SG6050 (sg6050-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6050 (sg6050-il) Reynolds number: 500,000 Max Cl/Cd: 97.26 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6050-il-500000-n5.txt Download as CSV file: xf-sg6050-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8413 0.09341 0.08977 -0.0434 1.0000 0.0070
-16.000 -0.8696 0.08448 0.08069 -0.0481 1.0000 0.0069
-15.750 -0.8984 0.07603 0.07210 -0.0527 1.0000 0.0069
-15.500 -0.9236 0.06849 0.06443 -0.0569 1.0000 0.0069
-15.250 -0.9459 0.06159 0.05739 -0.0608 1.0000 0.0069
-15.000 -0.9642 0.05529 0.05096 -0.0646 1.0000 0.0069
-14.750 -0.9780 0.04949 0.04503 -0.0684 1.0000 0.0069
-14.500 -0.9866 0.04416 0.03954 -0.0723 1.0000 0.0069
-14.250 -0.9911 0.03945 0.03468 -0.0760 1.0000 0.0070
-14.000 -0.9963 0.03519 0.03027 -0.0792 1.0000 0.0070
-13.750 -1.0003 0.03204 0.02699 -0.0805 1.0000 0.0071
-13.500 -1.0034 0.02980 0.02465 -0.0799 1.0000 0.0072
-13.250 -1.0045 0.02817 0.02292 -0.0782 0.9956 0.0074
-13.000 -0.9909 0.02668 0.02132 -0.0783 0.9801 0.0075
-12.750 -0.9745 0.02544 0.01997 -0.0782 0.9601 0.0078
-12.500 -0.9575 0.02437 0.01878 -0.0777 0.9408 0.0080
-12.250 -0.9421 0.02346 0.01772 -0.0766 0.9225 0.0082
-12.000 -0.9257 0.02264 0.01675 -0.0754 0.9065 0.0085
-11.750 -0.9078 0.02188 0.01585 -0.0744 0.8929 0.0088
-11.500 -0.8882 0.02114 0.01499 -0.0736 0.8814 0.0090
-11.250 -0.8684 0.02035 0.01409 -0.0730 0.8715 0.0095
-11.000 -0.8471 0.01967 0.01329 -0.0724 0.8619 0.0100
-10.750 -0.8246 0.01904 0.01255 -0.0720 0.8534 0.0107
-10.500 -0.8016 0.01844 0.01184 -0.0716 0.8453 0.0115
-10.250 -0.7782 0.01780 0.01114 -0.0714 0.8385 0.0130
-10.000 -0.7543 0.01719 0.01046 -0.0712 0.8316 0.0152
-9.750 -0.7302 0.01660 0.00980 -0.0710 0.8254 0.0190
-9.500 -0.7053 0.01602 0.00921 -0.0709 0.8190 0.0242
-9.250 -0.6799 0.01554 0.00873 -0.0709 0.8130 0.0308
-9.000 -0.6534 0.01518 0.00835 -0.0710 0.8079 0.0369
-8.750 -0.6262 0.01486 0.00801 -0.0711 0.8023 0.0414
-8.500 -0.5988 0.01460 0.00770 -0.0713 0.7969 0.0454
-8.250 -0.5714 0.01434 0.00737 -0.0714 0.7920 0.0482
-8.000 -0.5436 0.01407 0.00709 -0.0717 0.7868 0.0514
-7.750 -0.5154 0.01388 0.00682 -0.0719 0.7817 0.0543
-7.500 -0.4878 0.01360 0.00651 -0.0721 0.7771 0.0577
-7.250 -0.4595 0.01337 0.00626 -0.0724 0.7725 0.0612
-7.000 -0.4308 0.01320 0.00603 -0.0727 0.7677 0.0641
-6.750 -0.4029 0.01291 0.00572 -0.0730 0.7632 0.0681
-6.500 -0.3745 0.01268 0.00545 -0.0733 0.7590 0.0713
-6.250 -0.3457 0.01247 0.00520 -0.0736 0.7545 0.0739
-6.000 -0.3169 0.01227 0.00494 -0.0740 0.7500 0.0764
-5.750 -0.2883 0.01203 0.00468 -0.0743 0.7456 0.0802
