SG6043 (sg6043-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6043 (sg6043-il) Reynolds number: 1,000,000 Max Cl/Cd: 175.24 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6043-il-1000000.txt Download as CSV file: xf-sg6043-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1477 0.10361 0.10181 -0.0823 0.9835 0.0113
-9.750 -0.1390 0.09957 0.09777 -0.0855 0.9805 0.0114
-9.500 -0.1261 0.09582 0.09402 -0.0890 0.9787 0.0114
-9.250 -0.1126 0.09164 0.08985 -0.0930 0.9773 0.0115
-9.000 -0.1003 0.08692 0.08513 -0.0973 0.9761 0.0116
-8.750 -0.0828 0.08420 0.08241 -0.1000 0.9753 0.0118
-8.500 -0.0659 0.08143 0.07964 -0.1028 0.9739 0.0120
-8.250 -0.0584 0.07892 0.07714 -0.1036 0.9673 0.0122
-8.000 -0.0417 0.07557 0.07379 -0.1075 0.9651 0.0125
-7.750 -0.0240 0.07184 0.07007 -0.1122 0.9633 0.0129
-7.500 -0.0187 0.06873 0.06696 -0.1137 0.9545 0.0134
-7.000 0.0174 0.05461 0.05280 -0.1348 0.9393 0.0147
-6.750 0.0484 0.05157 0.04974 -0.1420 0.9342 0.0151
-6.500 0.0809 0.04732 0.04543 -0.1514 0.9264 0.0157
-6.250 0.1085 0.01535 0.01310 -0.1627 0.8868 0.0181
-6.000 0.1285 0.01396 0.01160 -0.1642 0.8796 0.0184
-5.750 0.1439 0.01413 0.00994 -0.1807 0.8869 0.0147
-5.500 0.1713 0.01264 0.00817 -0.1812 0.8809 0.0148
-5.250 0.1984 0.01162 0.00698 -0.1814 0.8753 0.0150
-5.000 0.2252 0.01093 0.00618 -0.1814 0.8694 0.0153
-4.750 0.2536 0.01034 0.00546 -0.1816 0.8641 0.0155
-4.500 0.2807 0.00983 0.00486 -0.1815 0.8588 0.0158
-4.250 0.3080 0.00936 0.00432 -0.1815 0.8532 0.0160
-4.000 0.3365 0.00901 0.00387 -0.1816 0.8480 0.0165
-3.750 0.3636 0.00870 0.00352 -0.1815 0.8426 0.0170
-3.500 0.3913 0.00838 0.00314 -0.1814 0.8371 0.0174
-3.250 0.4200 0.00815 0.00284 -0.1815 0.8320 0.0177
-3.000 0.4475 0.00775 0.00240 -0.1815 0.8270 0.0186
-2.750 0.4753 0.00756 0.00218 -0.1815 0.8218 0.0193
-2.500 0.5038 0.00743 0.00200 -0.1816 0.8168 0.0203
-2.250 0.5315 0.00730 0.00185 -0.1815 0.8117 0.0214
-2.000 0.5592 0.00716 0.00170 -0.1814 0.8061 0.0243
-1.750 0.5876 0.00701 0.00158 -0.1814 0.8005 0.0411
-1.500 0.6151 0.00686 0.00153 -0.1814 0.7949 0.0697
-1.250 0.6426 0.00678 0.00149 -0.1813 0.7889 0.0902
-1.000 0.6706 0.00670 0.00146 -0.1813 0.7831 0.1237
-0.750 0.6979 0.00652 0.00145 -0.1813 0.7767 0.1828
-0.500 0.7257 0.00629 0.00145 -0.1814 0.7700 0.2953
-0.250 0.7534 0.00596 0.00150 -0.1817 0.7635 0.4551
0.000 0.7806 0.00580 0.00157 -0.1816 0.7562 0.5636
0.250 0.8076 0.00573 0.00162 -0.1814 0.7491 0.6309
0.500 0.8342 0.00568 0.00167 -0.1810 0.7407 0.6815
0.750 0.8604 0.00565 0.00172 -0.1806 0.7320 0.7326
1.000 0.8858 0.00562 0.00178 -0.1800 0.7226 0.7845
1.250 0.9100 0.00556 0.00185 -0.1790 0.7130 0.8450
1.500 0.9285 0.00538 0.00184 -0.1766 0.7028 1.0000
1.750 0.9544 0.00549 0.00188 -0.1762 0.6907 1.0000
2.000 0.9801 0.00561 0.00193 -0.1757 0.6771 1.0000
2.250 1.0053 0.00574 0.00199 -0.1751 0.6628 1.0000
2.500 1.0304 0.00588 0.00207 -0.1745 0.6480 1.0000
2.750 1.0546 0.00606 0.00216 -0.1737 0.6306 1.0000
3.000 1.0779 0.00627 0.00227 -0.1727 0.6108 1.0000
3.250 1.1014 0.00648 0.00239 -0.1718 0.5895 1.0000
3.500 1.1244 0.00671 0.00253 -0.1708 0.5681 1.0000
3.750 1.1470 0.00697 0.00268 -0.1697 0.5473 1.0000
