SG6041 (sg6041-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6041 (sg6041-il) Reynolds number: 500,000 Max Cl/Cd: 74.2 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6041-il-500000-n5.txt Download as CSV file: xf-sg6041-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SG6041
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4709 0.08138 0.07907 -0.0398 1.0000 0.0060
-9.250 -0.4840 0.07606 0.07380 -0.0418 1.0000 0.0059
-9.000 -0.6360 0.03190 0.02838 -0.0650 0.9842 0.0050
-8.750 -0.6311 0.02609 0.02187 -0.0650 0.9766 0.0051
-8.500 -0.6091 0.02324 0.01860 -0.0659 0.9736 0.0052
-8.250 -0.5819 0.02158 0.01670 -0.0670 0.9718 0.0054
-8.000 -0.5604 0.02024 0.01516 -0.0665 0.9664 0.0055
-7.750 -0.5343 0.01910 0.01383 -0.0668 0.9627 0.0058
-7.500 -0.5068 0.01789 0.01242 -0.0674 0.9599 0.0060
-7.250 -0.4777 0.01683 0.01117 -0.0681 0.9577 0.0063
-7.000 -0.4547 0.01592 0.01010 -0.0674 0.9520 0.0065
-6.750 -0.4280 0.01508 0.00913 -0.0674 0.9480 0.0067
-6.500 -0.3994 0.01433 0.00825 -0.0678 0.9449 0.0070
-6.250 -0.3730 0.01367 0.00749 -0.0677 0.9408 0.0074
-6.000 -0.3479 0.01306 0.00682 -0.0674 0.9355 0.0078
-5.750 -0.3197 0.01267 0.00639 -0.0676 0.9317 0.0085
-5.500 -0.2921 0.01217 0.00583 -0.0677 0.9279 0.0092
-5.250 -0.2672 0.01173 0.00531 -0.0671 0.9221 0.0096
-5.000 -0.2407 0.01123 0.00476 -0.0669 0.9175 0.0104
-4.750 -0.2133 0.01086 0.00433 -0.0669 0.9135 0.0117
-4.500 -0.1880 0.01054 0.00396 -0.0663 0.9079 0.0133
-4.250 -0.1614 0.01021 0.00361 -0.0661 0.9029 0.0162
-4.000 -0.1342 0.00992 0.00331 -0.0660 0.8986 0.0211
-3.750 -0.1088 0.00966 0.00308 -0.0655 0.8926 0.0299
-3.500 -0.0821 0.00941 0.00287 -0.0653 0.8873 0.0415
-3.250 -0.0552 0.00920 0.00268 -0.0651 0.8823 0.0550
-3.000 -0.0290 0.00901 0.00251 -0.0648 0.8762 0.0685
-2.750 -0.0021 0.00880 0.00234 -0.0646 0.8708 0.0876
-2.250 0.0489 0.00815 0.00203 -0.0638 0.8576 0.1920
-2.000 0.0738 0.00775 0.00188 -0.0634 0.8510 0.2781
-1.750 0.0976 0.00724 0.00174 -0.0629 0.8434 0.3955
-1.500 0.1213 0.00676 0.00163 -0.0622 0.8361 0.5164
-1.250 0.1450 0.00642 0.00160 -0.0613 0.8275 0.6185
-1.000 0.1704 0.00630 0.00160 -0.0606 0.8187 0.6742
-0.750 0.1969 0.00625 0.00157 -0.0601 0.8095 0.7051
-0.500 0.2227 0.00619 0.00158 -0.0595 0.7981 0.7356
-0.250 0.2480 0.00615 0.00159 -0.0587 0.7857 0.7684
0.000 0.2738 0.00615 0.00159 -0.0581 0.7720 0.7902
0.250 0.2998 0.00616 0.00158 -0.0574 0.7559 0.8053
0.500 0.3255 0.00619 0.00155 -0.0568 0.7365 0.8159
0.750 0.3513 0.00626 0.00154 -0.0562 0.7135 0.8243
1.000 0.3766 0.00635 0.00154 -0.0556 0.6895 0.8321
1.250 0.4016 0.00646 0.00156 -0.0549 0.6627 0.8400
1.500 0.4258 0.00661 0.00160 -0.0540 0.6315 0.8484
1.750 0.4495 0.00679 0.00166 -0.0531 0.5964 0.8570
2.000 0.4724 0.00702 0.00174 -0.0520 0.5574 0.8668
2.250 0.4953 0.00725 0.00183 -0.0509 0.5186 0.8769
2.750 0.5412 0.00773 0.00208 -0.0489 0.4459 0.9007
3.000 0.5642 0.00799 0.00222 -0.0480 0.4094 0.9152
3.250 0.5891 0.00825 0.00237 -0.0474 0.3750 0.9311
3.500 0.6171 0.00861 0.00256 -0.0477 0.3336 0.9478
3.750 0.6488 0.00898 0.00277 -0.0488 0.2929 0.9638
4.000 0.6813 0.00935 0.00298 -0.0501 0.2582 0.9802
