SG6050 (sg6050-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6050 (sg6050-il) Reynolds number: 200,000 Max Cl/Cd: 74.66 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6050-il-200000.txt Download as CSV file: xf-sg6050-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SG6050
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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7211 0.07937 0.07530 -0.0623 1.0000 0.0258
-14.000 -0.7727 0.06691 0.06246 -0.0710 1.0000 0.0251
-13.750 -0.7970 0.05949 0.05478 -0.0762 1.0000 0.0250
-13.500 -0.8103 0.05409 0.04919 -0.0799 1.0000 0.0251
-13.250 -0.8192 0.04967 0.04460 -0.0826 1.0000 0.0253
-13.000 -0.8259 0.04594 0.04071 -0.0844 1.0000 0.0256
-12.750 -0.8317 0.04279 0.03741 -0.0852 1.0000 0.0259
-12.500 -0.8378 0.04017 0.03464 -0.0847 1.0000 0.0263
-12.250 -0.8460 0.03808 0.03241 -0.0827 1.0000 0.0267
-12.000 -0.8604 0.03665 0.03088 -0.0783 1.0000 0.0271
-11.750 -0.8764 0.03562 0.02976 -0.0729 1.0000 0.0274
-11.500 -0.8993 0.03513 0.02921 -0.0660 1.0000 0.0276
-11.250 -0.8881 0.03324 0.02704 -0.0657 0.9967 0.0286
-11.000 -0.8593 0.03151 0.02534 -0.0682 0.9925 0.0303
-10.750 -0.8296 0.03001 0.02360 -0.0705 0.9871 0.0333
-10.500 -0.7966 0.02885 0.02246 -0.0733 0.9833 0.0369
-10.250 -0.7673 0.02770 0.02120 -0.0751 0.9770 0.0420
-10.000 -0.7329 0.02681 0.02021 -0.0777 0.9728 0.0494
-9.750 -0.6986 0.02605 0.01931 -0.0802 0.9688 0.0572
-9.500 -0.6666 0.02580 0.01887 -0.0820 0.9625 0.0638
-9.250 -0.6325 0.02497 0.01808 -0.0843 0.9588 0.0698
-9.000 -0.6013 0.02473 0.01755 -0.0856 0.9528 0.0756
-8.750 -0.5717 0.02392 0.01685 -0.0869 0.9470 0.0821
-8.500 -0.5393 0.02347 0.01616 -0.0884 0.9427 0.0886
-8.250 -0.5137 0.02267 0.01542 -0.0886 0.9353 0.0938
-8.000 -0.4846 0.02208 0.01468 -0.0891 0.9295 0.0984
-7.750 -0.4569 0.02125 0.01371 -0.0894 0.9240 0.1023
-7.500 -0.4322 0.02046 0.01295 -0.0891 0.9165 0.1065
-7.250 -0.4048 0.01990 0.01231 -0.0891 0.9111 0.1111
-7.000 -0.3792 0.01950 0.01176 -0.0888 0.9041 0.1148
-6.750 -0.3547 0.01862 0.01095 -0.0884 0.8978 0.1198
-6.500 -0.3286 0.01813 0.01040 -0.0881 0.8929 0.1253
-6.250 -0.3033 0.01770 0.00990 -0.0878 0.8855 0.1307
-6.000 -0.2784 0.01708 0.00934 -0.0875 0.8798 0.1388
-5.750 -0.2529 0.01658 0.00884 -0.0872 0.8745 0.1492
-5.500 -0.2277 0.01605 0.00839 -0.0870 0.8677 0.1651
-5.250 -0.2029 0.01531 0.00787 -0.0868 0.8625 0.2039
-5.000 -0.1783 0.01473 0.00778 -0.0867 0.8570 0.3054
-4.750 -0.1507 0.01484 0.00789 -0.0867 0.8506 0.3520
-4.500 -0.1228 0.01493 0.00789 -0.0865 0.8456 0.3759
-4.250 -0.0948 0.01502 0.00789 -0.0865 0.8403 0.3936
-4.000 -0.0671 0.01506 0.00789 -0.0866 0.8339 0.4088
-3.750 -0.0391 0.01503 0.00779 -0.0865 0.8290 0.4224
-3.500 -0.0110 0.01502 0.00771 -0.0866 0.8237 0.4349
-3.250 0.0169 0.01500 0.00767 -0.0866 0.8172 0.4467
-3.000 0.0449 0.01488 0.00753 -0.0866 0.8122 0.4576
-2.750 0.0732 0.01485 0.00745 -0.0867 0.8068 0.4688
-2.500 0.1011 0.01484 0.00743 -0.0868 0.8003 0.4824
-2.250 0.1292 0.01477 0.00736 -0.0867 0.7955 0.5000
-2.000 0.1570 0.01473 0.00736 -0.0867 0.7901 0.5160
-1.750 0.1850 0.01462 0.00731 -0.0869 0.7836 0.5254
-1.500 0.2141 0.01453 0.00715 -0.0870 0.7788 0.5351
-1.250 0.2423 0.01444 0.00711 -0.0872 0.7732 0.5443
-1.000 0.2706 0.01437 0.00706 -0.0874 0.7667 0.5549
-0.750 0.2996 0.01425 0.00693 -0.0875 0.7618 0.5676
-0.500 0.3275 0.01418 0.00695 -0.0876 0.7557 0.5814
-0.250 0.3555 0.01406 0.00692 -0.0877 0.7492 0.5996
