SG6050 (sg6050-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6050 (sg6050-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.96 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6050-il-1000000-n5.txt Download as CSV file: xf-sg6050-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.8755 0.10885 0.10603 -0.0341 1.0000 0.0048
-17.250 -0.9292 0.09520 0.09217 -0.0410 1.0000 0.0047
-17.000 -0.9740 0.08361 0.08040 -0.0471 1.0000 0.0046
-16.750 -1.0128 0.07383 0.07045 -0.0524 1.0000 0.0046
-16.500 -1.0445 0.06560 0.06207 -0.0569 1.0000 0.0046
-16.250 -1.0710 0.05829 0.05462 -0.0611 1.0000 0.0046
-16.000 -1.0916 0.05169 0.04788 -0.0651 1.0000 0.0046
-15.750 -1.1056 0.04572 0.04178 -0.0691 1.0000 0.0046
-15.500 -1.1134 0.04043 0.03635 -0.0732 1.0000 0.0046
-15.250 -1.1170 0.03595 0.03173 -0.0768 1.0000 0.0046
-15.000 -1.1179 0.03245 0.02810 -0.0793 1.0000 0.0047
-14.750 -1.1170 0.02986 0.02540 -0.0801 1.0000 0.0047
-14.500 -1.1150 0.02790 0.02334 -0.0798 1.0000 0.0047
-14.250 -1.1087 0.02633 0.02167 -0.0792 0.9915 0.0048
-14.000 -1.1009 0.02507 0.02031 -0.0780 0.9664 0.0049
-13.750 -1.0932 0.02413 0.01923 -0.0757 0.9327 0.0049
-13.500 -1.0819 0.02328 0.01822 -0.0739 0.9088 0.0050
-13.250 -1.0667 0.02247 0.01728 -0.0727 0.8912 0.0050
-12.750 -1.0301 0.02102 0.01558 -0.0711 0.8648 0.0051
-12.500 -1.0100 0.02032 0.01478 -0.0705 0.8551 0.0052
-12.250 -0.9899 0.01955 0.01390 -0.0699 0.8455 0.0054
-12.000 -0.9684 0.01886 0.01311 -0.0695 0.8371 0.0055
-11.750 -0.9459 0.01824 0.01240 -0.0691 0.8287 0.0057
-11.500 -0.9224 0.01767 0.01176 -0.0689 0.8218 0.0059
-11.250 -0.8983 0.01714 0.01116 -0.0687 0.8151 0.0061
-11.000 -0.8737 0.01666 0.01060 -0.0685 0.8091 0.0064
-10.750 -0.8484 0.01620 0.01006 -0.0685 0.8033 0.0066
-10.500 -0.8227 0.01578 0.00957 -0.0685 0.7972 0.0069
-10.250 -0.7971 0.01531 0.00905 -0.0684 0.7918 0.0074
-10.000 -0.7710 0.01486 0.00856 -0.0685 0.7868 0.0079
-9.750 -0.7446 0.01446 0.00810 -0.0686 0.7816 0.0086
-9.250 -0.6913 0.01363 0.00719 -0.0688 0.7720 0.0119
-9.000 -0.6646 0.01317 0.00672 -0.0689 0.7670 0.0160
-8.750 -0.6377 0.01273 0.00627 -0.0691 0.7621 0.0217
-8.500 -0.6104 0.01234 0.00589 -0.0693 0.7578 0.0283
-8.250 -0.5824 0.01201 0.00559 -0.0696 0.7534 0.0345
-8.000 -0.5540 0.01177 0.00534 -0.0699 0.7489 0.0392
-7.750 -0.5256 0.01155 0.00510 -0.0702 0.7447 0.0426
-7.500 -0.4967 0.01136 0.00489 -0.0706 0.7408 0.0458
-7.250 -0.4679 0.01114 0.00468 -0.0709 0.7367 0.0494
-7.000 -0.4389 0.01096 0.00449 -0.0713 0.7324 0.0528
-6.750 -0.4097 0.01083 0.00431 -0.0717 0.7283 0.0547
-6.500 -0.3806 0.01063 0.00411 -0.0721 0.7247 0.0578
-6.250 -0.3514 0.01045 0.00392 -0.0725 0.7208 0.0609