-5.500 -0.2594 0.01183 0.00445 -0.0746 0.7417 0.0843
-5.250 -0.2303 0.01164 0.00424 -0.0750 0.7373 0.0893
-5.000 -0.2013 0.01142 0.00403 -0.0754 0.7328 0.0968
-4.750 -0.1724 0.01123 0.00382 -0.0758 0.7286 0.1057
-4.500 -0.1433 0.01102 0.00363 -0.0762 0.7244 0.1186
-4.250 -0.1142 0.01076 0.00344 -0.0767 0.7196 0.1380
-4.000 -0.0854 0.01047 0.00324 -0.0771 0.7146 0.1678
-3.750 -0.0569 0.01011 0.00303 -0.0776 0.7102 0.2170
-3.500 -0.0279 0.00980 0.00291 -0.0781 0.7053 0.2658
-3.250 0.0014 0.00964 0.00284 -0.0786 0.7003 0.2981
-3.000 0.0309 0.00957 0.00279 -0.0790 0.6957 0.3191
-2.750 0.0606 0.00952 0.00274 -0.0794 0.6911 0.3346
-2.500 0.0904 0.00948 0.00271 -0.0799 0.6859 0.3481
-2.250 0.1201 0.00944 0.00266 -0.0803 0.6808 0.3582
-2.000 0.1498 0.00944 0.00262 -0.0808 0.6761 0.3659
-1.750 0.1796 0.00940 0.00260 -0.0812 0.6705 0.3763
-1.500 0.2091 0.00938 0.00260 -0.0817 0.6650 0.3925
-1.250 0.2387 0.00936 0.00258 -0.0821 0.6597 0.4046
-1.000 0.2684 0.00934 0.00256 -0.0825 0.6536 0.4107
-0.750 0.2979 0.00935 0.00252 -0.0829 0.6474 0.4148
-0.500 0.3275 0.00933 0.00250 -0.0834 0.6413 0.4188
-0.250 0.3570 0.00931 0.00248 -0.0838 0.6346 0.4238
0.000 0.3864 0.00933 0.00247 -0.0842 0.6287 0.4288
0.250 0.4160 0.00933 0.00247 -0.0846 0.6220 0.4335
0.500 0.4453 0.00933 0.00248 -0.0850 0.6155 0.4396
0.750 0.4747 0.00934 0.00249 -0.0854 0.6089 0.4459
1.000 0.5040 0.00935 0.00252 -0.0858 0.6018 0.4531
1.250 0.5332 0.00936 0.00255 -0.0862 0.5949 0.4621
1.500 0.5623 0.00937 0.00258 -0.0866 0.5866 0.4724
1.750 0.5913 0.00938 0.00263 -0.0870 0.5786 0.4862
2.000 0.6202 0.00938 0.00269 -0.0874 0.5696 0.5074
2.250 0.6490 0.00936 0.00276 -0.0877 0.5612 0.5387
2.500 0.6775 0.00931 0.00285 -0.0881 0.5524 0.5843
2.750 0.7059 0.00923 0.00295 -0.0884 0.5437 0.6436
3.000 0.7333 0.00915 0.00307 -0.0885 0.5348 0.7131
3.250 0.7586 0.00901 0.00324 -0.0879 0.5259 0.8023
3.500 0.7817 0.00904 0.00339 -0.0867 0.5171 0.8698
3.750 0.8064 0.00910 0.00351 -0.0860 0.5078 0.8993
4.000 0.8307 0.00921 0.00363 -0.0852 0.4985 0.9220
4.250 0.8550 0.00932 0.00375 -0.0844 0.4883 0.9423
4.500 0.8816 0.00945 0.00386 -0.0842 0.4766 0.9632
4.750 0.9104 0.00961 0.00400 -0.0846 0.4641 0.9840
5.000 0.9401 0.00978 0.00413 -0.0853 0.4518 1.0000
5.250 0.9666 0.01001 0.00431 -0.0852 0.4396 1.0000
5.500 0.9932 0.01023 0.00450 -0.0852 0.4277 1.0000
5.750 1.0193 0.01048 0.00472 -0.0851 0.4152 1.0000
6.000 1.0448 0.01075 0.00495 -0.0850 0.4017 1.0000
6.250 1.0700 0.01104 0.00519 -0.0847 0.3885 1.0000
6.500 1.0948 0.01135 0.00546 -0.0844 0.3750 1.0000
