SG6042 (sg6042-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6042 (sg6042-il) Reynolds number: 100,000 Max Cl/Cd: 60.7 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6042-il-100000-n5.txt Download as CSV file: xf-sg6042-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SG6042
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3771 0.10095 0.09624 -0.0331 1.0000 0.0477
-8.000 -0.3872 0.09878 0.09416 -0.0317 1.0000 0.0476
-7.750 -0.3973 0.09629 0.09174 -0.0316 0.9991 0.0473
-7.500 -0.3966 0.08780 0.08322 -0.0389 0.9924 0.0301
-7.250 -0.3842 0.08282 0.07823 -0.0447 0.9866 0.0293
-7.000 -0.3710 0.07749 0.07289 -0.0514 0.9800 0.0292
-6.750 -0.3542 0.07098 0.06630 -0.0601 0.9739 0.0291
-6.500 -0.3418 0.06503 0.06025 -0.0660 0.9666 0.0291
-6.250 -0.3226 0.05945 0.05450 -0.0718 0.9615 0.0288
-6.000 -0.3070 0.05431 0.04917 -0.0756 0.9551 0.0283
-5.750 -0.2858 0.04849 0.04303 -0.0800 0.9497 0.0278
-5.500 -0.2578 0.04260 0.03665 -0.0847 0.9464 0.0275
-5.250 -0.2393 0.03818 0.03173 -0.0858 0.9397 0.0275
-5.000 -0.2101 0.03401 0.02690 -0.0880 0.9360 0.0283
-4.750 -0.1769 0.03062 0.02275 -0.0901 0.9334 0.0301
-4.500 -0.1521 0.02903 0.02095 -0.0903 0.9285 0.0313
-4.250 -0.1238 0.02727 0.01885 -0.0908 0.9242 0.0323
-4.000 -0.0912 0.02558 0.01682 -0.0918 0.9212 0.0338
-3.750 -0.0565 0.02427 0.01510 -0.0930 0.9189 0.0367
-3.500 -0.0317 0.02337 0.01421 -0.0928 0.9136 0.0394
-3.250 -0.0030 0.02247 0.01321 -0.0930 0.9091 0.0423
-3.000 0.0300 0.02154 0.01213 -0.0939 0.9060 0.0462
-2.750 0.0651 0.02083 0.01142 -0.0954 0.9036 0.0549
-2.500 0.0874 0.02030 0.01091 -0.0945 0.8968 0.0644
-2.250 0.1188 0.01974 0.01036 -0.0952 0.8926 0.0845
-2.000 0.1537 0.01914 0.00992 -0.0968 0.8898 0.1239
-1.750 0.1811 0.01859 0.00962 -0.0969 0.8844 0.1808
-1.500 0.2086 0.01772 0.00942 -0.0974 0.8791 0.3529
-1.250 0.2365 0.01682 0.00949 -0.0970 0.8757 0.6419
-1.000 0.2665 0.01646 0.00936 -0.0963 0.8730 0.7615
-0.750 0.2796 0.01642 0.00943 -0.0927 0.8639 0.8311
-0.500 0.3224 0.01607 0.00913 -0.0946 0.8610 0.9560
-0.250 0.3657 0.01591 0.00878 -0.0976 0.8582 1.0000
0.000 0.3872 0.01605 0.00878 -0.0966 0.8488 1.0000
0.250 0.4246 0.01593 0.00853 -0.0983 0.8445 1.0000
0.500 0.4510 0.01600 0.00849 -0.0980 0.8365 1.0000
0.750 0.4848 0.01593 0.00832 -0.0990 0.8306 1.0000
1.000 0.5157 0.01591 0.00822 -0.0994 0.8238 1.0000
1.250 0.5458 0.01587 0.00812 -0.0997 0.8160 1.0000
1.500 0.5765 0.01582 0.00801 -0.1000 0.8080 1.0000
2.000 0.6351 0.01573 0.00785 -0.1000 0.7893 1.0000
2.250 0.6716 0.01552 0.00760 -0.1013 0.7819 1.0000
2.500 0.6960 0.01556 0.00764 -0.1004 0.7693 1.0000
2.750 0.7226 0.01555 0.00762 -0.0998 0.7566 1.0000
3.000 0.7503 0.01550 0.00758 -0.0995 0.7432 1.0000
3.250 0.7783 0.01545 0.00753 -0.0991 0.7284 1.0000
3.500 0.8063 0.01541 0.00747 -0.0988 0.7121 1.0000
3.750 0.8351 0.01535 0.00742 -0.0985 0.6941 1.0000
