SG6043 (sg6043-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6043 (sg6043-il) Reynolds number: 500,000 Max Cl/Cd: 142.98 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6043-il-500000.txt Download as CSV file: xf-sg6043-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0664 0.09089 0.08859 -0.0846 0.9694 0.0181
-9.500 -0.0547 0.08749 0.08518 -0.0865 0.9673 0.0183
-9.250 -0.0426 0.08399 0.08168 -0.0887 0.9658 0.0188
-9.000 -0.0306 0.08017 0.07787 -0.0914 0.9646 0.0193
-8.750 -0.0186 0.07618 0.07388 -0.0944 0.9636 0.0199
-8.500 -0.0191 0.07190 0.06960 -0.0970 0.9578 0.0212
-8.250 -0.0147 0.06691 0.06462 -0.1016 0.9546 0.0214
-8.000 -0.0029 0.06258 0.06029 -0.1038 0.9530 0.0217
-7.750 0.0152 0.05963 0.05734 -0.1054 0.9518 0.0222
-7.500 0.0310 0.05602 0.05373 -0.1086 0.9507 0.0230
-7.000 -0.0421 0.06812 0.06575 -0.1093 0.9444 0.0220
-6.750 -0.0209 0.06517 0.06280 -0.1129 0.9414 0.0228
-6.500 0.0058 0.06054 0.05815 -0.1213 0.9390 0.0244
-6.250 0.0369 0.04980 0.04732 -0.1415 0.9303 0.0260
-6.000 0.0631 0.04820 0.04570 -0.1437 0.9279 0.0267
-5.750 0.0980 0.04415 0.04157 -0.1515 0.9253 0.0282
-5.500 0.1312 0.03477 0.03181 -0.1639 0.9172 0.0314
-5.250 0.1599 0.03295 0.02992 -0.1664 0.9131 0.0323
-5.000 0.1957 0.02939 0.02611 -0.1713 0.9098 0.0350
-4.750 0.2236 0.01818 0.01360 -0.1758 0.9019 0.0249
-4.500 0.2558 0.01488 0.00974 -0.1774 0.8976 0.0230
-4.250 0.2901 0.01358 0.00816 -0.1790 0.8944 0.0234
-4.000 0.3164 0.01275 0.00716 -0.1787 0.8887 0.0239
-3.750 0.3456 0.01186 0.00612 -0.1789 0.8838 0.0240
-3.500 0.3777 0.01116 0.00529 -0.1797 0.8798 0.0245
-3.250 0.4055 0.01068 0.00474 -0.1797 0.8746 0.0252
-3.000 0.4334 0.01021 0.00421 -0.1797 0.8690 0.0260
-2.750 0.4646 0.00978 0.00375 -0.1804 0.8644 0.0274
-2.500 0.4925 0.00956 0.00350 -0.1803 0.8591 0.0295
-2.250 0.5204 0.00930 0.00323 -0.1803 0.8534 0.0330
-2.000 0.5511 0.00903 0.00295 -0.1808 0.8489 0.0411
-1.750 0.5791 0.00878 0.00280 -0.1808 0.8435 0.0756
-1.500 0.6066 0.00863 0.00271 -0.1808 0.8376 0.1021
-1.250 0.6369 0.00843 0.00262 -0.1813 0.8326 0.1508
-1.000 0.6638 0.00812 0.00262 -0.1814 0.8265 0.2601
-0.750 0.6919 0.00763 0.00265 -0.1818 0.8203 0.4622
-0.500 0.7210 0.00740 0.00273 -0.1821 0.8149 0.6077
-0.250 0.7458 0.00728 0.00279 -0.1813 0.8079 0.6771
0.000 0.7729 0.00719 0.00280 -0.1809 0.8017 0.7381
0.250 0.7967 0.00710 0.00285 -0.1798 0.7946 0.7993
0.500 0.8177 0.00697 0.00285 -0.1779 0.7873 0.8717
0.750 0.8411 0.00682 0.00277 -0.1766 0.7801 1.0000
1.000 0.8683 0.00688 0.00276 -0.1763 0.7722 1.0000
1.250 0.8957 0.00695 0.00277 -0.1762 0.7644 1.0000
1.500 0.9223 0.00701 0.00277 -0.1758 0.7554 1.0000
1.750 0.9485 0.00709 0.00280 -0.1754 0.7461 1.0000
2.000 0.9756 0.00718 0.00281 -0.1751 0.7371 1.0000
2.250 1.0006 0.00725 0.00287 -0.1745 0.7263 1.0000
2.500 1.0262 0.00734 0.00292 -0.1739 0.7152 1.0000
2.750 1.0514 0.00745 0.00296 -0.1733 0.7031 1.0000
3.000 1.0761 0.00757 0.00302 -0.1725 0.6900 1.0000