6.750 1.1194 0.01165 0.00573 -0.0841 0.3610 1.0000
7.000 1.1431 0.01200 0.00604 -0.0837 0.3460 1.0000
7.250 1.1658 0.01239 0.00637 -0.0830 0.3297 1.0000
7.500 1.1878 0.01281 0.00673 -0.0823 0.3134 1.0000
7.750 1.2092 0.01323 0.00711 -0.0814 0.2974 1.0000
8.000 1.2296 0.01369 0.00752 -0.0804 0.2811 1.0000
8.250 1.2484 0.01420 0.00797 -0.0792 0.2631 1.0000
8.500 1.2643 0.01483 0.00850 -0.0774 0.2410 1.0000
8.750 1.2760 0.01554 0.00910 -0.0750 0.2186 1.0000
9.000 1.2863 0.01630 0.00978 -0.0723 0.1975 1.0000
9.250 1.2963 0.01716 0.01054 -0.0698 0.1781 1.0000
9.500 1.3064 0.01810 0.01139 -0.0675 0.1595 1.0000
9.750 1.3163 0.01910 0.01232 -0.0654 0.1416 1.0000
10.000 1.3262 0.02017 0.01332 -0.0634 0.1256 1.0000
10.250 1.3356 0.02133 0.01442 -0.0615 0.1107 1.0000
10.500 1.3450 0.02253 0.01558 -0.0598 0.0978 1.0000
10.750 1.3543 0.02380 0.01682 -0.0582 0.0861 1.0000
11.000 1.3638 0.02511 0.01810 -0.0567 0.0763 1.0000
11.250 1.3729 0.02648 0.01945 -0.0553 0.0676 1.0000
11.500 1.3814 0.02793 0.02089 -0.0539 0.0601 1.0000
11.750 1.3896 0.02944 0.02241 -0.0526 0.0533 1.0000
12.000 1.3981 0.03096 0.02393 -0.0514 0.0475 1.0000
12.250 1.4052 0.03262 0.02560 -0.0502 0.0422 1.0000
12.500 1.4116 0.03437 0.02737 -0.0490 0.0374 1.0000
12.750 1.4186 0.03610 0.02913 -0.0480 0.0333 1.0000
13.000 1.4241 0.03798 0.03105 -0.0469 0.0300 1.0000
13.250 1.4292 0.03994 0.03305 -0.0459 0.0268 1.0000
13.500 1.4342 0.04196 0.03511 -0.0450 0.0242 1.0000
13.750 1.4378 0.04416 0.03735 -0.0442 0.0218 1.0000
14.000 1.4424 0.04633 0.03958 -0.0435 0.0197 1.0000
14.250 1.4447 0.04878 0.04208 -0.0428 0.0179 1.0000
14.500 1.4483 0.05118 0.04454 -0.0422 0.0162 1.0000
14.750 1.4498 0.05385 0.04727 -0.0418 0.0147 1.0000
15.000 1.4521 0.05647 0.04997 -0.0414 0.0134 1.0000
15.250 1.4529 0.05932 0.05289 -0.0411 0.0124 1.0000
15.500 1.4534 0.06228 0.05592 -0.0409 0.0116 1.0000
15.750 1.4540 0.06529 0.05901 -0.0408 0.0108 1.0000
16.000 1.4533 0.06849 0.06229 -0.0409 0.0103 1.0000
16.250 1.4513 0.07190 0.06578 -0.0410 0.0098 1.0000
16.500 1.4491 0.07542 0.06939 -0.0412 0.0094 1.0000
16.750 1.4473 0.07894 0.07301 -0.0415 0.0091 1.0000
17.000 1.4448 0.08261 0.07677 -0.0420 0.0089 1.0000
17.250 1.4415 0.08641 0.08068 -0.0426 0.0086 1.0000
17.500 1.4373 0.09038 0.08475 -0.0432 0.0084 1.0000
17.750 1.4325 0.09451 0.08897 -0.0440 0.0082 1.0000
18.000 1.4269 0.09882 0.09338 -0.0450 0.0081 1.0000
18.250 1.4207 0.10327 0.09792 -0.0461 0.0079 1.0000
18.500 1.4135 0.10788 0.10264 -0.0474 0.0078 1.0000
18.750 1.4053 0.11275 0.10760 -0.0489 0.0076 1.0000
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