0.000 0.3841 0.01388 0.00681 -0.0877 0.7444 0.6244
0.250 0.4103 0.01374 0.00691 -0.0874 0.7373 0.6632
0.500 0.4346 0.01344 0.00693 -0.0863 0.7312 0.7346
0.750 0.4526 0.01320 0.00700 -0.0830 0.7266 0.8493
1.000 0.4739 0.01323 0.00716 -0.0809 0.7187 0.9258
1.250 0.5136 0.01317 0.00705 -0.0829 0.7130 0.9697
1.750 0.6025 0.01321 0.00700 -0.0901 0.6991 1.0000
2.000 0.6278 0.01319 0.00686 -0.0896 0.6939 1.0000
2.250 0.6500 0.01329 0.00698 -0.0888 0.6852 1.0000
2.500 0.6762 0.01327 0.00686 -0.0884 0.6792 1.0000
2.750 0.7005 0.01337 0.00697 -0.0879 0.6708 1.0000
3.000 0.7276 0.01337 0.00690 -0.0878 0.6640 1.0000
3.250 0.7534 0.01347 0.00700 -0.0875 0.6558 1.0000
3.500 0.7809 0.01349 0.00696 -0.0874 0.6484 1.0000
3.750 0.8073 0.01360 0.00709 -0.0873 0.6401 1.0000
4.000 0.8352 0.01364 0.00708 -0.0873 0.6323 1.0000
4.250 0.8616 0.01377 0.00722 -0.0871 0.6234 1.0000
4.500 0.8898 0.01383 0.00723 -0.0872 0.6154 1.0000
4.750 0.9158 0.01398 0.00742 -0.0870 0.6056 1.0000
5.000 0.9443 0.01407 0.00744 -0.0871 0.5975 1.0000
5.250 0.9697 0.01422 0.00764 -0.0868 0.5866 1.0000
5.500 0.9962 0.01435 0.00778 -0.0866 0.5763 1.0000
5.750 1.0236 0.01447 0.00784 -0.0865 0.5664 1.0000
6.000 1.0485 0.01464 0.00807 -0.0861 0.5546 1.0000
6.250 1.0741 0.01483 0.00827 -0.0858 0.5434 1.0000
6.500 1.1003 0.01502 0.00843 -0.0856 0.5325 1.0000
6.750 1.1250 0.01523 0.00865 -0.0851 0.5202 1.0000
7.000 1.1488 0.01548 0.00893 -0.0845 0.5072 1.0000
7.250 1.1727 0.01574 0.00922 -0.0839 0.4944 1.0000
7.500 1.1963 0.01603 0.00950 -0.0833 0.4817 1.0000
7.750 1.2192 0.01633 0.00979 -0.0826 0.4685 1.0000
8.000 1.2412 0.01667 0.01011 -0.0817 0.4546 1.0000
8.250 1.2616 0.01702 0.01049 -0.0805 0.4398 1.0000
8.500 1.2811 0.01742 0.01091 -0.0793 0.4248 1.0000
8.750 1.2996 0.01785 0.01136 -0.0779 0.4097 1.0000
9.000 1.3167 0.01832 0.01185 -0.0762 0.3943 1.0000
9.250 1.3321 0.01883 0.01237 -0.0743 0.3785 1.0000
9.500 1.3448 0.01940 0.01294 -0.0720 0.3619 1.0000
9.750 1.3538 0.02004 0.01356 -0.0691 0.3452 1.0000
10.000 1.3598 0.02079 0.01429 -0.0658 0.3287 1.0000
10.250 1.3661 0.02166 0.01517 -0.0628 0.3118 1.0000
10.500 1.3724 0.02265 0.01617 -0.0601 0.2941 1.0000
10.750 1.3777 0.02379 0.01732 -0.0575 0.2758 1.0000
11.000 1.3814 0.02514 0.01864 -0.0550 0.2570 1.0000
11.250 1.3832 0.02673 0.02017 -0.0525 0.2378 1.0000
11.500 1.3845 0.02848 0.02187 -0.0503 0.2180 1.0000
11.750 1.3851 0.03040 0.02375 -0.0482 0.1978 1.0000
12.000 1.3835 0.03257 0.02585 -0.0462 0.1793 1.0000
12.250 1.3812 0.03492 0.02812 -0.0444 0.1625 1.0000
12.500 1.3801 0.03726 0.03042 -0.0428 0.1467 1.0000
12.750 1.3785 0.03972 0.03285 -0.0414 0.1325 1.0000
13.000 1.3757 0.04237 0.03547 -0.0400 0.1204 1.0000
13.250 1.3740 0.04499 0.03810 -0.0388 0.1090 1.0000
13.500 1.3723 0.04771 0.04084 -0.0378 0.0986 1.0000
13.750 1.3697 0.05065 0.04380 -0.0370 0.0894 1.0000
14.000 1.3642 0.05395 0.04709 -0.0362 0.0817 1.0000
14.250 1.3612 0.05711 0.05029 -0.0356 0.0740 1.0000
14.500 1.3574 0.06047 0.05370 -0.0352 0.0674 1.0000
14.750 1.3495 0.06437 0.05758 -0.0349 0.0621 1.0000
15.000 1.3467 0.06778 0.06110 -0.0348 0.0563 1.0000
15.250 1.3365 0.07210 0.06537 -0.0347 0.0522 1.0000
15.500 1.3343 0.07565 0.06905 -0.0349 0.0474 1.0000
15.750 1.3245 0.08006 0.07344 -0.0351 0.0442 1.0000
16.000 1.3220 0.08374 0.07725 -0.0354 0.0406 1.0000
16.250 1.3163 0.08782 0.08135 -0.0360 0.0381 1.0000
16.500 1.3120 0.09166 0.08527 -0.0363 0.0358 1.0000
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