SG6050 (sg6050-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6050 (sg6050-il) Reynolds number: 500,000 Max Cl/Cd: 105.08 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6050-il-500000.txt Download as CSV file: xf-sg6050-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.7510 0.13745 0.13454 -0.0219 1.0000 0.0113
-17.750 -0.7703 0.12881 0.12577 -0.0266 1.0000 0.0112
-17.500 -0.7873 0.12091 0.11776 -0.0309 1.0000 0.0112
-17.250 -0.8028 0.11355 0.11029 -0.0349 1.0000 0.0112
-17.000 -0.8175 0.10656 0.10318 -0.0387 1.0000 0.0111
-16.750 -0.8313 0.09982 0.09633 -0.0424 1.0000 0.0111
-16.500 -0.8442 0.09344 0.08985 -0.0459 1.0000 0.0111
-16.250 -0.8563 0.08738 0.08368 -0.0493 1.0000 0.0111
-16.000 -0.8682 0.08154 0.07773 -0.0526 1.0000 0.0111
-15.750 -0.8805 0.07600 0.07208 -0.0556 1.0000 0.0112
-15.500 -0.8922 0.07072 0.06669 -0.0585 1.0000 0.0112
-15.250 -0.9031 0.06567 0.06154 -0.0613 1.0000 0.0112
-15.000 -0.9129 0.06078 0.05654 -0.0640 1.0000 0.0112
-14.750 -0.9210 0.05613 0.05178 -0.0667 1.0000 0.0112
-14.500 -0.9294 0.05142 0.04697 -0.0694 1.0000 0.0113
-14.250 -0.9376 0.04668 0.04212 -0.0723 1.0000 0.0114
-14.000 -0.9439 0.04207 0.03740 -0.0754 1.0000 0.0114
-13.750 -0.9483 0.03780 0.03301 -0.0785 1.0000 0.0115
-13.500 -0.9519 0.03417 0.02926 -0.0807 1.0000 0.0117
-13.250 -0.9548 0.03144 0.02643 -0.0812 1.0000 0.0118
-13.000 -0.9586 0.02944 0.02435 -0.0799 1.0000 0.0119
-12.750 -0.9677 0.02812 0.02296 -0.0762 1.0000 0.0121
-12.500 -0.9739 0.02715 0.02194 -0.0721 0.9994 0.0122
-12.250 -0.9473 0.02564 0.02033 -0.0743 0.9952 0.0127
-12.000 -0.9194 0.02430 0.01888 -0.0763 0.9902 0.0132
-11.750 -0.8910 0.02315 0.01760 -0.0780 0.9835 0.0137
-11.500 -0.8693 0.02172 0.01608 -0.0786 0.9717 0.0143
-11.250 -0.8472 0.02066 0.01494 -0.0787 0.9590 0.0150
-11.000 -0.8262 0.01982 0.01399 -0.0782 0.9457 0.0158
-10.500 -0.7877 0.01818 0.01215 -0.0761 0.9204 0.0184
-10.000 -0.7465 0.01654 0.01041 -0.0744 0.8996 0.0283
-9.750 -0.7223 0.01613 0.01001 -0.0741 0.8912 0.0395
-9.500 -0.6956 0.01595 0.00982 -0.0741 0.8827 0.0456
-9.250 -0.6696 0.01573 0.00956 -0.0739 0.8758 0.0498
-9.000 -0.6416 0.01564 0.00940 -0.0741 0.8684 0.0535
-8.750 -0.6154 0.01536 0.00904 -0.0740 0.8618 0.0567
-8.500 -0.5883 0.01514 0.00880 -0.0742 0.8553 0.0600
-8.250 -0.5605 0.01498 0.00856 -0.0743 0.8489 0.0629
-8.000 -0.5336 0.01476 0.00823 -0.0743 0.8433 0.0652
-7.750 -0.5069 0.01431 0.00779 -0.0745 0.8373 0.0690
-7.500 -0.4790 0.01413 0.00756 -0.0747 0.8317 0.0724
-7.250 -0.4508 0.01406 0.00738 -0.0748 0.8267 0.0752