4.250 0.7136 0.00970 0.00320 -0.0514 0.2286 0.9961
4.500 0.7388 0.01000 0.00340 -0.0512 0.2070 1.0000
5.000 0.7834 0.01061 0.00383 -0.0493 0.1690 1.0000
5.250 0.8063 0.01090 0.00407 -0.0484 0.1538 1.0000
5.500 0.8294 0.01119 0.00431 -0.0477 0.1411 1.0000
5.750 0.8524 0.01149 0.00456 -0.0469 0.1293 1.0000
6.000 0.8755 0.01180 0.00484 -0.0461 0.1178 1.0000
6.250 0.8986 0.01211 0.00512 -0.0454 0.1075 1.0000
6.500 0.9216 0.01243 0.00541 -0.0446 0.0983 1.0000
6.750 0.9441 0.01279 0.00573 -0.0438 0.0884 1.0000
7.000 0.9666 0.01315 0.00606 -0.0430 0.0795 1.0000
7.250 0.9894 0.01348 0.00640 -0.0422 0.0730 1.0000
7.500 1.0115 0.01387 0.00676 -0.0413 0.0667 1.0000
7.750 1.0340 0.01421 0.00713 -0.0405 0.0624 1.0000
8.000 1.0559 0.01459 0.00752 -0.0396 0.0578 1.0000
8.250 1.0773 0.01501 0.00794 -0.0387 0.0534 1.0000
8.500 1.0990 0.01537 0.00835 -0.0378 0.0496 1.0000
8.750 1.1197 0.01582 0.00880 -0.0367 0.0457 1.0000
9.000 1.1403 0.01626 0.00929 -0.0357 0.0427 1.0000
9.250 1.1607 0.01668 0.00975 -0.0346 0.0393 1.0000
9.500 1.1797 0.01722 0.01028 -0.0333 0.0355 1.0000
9.750 1.1988 0.01767 0.01080 -0.0320 0.0331 1.0000
10.000 1.2163 0.01817 0.01133 -0.0305 0.0305 1.0000
10.250 1.2323 0.01876 0.01195 -0.0287 0.0281 1.0000
10.500 1.2484 0.01931 0.01257 -0.0270 0.0263 1.0000
10.750 1.2642 0.01989 0.01321 -0.0253 0.0247 1.0000
11.000 1.2790 0.02054 0.01389 -0.0235 0.0232 1.0000
11.250 1.2922 0.02130 0.01470 -0.0215 0.0218 1.0000
11.500 1.3058 0.02202 0.01551 -0.0196 0.0209 1.0000
11.750 1.3193 0.02274 0.01633 -0.0179 0.0200 1.0000
12.000 1.3323 0.02351 0.01718 -0.0161 0.0190 1.0000
12.250 1.3438 0.02438 0.01813 -0.0142 0.0183 1.0000
12.500 1.3541 0.02535 0.01917 -0.0123 0.0174 1.0000
12.750 1.3612 0.02656 0.02046 -0.0102 0.0167 1.0000
13.000 1.3698 0.02768 0.02168 -0.0084 0.0161 1.0000
13.250 1.3795 0.02875 0.02286 -0.0068 0.0156 1.0000
13.500 1.3868 0.03002 0.02425 -0.0051 0.0151 1.0000
13.750 1.3943 0.03132 0.02567 -0.0036 0.0145 1.0000
14.000 1.4001 0.03279 0.02725 -0.0021 0.0141 1.0000
14.250 1.4048 0.03442 0.02897 -0.0008 0.0135 1.0000
14.500 1.4074 0.03628 0.03092 0.0005 0.0130 1.0000
14.750 1.4079 0.03843 0.03317 0.0016 0.0123 1.0000
15.000 1.4107 0.04046 0.03534 0.0024 0.0120 1.0000
15.250 1.4138 0.04256 0.03757 0.0029 0.0115 1.0000
15.500 1.4123 0.04525 0.04039 0.0032 0.0112 1.0000
15.750 1.4148 0.04763 0.04288 0.0033 0.0105 1.0000
16.000 1.4133 0.05060 0.04594 0.0030 0.0100 1.0000
16.250 1.4055 0.05458 0.05008 0.0022 0.0100 1.0000
16.500 1.3975 0.05885 0.05448 0.0009 0.0098 1.0000
16.750 1.3871 0.06378 0.05954 -0.0010 0.0095 1.0000
17.000 1.3751 0.06928 0.06518 -0.0034 0.0092 1.0000
17.250 1.3561 0.07629 0.07238 -0.0069 0.0094 1.0000
17.500 1.3411 0.08296 0.07921 -0.0104 0.0092 1.0000
17.750 1.3193 0.09116 0.08757 -0.0149 0.0092 1.0000
18.000 1.2960 0.09991 0.09648 -0.0197 0.0092 1.0000
18.250 1.2666 0.11014 0.10687 -0.0254 0.0093 1.0000
18.500 1.2426 0.11949 0.11637 -0.0307 0.0093 1.0000
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Polar data table (+)
Polar graphs
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