4.000 1.1698 0.00722 0.00284 -0.1687 0.5245 1.0000
4.250 1.1911 0.00754 0.00304 -0.1674 0.4986 1.0000
4.500 1.2127 0.00785 0.00324 -0.1662 0.4733 1.0000
4.750 1.2338 0.00819 0.00346 -0.1649 0.4479 1.0000
5.000 1.2537 0.00859 0.00371 -0.1634 0.4183 1.0000
5.250 1.2729 0.00901 0.00399 -0.1618 0.3880 1.0000
5.500 1.2905 0.00947 0.00428 -0.1598 0.3553 1.0000
5.750 1.3074 0.00996 0.00460 -0.1578 0.3224 1.0000
6.000 1.3246 0.01044 0.00493 -0.1558 0.2945 1.0000
6.250 1.3428 0.01086 0.00525 -0.1541 0.2709 1.0000
6.500 1.3603 0.01133 0.00560 -0.1522 0.2481 1.0000
6.750 1.3780 0.01179 0.00595 -0.1504 0.2255 1.0000
7.000 1.3946 0.01230 0.00635 -0.1484 0.2045 1.0000
7.250 1.4122 0.01276 0.00673 -0.1466 0.1870 1.0000
7.500 1.4298 0.01323 0.00713 -0.1449 0.1708 1.0000
7.750 1.4467 0.01373 0.00755 -0.1430 0.1551 1.0000
8.000 1.4634 0.01423 0.00800 -0.1412 0.1412 1.0000
8.250 1.4802 0.01474 0.00845 -0.1394 0.1292 1.0000
8.500 1.4964 0.01529 0.00894 -0.1375 0.1178 1.0000
8.750 1.5132 0.01579 0.00942 -0.1357 0.1089 1.0000
9.000 1.5297 0.01632 0.00993 -0.1340 0.1004 1.0000
9.250 1.5448 0.01694 0.01051 -0.1320 0.0918 1.0000
9.500 1.5614 0.01747 0.01104 -0.1303 0.0860 1.0000
9.750 1.5764 0.01811 0.01165 -0.1284 0.0791 1.0000
10.000 1.5915 0.01873 0.01227 -0.1266 0.0732 1.0000
10.250 1.6062 0.01940 0.01294 -0.1248 0.0676 1.0000
10.500 1.6205 0.02010 0.01363 -0.1229 0.0627 1.0000
10.750 1.6343 0.02085 0.01439 -0.1210 0.0579 1.0000
11.000 1.6483 0.02159 0.01514 -0.1192 0.0542 1.0000
11.250 1.6601 0.02250 0.01605 -0.1172 0.0497 1.0000
11.500 1.6745 0.02323 0.01683 -0.1156 0.0476 1.0000
11.750 1.6869 0.02414 0.01775 -0.1137 0.0448 1.0000
12.000 1.6971 0.02522 0.01884 -0.1117 0.0417 1.0000
12.250 1.7107 0.02605 0.01974 -0.1101 0.0403 1.0000
12.500 1.7225 0.02705 0.02078 -0.1084 0.0383 1.0000
12.750 1.7318 0.02827 0.02201 -0.1065 0.0361 1.0000
13.000 1.7419 0.02945 0.02325 -0.1048 0.0343 1.0000
13.250 1.7534 0.03052 0.02439 -0.1033 0.0329 1.0000
13.500 1.7627 0.03181 0.02571 -0.1016 0.0311 1.0000
13.750 1.7682 0.03348 0.02740 -0.0997 0.0289 1.0000
14.000 1.7799 0.03462 0.02862 -0.0984 0.0277 1.0000
14.250 1.7886 0.03605 0.03011 -0.0970 0.0262 1.0000
14.500 1.7944 0.03780 0.03189 -0.0954 0.0245 1.0000
14.750 1.8009 0.03953 0.03369 -0.0940 0.0233 1.0000
15.000 1.8085 0.04119 0.03542 -0.0928 0.0222 1.0000
15.250 1.8140 0.04311 0.03739 -0.0915 0.0210 1.0000
15.500 1.8161 0.04544 0.03977 -0.0902 0.0198 1.0000
15.750 1.8205 0.04759 0.04201 -0.0891 0.0190 1.0000
16.000 1.8255 0.04973 0.04423 -0.0882 0.0183 1.0000
16.250 1.8287 0.05212 0.04670 -0.0873 0.0175 1.0000
16.500 1.8299 0.05483 0.04947 -0.0866 0.0167 1.0000
16.750 1.8261 0.05823 0.05296 -0.0859 0.0159 1.0000
17.000 1.8293 0.06086 0.05568 -0.0855 0.0154 1.0000
17.250 1.8310 0.06372 0.05864 -0.0852 0.0150 1.0000
17.500 1.8311 0.06690 0.06191 -0.0851 0.0145 1.0000
17.750 1.8293 0.07042 0.06553 -0.0851 0.0141 1.0000
18.000 1.8257 0.07428 0.06948 -0.0854 0.0137 1.0000
18.250 1.8195 0.07865 0.07395 -0.0859 0.0133 1.0000
18.500 1.8100 0.08367 0.07908 -0.0868 0.0129 1.0000
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Polar data table (+)
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