-7.000 -0.4240 0.01353 0.00686 -0.0750 0.8213 0.0796
-6.750 -0.3960 0.01330 0.00660 -0.0752 0.8160 0.0836
-6.500 -0.3677 0.01313 0.00634 -0.0754 0.8112 0.0868
-6.250 -0.3400 0.01275 0.00591 -0.0756 0.8064 0.0903
-6.000 -0.3118 0.01241 0.00557 -0.0759 0.8012 0.0950
-5.750 -0.2833 0.01219 0.00529 -0.0762 0.7966 0.0994
-5.500 -0.2550 0.01190 0.00496 -0.0764 0.7922 0.1058
-5.250 -0.2261 0.01162 0.00470 -0.0768 0.7872 0.1146
-5.000 -0.1977 0.01125 0.00439 -0.0772 0.7824 0.1322
-4.750 -0.1698 0.01077 0.00406 -0.0775 0.7781 0.1725
-4.500 -0.1422 0.01016 0.00380 -0.0780 0.7734 0.2542
-4.250 -0.1134 0.00990 0.00373 -0.0784 0.7683 0.3081
-4.000 -0.0840 0.00983 0.00367 -0.0788 0.7635 0.3354
-3.750 -0.0544 0.00983 0.00364 -0.0792 0.7589 0.3532
-3.500 -0.0245 0.00982 0.00360 -0.0796 0.7538 0.3664
-3.250 0.0051 0.00978 0.00356 -0.0800 0.7490 0.3769
-3.000 0.0348 0.00978 0.00349 -0.0804 0.7446 0.3857
-2.750 0.0645 0.00976 0.00346 -0.0809 0.7399 0.3942
-2.500 0.0943 0.00973 0.00341 -0.0813 0.7347 0.4023
-2.250 0.1239 0.00969 0.00335 -0.0817 0.7300 0.4099
-2.000 0.1536 0.00971 0.00330 -0.0821 0.7254 0.4165
-1.750 0.1832 0.00962 0.00326 -0.0825 0.7201 0.4248
-1.500 0.2127 0.00958 0.00323 -0.0829 0.7150 0.4383
-1.250 0.2423 0.00961 0.00320 -0.0833 0.7103 0.4503
-1.000 0.2718 0.00950 0.00316 -0.0838 0.7047 0.4574
-0.750 0.3015 0.00945 0.00311 -0.0842 0.6991 0.4636
-0.500 0.3310 0.00943 0.00305 -0.0846 0.6941 0.4697
-0.250 0.3606 0.00935 0.00303 -0.0851 0.6881 0.4771
0.000 0.3902 0.00931 0.00299 -0.0855 0.6824 0.4853
0.250 0.4196 0.00927 0.00297 -0.0859 0.6771 0.4950
0.500 0.4491 0.00919 0.00297 -0.0864 0.6708 0.5075
0.750 0.4785 0.00913 0.00295 -0.0868 0.6648 0.5248
1.000 0.5078 0.00905 0.00297 -0.0872 0.6589 0.5521
1.250 0.5368 0.00887 0.00300 -0.0876 0.6521 0.6042
1.500 0.5648 0.00864 0.00304 -0.0877 0.6458 0.6950
1.750 0.5889 0.00832 0.00319 -0.0867 0.6385 0.8155
2.000 0.6111 0.00828 0.00327 -0.0851 0.6316 0.8894
2.250 0.6335 0.00827 0.00332 -0.0837 0.6244 0.9256
2.500 0.6572 0.00827 0.00334 -0.0825 0.6171 0.9534
2.750 0.6872 0.00830 0.00336 -0.0828 0.6095 0.9756
3.000 0.7226 0.00836 0.00339 -0.0845 0.6013 0.9918
3.250 0.7595 0.00841 0.00343 -0.0867 0.5929 1.0000
3.500 0.7862 0.00851 0.00348 -0.0866 0.5844 1.0000
3.750 0.8135 0.00860 0.00357 -0.0867 0.5757 1.0000
4.000 0.8409 0.00874 0.00364 -0.0867 0.5668 1.0000
4.250 0.8687 0.00884 0.00376 -0.0869 0.5570 1.0000
4.500 0.8962 0.00899 0.00386 -0.0870 0.5468 1.0000
4.750 0.9235 0.00915 0.00398 -0.0871 0.5358 1.0000