3.250 1.1003 0.00770 0.00311 -0.1717 0.6757 1.0000
3.500 1.1238 0.00786 0.00321 -0.1707 0.6595 1.0000
3.750 1.1467 0.00805 0.00332 -0.1696 0.6415 1.0000
4.000 1.1692 0.00825 0.00345 -0.1684 0.6226 1.0000
4.250 1.1911 0.00848 0.00360 -0.1672 0.6023 1.0000
4.500 1.2123 0.00874 0.00379 -0.1658 0.5818 1.0000
4.750 1.2329 0.00903 0.00399 -0.1643 0.5594 1.0000
5.000 1.2522 0.00937 0.00422 -0.1626 0.5345 1.0000
5.250 1.2712 0.00971 0.00447 -0.1608 0.5095 1.0000
5.500 1.2886 0.01013 0.00476 -0.1588 0.4824 1.0000
5.750 1.3044 0.01057 0.00507 -0.1564 0.4538 1.0000
6.000 1.3190 0.01105 0.00541 -0.1539 0.4230 1.0000
6.250 1.3326 0.01160 0.00581 -0.1512 0.3908 1.0000
6.500 1.3461 0.01220 0.00624 -0.1486 0.3580 1.0000
6.750 1.3601 0.01281 0.00669 -0.1461 0.3274 1.0000
7.000 1.3749 0.01340 0.00716 -0.1439 0.2994 1.0000
7.250 1.3897 0.01401 0.00766 -0.1416 0.2739 1.0000
7.750 1.4185 0.01532 0.00874 -0.1372 0.2262 1.0000
8.000 1.4320 0.01603 0.00933 -0.1349 0.2045 1.0000
8.250 1.4465 0.01670 0.00994 -0.1328 0.1860 1.0000
8.500 1.4609 0.01739 0.01056 -0.1308 0.1691 1.0000
8.750 1.4747 0.01813 0.01123 -0.1286 0.1534 1.0000
9.000 1.4885 0.01887 0.01193 -0.1266 0.1399 1.0000
9.250 1.5018 0.01965 0.01268 -0.1245 0.1284 1.0000
9.500 1.5143 0.02051 0.01348 -0.1224 0.1176 1.0000
9.750 1.5284 0.02126 0.01424 -0.1205 0.1089 1.0000
10.000 1.5414 0.02210 0.01508 -0.1185 0.1010 1.0000
10.250 1.5528 0.02308 0.01603 -0.1164 0.0932 1.0000
10.500 1.5663 0.02391 0.01691 -0.1147 0.0871 1.0000
10.750 1.5757 0.02507 0.01804 -0.1124 0.0804 1.0000
11.000 1.5895 0.02591 0.01895 -0.1108 0.0755 1.0000
11.250 1.5987 0.02713 0.02016 -0.1088 0.0701 1.0000
11.500 1.6109 0.02814 0.02124 -0.1071 0.0661 1.0000
11.750 1.6213 0.02931 0.02243 -0.1053 0.0620 1.0000
12.000 1.6281 0.03081 0.02395 -0.1032 0.0583 1.0000
12.250 1.6401 0.03190 0.02513 -0.1017 0.0556 1.0000
12.500 1.6489 0.03328 0.02655 -0.1001 0.0526 1.0000
12.750 1.6522 0.03519 0.02849 -0.0980 0.0496 1.0000
13.000 1.6638 0.03640 0.02980 -0.0967 0.0476 1.0000
13.250 1.6721 0.03792 0.03139 -0.0952 0.0453 1.0000
13.500 1.6765 0.03987 0.03337 -0.0936 0.0431 1.0000
13.750 1.6794 0.04203 0.03562 -0.0920 0.0412 1.0000
14.000 1.6878 0.04370 0.03740 -0.0909 0.0394 1.0000
14.250 1.6935 0.04566 0.03944 -0.0897 0.0377 1.0000
14.500 1.6947 0.04818 0.04201 -0.0884 0.0360 1.0000
14.750 1.6927 0.05114 0.04507 -0.0872 0.0345 1.0000
15.000 1.6988 0.05327 0.04732 -0.0864 0.0332 1.0000
15.250 1.7026 0.05571 0.04986 -0.0857 0.0318 1.0000
15.500 1.7038 0.05853 0.05276 -0.0851 0.0305 1.0000
15.750 1.6979 0.06235 0.05665 -0.0845 0.0293 1.0000
16.000 1.6966 0.06571 0.06013 -0.0842 0.0283 1.0000
16.250 1.6987 0.06870 0.06326 -0.0841 0.0273 1.0000
16.500 1.6987 0.07203 0.06670 -0.0841 0.0264 1.0000
16.750 1.6975 0.07562 0.07039 -0.0844 0.0256 1.0000
17.000 1.6932 0.07977 0.07462 -0.0849 0.0248 1.0000
17.250 1.6837 0.08478 0.07973 -0.0857 0.0241 1.0000
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