 0.04350 0.03587 -0.0896 0.0841 1.0000
12.750 1.5628 0.04553 0.03784 -0.0882 0.0797 1.0000
13.000 1.5702 0.04727 0.03980 -0.0868 0.0760 1.0000
13.250 1.5768 0.04917 0.04178 -0.0856 0.0724 1.0000
13.500 1.5854 0.05128 0.04383 -0.0844 0.0687 1.0000
13.750 1.5902 0.05336 0.04615 -0.0832 0.0659 1.0000
14.000 1.5953 0.05552 0.04843 -0.0821 0.0629 1.0000
14.250 1.6005 0.05777 0.05070 -0.0812 0.0603 1.0000
14.500 1.6074 0.06016 0.05321 -0.0802 0.0576 1.0000
14.750 1.6100 0.06275 0.05601 -0.0793 0.0553 1.0000
15.000 1.6133 0.06531 0.05869 -0.0786 0.0531 1.0000
15.250 1.6181 0.06778 0.06118 -0.0780 0.0511 1.0000
15.500 1.6234 0.07062 0.06412 -0.0772 0.0490 1.0000
15.750 1.6213 0.07396 0.06773 -0.0768 0.0474 1.0000
16.000 1.6200 0.07731 0.07126 -0.0766 0.0458 1.0000
16.250 1.6201 0.08049 0.07457 -0.0765 0.0444 1.0000
16.500 1.6237 0.08334 0.07746 -0.0764 0.0430 1.0000
16.750 1.6277 0.08670 0.08093 -0.0761 0.0416 1.0000
17.000 1.6188 0.09130 0.08582 -0.0767 0.0409 1.0000
17.250 1.6097 0.09613 0.09092 -0.0776 0.0402 1.0000
17.500 1.5998 0.10122 0.09626 -0.0789 0.0395 1.0000
17.750 1.5899 0.10644 0.10172 -0.0806 0.0388 1.0000
18.000 1.5792 0.11189 0.10738 -0.0826 0.0382 1.0000
18.250 1.5679 0.11761 0.11330 -0.0851 0.0376 1.0000
18.500 1.5575 0.12326 0.11913 -0.0878 0.0370 1.0000
18.750 1.5474 0.12900 0.12503 -0.0908 0.0365 1.0000
19.000 1.5392 0.13444 0.13060 -0.0937 0.0360 1.0000
19.250 1.5298 0.14028 0.13657 -0.0970 0.0356 1.0000
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Polar data table (+)
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