5.000 0.9510 0.00930 0.00413 -0.0872 0.5249 1.0000
5.250 0.9782 0.00948 0.00428 -0.0873 0.5142 1.0000
5.500 1.0049 0.00969 0.00444 -0.0873 0.5028 1.0000
5.750 1.0318 0.00987 0.00462 -0.0873 0.4907 1.0000
6.000 1.0583 0.01008 0.00482 -0.0873 0.4784 1.0000
6.250 1.0844 0.01032 0.00502 -0.0872 0.4661 1.0000
6.500 1.1099 0.01058 0.00525 -0.0870 0.4537 1.0000
6.750 1.1353 0.01084 0.00549 -0.0867 0.4406 1.0000
7.000 1.1604 0.01111 0.00574 -0.0865 0.4269 1.0000
7.250 1.1848 0.01141 0.00603 -0.0861 0.4127 1.0000
7.500 1.2087 0.01173 0.00632 -0.0856 0.3986 1.0000
7.750 1.2320 0.01207 0.00663 -0.0851 0.3843 1.0000
8.000 1.2546 0.01244 0.00697 -0.0844 0.3696 1.0000
8.250 1.2759 0.01285 0.00734 -0.0835 0.3526 1.0000
8.500 1.2952 0.01333 0.00776 -0.0823 0.3330 1.0000
8.750 1.3132 0.01387 0.00822 -0.0809 0.3142 1.0000
9.000 1.3299 0.01442 0.00872 -0.0792 0.2953 1.0000
9.250 1.3445 0.01502 0.00925 -0.0772 0.2747 1.0000
9.500 1.3540 0.01574 0.00989 -0.0744 0.2546 1.0000
9.750 1.3634 0.01657 0.01064 -0.0717 0.2349 1.0000
10.000 1.3731 0.01748 0.01147 -0.0693 0.2132 1.0000
10.250 1.3807 0.01858 0.01247 -0.0668 0.1921 1.0000
10.500 1.3888 0.01972 0.01353 -0.0645 0.1728 1.0000
10.750 1.3968 0.02095 0.01469 -0.0625 0.1551 1.0000
11.000 1.4044 0.02227 0.01595 -0.0605 0.1390 1.0000
11.250 1.4116 0.02368 0.01730 -0.0587 0.1242 1.0000
11.500 1.4184 0.02517 0.01875 -0.0570 0.1108 1.0000
11.750 1.4251 0.02672 0.02026 -0.0554 0.0988 1.0000
12.000 1.4316 0.02833 0.02185 -0.0538 0.0879 1.0000
12.250 1.4373 0.03004 0.02354 -0.0524 0.0781 1.0000
12.500 1.4421 0.03186 0.02535 -0.0510 0.0695 1.0000
13.000 1.4509 0.03570 0.02920 -0.0484 0.0550 1.0000
13.250 1.4543 0.03776 0.03127 -0.0472 0.0490 1.0000
13.500 1.4558 0.04002 0.03354 -0.0460 0.0434 1.0000
13.750 1.4574 0.04237 0.03591 -0.0449 0.0381 1.0000
14.000 1.4587 0.04481 0.03837 -0.0439 0.0334 1.0000
14.250 1.4578 0.04754 0.04114 -0.0430 0.0291 1.0000
14.500 1.4546 0.05061 0.04423 -0.0422 0.0255 1.0000
14.750 1.4529 0.05362 0.04730 -0.0416 0.0227 1.0000
15.000 1.4493 0.05692 0.05067 -0.0411 0.0206 1.0000
15.250 1.4474 0.06012 0.05393 -0.0408 0.0190 1.0000
15.500 1.4401 0.06406 0.05794 -0.0406 0.0179 1.0000
15.750 1.4396 0.06726 0.06124 -0.0405 0.0169 1.0000
16.000 1.4373 0.07071 0.06479 -0.0406 0.0162 1.0000
16.250 1.4334 0.07445 0.06861 -0.0408 0.0156 1.0000
16.500 1.4265 0.07866 0.07290 -0.0412 0.0151 1.0000
16.750 1.4155 0.08351 0.07785 -0.0418 0.0146 1.0000
17.000 1.4117 0.08742 0.08187 -0.0424 0.0143 1.0000
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