-6.000 -0.3220 0.01031 0.00376 -0.0730 0.7165 0.0634
-5.750 -0.2926 0.01017 0.00359 -0.0734 0.7124 0.0664
-5.500 -0.2633 0.01000 0.00342 -0.0738 0.7087 0.0703
-5.250 -0.2337 0.00985 0.00326 -0.0743 0.7044 0.0734
-5.000 -0.2041 0.00973 0.00312 -0.0747 0.6993 0.0760
-4.750 -0.1747 0.00958 0.00296 -0.0752 0.6945 0.0822
-4.500 -0.1450 0.00945 0.00284 -0.0756 0.6899 0.0877
-4.250 -0.1154 0.00929 0.00270 -0.0761 0.6850 0.0970
-4.000 -0.0858 0.00914 0.00257 -0.0766 0.6801 0.1085
-3.750 -0.0562 0.00897 0.00244 -0.0771 0.6758 0.1242
-3.250 0.0029 0.00855 0.00218 -0.0782 0.6655 0.1767
-3.000 0.0321 0.00824 0.00204 -0.0787 0.6608 0.2258
-2.750 0.0617 0.00802 0.00195 -0.0793 0.6555 0.2655
-2.500 0.0914 0.00790 0.00190 -0.0798 0.6499 0.2925
-2.250 0.1212 0.00784 0.00186 -0.0803 0.6446 0.3117
-2.000 0.1512 0.00779 0.00184 -0.0809 0.6387 0.3259
-1.750 0.1810 0.00777 0.00182 -0.0813 0.6323 0.3380
-1.500 0.2110 0.00776 0.00181 -0.0818 0.6262 0.3473
-1.250 0.2409 0.00775 0.00180 -0.0823 0.6194 0.3567
-1.000 0.2706 0.00775 0.00181 -0.0828 0.6131 0.3731
-0.750 0.3006 0.00774 0.00182 -0.0833 0.6071 0.3844
-0.500 0.3304 0.00775 0.00182 -0.0838 0.6005 0.3907
-0.250 0.3603 0.00777 0.00182 -0.0843 0.5942 0.3945
0.000 0.3901 0.00780 0.00183 -0.0848 0.5871 0.3974
0.250 0.4198 0.00783 0.00184 -0.0853 0.5803 0.4009
0.500 0.4496 0.00784 0.00185 -0.0858 0.5723 0.4051
0.750 0.4791 0.00789 0.00188 -0.0862 0.5639 0.4091
1.000 0.5086 0.00794 0.00190 -0.0866 0.5544 0.4132
1.250 0.5381 0.00799 0.00194 -0.0871 0.5457 0.4174
1.500 0.5674 0.00804 0.00198 -0.0875 0.5366 0.4225
1.750 0.5968 0.00809 0.00203 -0.0880 0.5282 0.4281
2.250 0.6553 0.00821 0.00214 -0.0888 0.5106 0.4404
2.500 0.6842 0.00830 0.00221 -0.0892 0.5014 0.4483
2.750 0.7134 0.00834 0.00229 -0.0896 0.4924 0.4599
3.000 0.7423 0.00840 0.00238 -0.0900 0.4832 0.4751
3.250 0.7710 0.00846 0.00247 -0.0904 0.4728 0.4975
3.500 0.7998 0.00849 0.00258 -0.0908 0.4626 0.5328
3.750 0.8280 0.00851 0.00271 -0.0911 0.4498 0.5840
4.000 0.8561 0.00853 0.00285 -0.0915 0.4369 0.6487
4.250 0.8841 0.00852 0.00301 -0.0918 0.4250 0.7164
4.500 0.9113 0.00846 0.00318 -0.0918 0.4140 0.7991
4.750 0.9370 0.00853 0.00338 -0.0914 0.4030 0.8600
5.000 0.9626 0.00869 0.00355 -0.0911 0.3903 0.8861
5.250 0.9878 0.00887 0.00373 -0.0907 0.3762 0.9051
5.500 1.0120 0.00904 0.00390 -0.0900 0.3633 0.9244
5.750 1.0339 0.00920 0.00407 -0.0888 0.3511 0.9455
6.000 1.0557 0.00937 0.00422 -0.0876 0.3386 0.9741
6.250 1.0833 0.00959 0.00439 -0.0878 0.3247 1.0000
6.500 1.1088 0.00991 0.00464 -0.0877 0.3079 1.0000
6.750 1.1338 0.01024 0.00490 -0.0875 0.2906 1.0000