4.000 0.8627 0.01536 0.00740 -0.0981 0.6742 1.0000
4.250 0.8885 0.01542 0.00744 -0.0973 0.6512 1.0000
4.500 0.9147 0.01552 0.00747 -0.0967 0.6253 1.0000
4.750 0.9402 0.01567 0.00756 -0.0959 0.5961 1.0000
5.000 0.9640 0.01592 0.00769 -0.0948 0.5631 1.0000
5.250 0.9863 0.01625 0.00788 -0.0935 0.5275 1.0000
5.500 1.0071 0.01667 0.00817 -0.0921 0.4912 1.0000
5.750 1.0262 0.01718 0.00852 -0.0904 0.4531 1.0000
6.000 1.0440 0.01776 0.00892 -0.0886 0.4161 1.0000
6.250 1.0607 0.01840 0.00940 -0.0867 0.3788 1.0000
6.500 1.0766 0.01910 0.00995 -0.0847 0.3436 1.0000
6.750 1.0917 0.01985 0.01054 -0.0826 0.3106 1.0000
7.000 1.1067 0.02062 0.01118 -0.0806 0.2803 1.0000
7.250 1.1215 0.02138 0.01184 -0.0786 0.2533 1.0000
7.500 1.1356 0.02217 0.01256 -0.0766 0.2293 1.0000
7.750 1.1494 0.02300 0.01331 -0.0745 0.2085 1.0000
8.000 1.1631 0.02386 0.01411 -0.0725 0.1904 1.0000
8.250 1.1773 0.02472 0.01494 -0.0706 0.1744 1.0000
8.500 1.1909 0.02563 0.01585 -0.0686 0.1608 1.0000
8.750 1.2040 0.02658 0.01679 -0.0667 0.1488 1.0000
9.000 1.2181 0.02751 0.01777 -0.0649 0.1377 1.0000
9.250 1.2313 0.02851 0.01882 -0.0631 0.1284 1.0000
9.750 1.2561 0.03066 0.02107 -0.0595 0.1123 1.0000
10.000 1.2666 0.03188 0.02229 -0.0576 0.1058 1.0000
10.250 1.2795 0.03301 0.02356 -0.0559 0.0992 1.0000
10.500 1.2883 0.03439 0.02491 -0.0540 0.0939 1.0000
10.750 1.3011 0.03559 0.02631 -0.0525 0.0879 1.0000
11.000 1.3103 0.03699 0.02777 -0.0508 0.0833 1.0000
11.250 1.3202 0.03846 0.02936 -0.0492 0.0788 1.0000
11.500 1.3299 0.03992 0.03097 -0.0477 0.0742 1.0000
11.750 1.3368 0.04156 0.03266 -0.0461 0.0708 1.0000
12.000 1.3455 0.04328 0.03453 -0.0447 0.0671 1.0000
12.250 1.3532 0.04502 0.03646 -0.0433 0.0635 1.0000
12.500 1.3588 0.04690 0.03845 -0.0420 0.0607 1.0000
12.750 1.3635 0.04901 0.04059 -0.0407 0.0583 1.0000
13.000 1.3691 0.05117 0.04304 -0.0395 0.0555 1.0000
13.250 1.3728 0.05344 0.04551 -0.0385 0.0530 1.0000
13.500 1.3749 0.05583 0.04802 -0.0375 0.0510 1.0000
13.750 1.3765 0.05838 0.05064 -0.0367 0.0494 1.0000
14.000 1.3773 0.06129 0.05374 -0.0360 0.0478 1.0000
14.250 1.3753 0.06454 0.05729 -0.0355 0.0461 1.0000
14.500 1.3716 0.06798 0.06101 -0.0353 0.0446 1.0000
14.750 1.3669 0.07160 0.06482 -0.0354 0.0432 1.0000
15.000 1.3618 0.07534 0.06874 -0.0357 0.0421 1.0000
15.250 1.3568 0.07923 0.07277 -0.0363 0.0412 1.0000
15.500 1.3522 0.08322 0.07687 -0.0371 0.0404 1.0000
15.750 1.3465 0.08759 0.08135 -0.0381 0.0397 1.0000
16.000 1.3308 0.09375 0.08782 -0.0404 0.0393 1.0000
16.250 1.3130 0.10061 0.09497 -0.0435 0.0389 1.0000
16.500 1.2923 0.10842 0.10306 -0.0476 0.0386 1.0000
16.750 1.2681 0.11744 0.11233 -0.0529 0.0385 1.0000
17.000 1.2391 0.12823 0.12336 -0.0598 0.0386 1.0000
17.250 1.2015 0.14219 0.13753 -0.0692 0.0390 1.0000
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Polar data table (+)
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