7.000 1.1584 0.01059 0.00518 -0.0872 0.2742 1.0000
7.250 1.1824 0.01097 0.00548 -0.0868 0.2577 1.0000
7.500 1.2049 0.01142 0.00583 -0.0861 0.2380 1.0000
7.750 1.2246 0.01202 0.00628 -0.0850 0.2097 1.0000
8.000 1.2417 0.01273 0.00681 -0.0835 0.1791 1.0000
8.250 1.2599 0.01333 0.00730 -0.0822 0.1584 1.0000
8.500 1.2776 0.01389 0.00777 -0.0808 0.1413 1.0000
8.750 1.2942 0.01448 0.00828 -0.0791 0.1258 1.0000
9.000 1.3071 0.01508 0.00883 -0.0768 0.1122 1.0000
9.250 1.3198 0.01574 0.00944 -0.0745 0.1001 1.0000
9.500 1.3322 0.01648 0.01012 -0.0723 0.0879 1.0000
9.750 1.3436 0.01732 0.01090 -0.0702 0.0753 1.0000
10.000 1.3555 0.01820 0.01172 -0.0682 0.0649 1.0000
10.250 1.3680 0.01908 0.01258 -0.0665 0.0565 1.0000
10.500 1.3804 0.02003 0.01351 -0.0649 0.0496 1.0000
10.750 1.3924 0.02103 0.01450 -0.0633 0.0434 1.0000
11.000 1.4046 0.02207 0.01552 -0.0619 0.0381 1.0000
11.250 1.4168 0.02315 0.01661 -0.0606 0.0335 1.0000
11.500 1.4281 0.02432 0.01778 -0.0593 0.0293 1.0000
11.750 1.4385 0.02558 0.01904 -0.0580 0.0257 1.0000
12.000 1.4495 0.02683 0.02031 -0.0568 0.0228 1.0000
12.250 1.4598 0.02817 0.02167 -0.0556 0.0203 1.0000
12.500 1.4688 0.02962 0.02314 -0.0544 0.0179 1.0000
12.750 1.4779 0.03109 0.02465 -0.0533 0.0155 1.0000
13.000 1.4856 0.03271 0.02629 -0.0522 0.0133 1.0000
13.250 1.4925 0.03443 0.02804 -0.0511 0.0113 1.0000
13.500 1.4988 0.03621 0.02985 -0.0500 0.0098 1.0000
13.750 1.5054 0.03799 0.03168 -0.0491 0.0089 1.0000
14.000 1.5114 0.03989 0.03362 -0.0482 0.0082 1.0000
14.250 1.5165 0.04192 0.03571 -0.0473 0.0077 1.0000
14.500 1.5223 0.04392 0.03777 -0.0466 0.0073 1.0000
14.750 1.5278 0.04600 0.03990 -0.0459 0.0070 1.0000
15.000 1.5323 0.04823 0.04220 -0.0453 0.0068 1.0000
15.250 1.5359 0.05061 0.04464 -0.0448 0.0065 1.0000
15.500 1.5389 0.05311 0.04720 -0.0443 0.0063 1.0000
15.750 1.5408 0.05574 0.04991 -0.0439 0.0061 1.0000
16.000 1.5418 0.05854 0.05277 -0.0436 0.0059 1.0000
16.250 1.5426 0.06143 0.05573 -0.0434 0.0058 1.0000
16.500 1.5439 0.06432 0.05871 -0.0433 0.0057 1.0000
16.750 1.5444 0.06735 0.06182 -0.0432 0.0056 1.0000
17.000 1.5440 0.07050 0.06505 -0.0433 0.0055 1.0000
17.250 1.5429 0.07378 0.06841 -0.0434 0.0054 1.0000
17.500 1.5412 0.07721 0.07192 -0.0437 0.0054 1.0000
17.750 1.5388 0.08078 0.07557 -0.0441 0.0053 1.0000
18.000 1.5353 0.08454 0.07942 -0.0446 0.0052 1.0000
18.250 1.5310 0.08842 0.08339 -0.0451 0.0051 1.0000
18.500 1.5259 0.09246 0.08751 -0.0458 0.0050 1.0000
18.750 1.5204 0.09663 0.09178 -0.0467 0.0049 1.0000
19.000 1.5145 0.10091 0.09615 -0.0476 0.0048 1.0000
19.250 1.5078 0.10535 0.10067 -0.0488 0.0048 1.0000
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