SG6050 (sg6050-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6050 (sg6050-il) Reynolds number: 100,000 Max Cl/Cd: 52.45 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6050-il-100000-n5.txt Download as CSV file: xf-sg6050-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6019 0.09185 0.08667 -0.0544 1.0000 0.0324
-13.250 -0.6805 0.07319 0.06770 -0.0658 1.0000 0.0302
-13.000 -0.7117 0.06440 0.05868 -0.0716 1.0000 0.0300
-12.750 -0.7298 0.05815 0.05228 -0.0759 1.0000 0.0303
-12.500 -0.7436 0.05306 0.04702 -0.0793 1.0000 0.0308
-12.250 -0.7560 0.04885 0.04263 -0.0814 1.0000 0.0316
-12.000 -0.7692 0.04544 0.03903 -0.0817 1.0000 0.0326
-11.500 -0.8008 0.04156 0.03496 -0.0757 1.0000 0.0342
-11.250 -0.8131 0.04061 0.03401 -0.0715 1.0000 0.0351
-11.000 -0.8159 0.03948 0.03278 -0.0690 0.9974 0.0368
-10.750 -0.7948 0.03739 0.03043 -0.0709 0.9894 0.0407
-10.500 -0.7694 0.03586 0.02865 -0.0731 0.9825 0.0454
-10.250 -0.7445 0.03470 0.02736 -0.0747 0.9742 0.0498
-10.000 -0.7183 0.03341 0.02573 -0.0764 0.9671 0.0557
-9.750 -0.6909 0.03269 0.02492 -0.0780 0.9598 0.0613
-9.500 -0.6646 0.03168 0.02370 -0.0792 0.9528 0.0670
-9.250 -0.6374 0.03084 0.02269 -0.0803 0.9458 0.0726
-9.000 -0.6090 0.02971 0.02135 -0.0815 0.9402 0.0776
-8.750 -0.5832 0.02889 0.02046 -0.0820 0.9325 0.0820
-8.500 -0.5534 0.02795 0.01921 -0.0830 0.9272 0.0870
-8.250 -0.5284 0.02701 0.01826 -0.0832 0.9198 0.0908
-8.000 -0.5008 0.02621 0.01737 -0.0837 0.9136 0.0951
-7.750 -0.4723 0.02545 0.01641 -0.0842 0.9081 0.0997
-7.500 -0.4482 0.02467 0.01560 -0.0840 0.9005 0.1035
-7.250 -0.4208 0.02395 0.01483 -0.0843 0.8950 0.1079
-7.000 -0.3952 0.02338 0.01414 -0.0842 0.8885 0.1131
-6.750 -0.3701 0.02273 0.01346 -0.0841 0.8819 0.1183
-6.500 -0.3428 0.02211 0.01277 -0.0843 0.8770 0.1246
-6.250 -0.3186 0.02161 0.01221 -0.0840 0.8697 0.1317
-6.000 -0.2928 0.02105 0.01162 -0.0840 0.8638 0.1420
-5.750 -0.2661 0.02044 0.01102 -0.0841 0.8589 0.1559
-5.500 -0.2418 0.01993 0.01055 -0.0839 0.8518 0.1759
-5.250 -0.2160 0.01929 0.01010 -0.0840 0.8464 0.2129
-5.000 -0.1897 0.01885 0.00991 -0.0841 0.8413 0.2706
-4.750 -0.1638 0.01877 0.00989 -0.0839 0.8346 0.3158
-4.500 -0.1356 0.01874 0.00977 -0.0840 0.8294 0.3462
-4.250 -0.1075 0.01873 0.00965 -0.0840 0.8244 0.3689
-4.000 -0.0808 0.01874 0.00959 -0.0840 0.8179 0.3870
-3.750 -0.0527 0.01868 0.00945 -0.0840 0.8128 0.4037
-3.500 -0.0246 0.01862 0.00931 -0.0840 0.8079 0.4198
-3.250 0.0018 0.01861 0.00928 -0.0839 0.8013 0.4365
-3.000 0.0293 0.01852 0.00920 -0.0838 0.7962 0.4559
-2.750 0.0569 0.01844 0.00911 -0.0837 0.7913 0.4745
-2.500 0.0834 0.01840 0.00908 -0.0836 0.7845 0.4881
-2.250 0.1119 0.01829 0.00889 -0.0837 0.7793 0.4982
-2.000 0.1399 0.01818 0.00877 -0.0837 0.7741 0.5068
-1.750 0.1669 0.01815 0.00872 -0.0837 0.7673 0.5167
-1.500 0.1952 0.01802 0.00858 -0.0837 0.7622 0.5262
-1.250 0.2229 0.01797 0.00853 -0.0837 0.7565 0.5374
-1.000 0.2498 0.01793 0.00852 -0.0836 0.7500 0.5498
-0.750 0.2782 0.01780 0.00842 -0.0836 0.7451 0.5641
-0.500 0.3046 0.01778 0.00847 -0.0834 0.7387 0.5813
-0.250 0.3314 0.01772 0.00848 -0.0832 0.7323 0.6030
0.000 0.3593 0.01755 0.00840 -0.0829 0.7277 0.6315
0.250 0.3834 0.01754 0.00857 -0.0822 0.7203 0.6704
0.500 0.4078 0.01739 0.00862 -0.0811 0.7144 0.7240
0.750 0.4313 0.01724 0.00868 -0.0793 0.7093 0.7937
1.000 0.4553 0.01732 0.00890 -0.0781 0.7014 0.8700
1.250 0.4881 0.01727 0.00884 -0.0787 0.6959 0.9232
1.500 0.5259 0.01735 0.00893 -0.0808 0.6884 0.9625
1.750 0.5673 0.01737 0.00890 -0.0837 0.6816 0.9939
2.000 0.5958 0.01740 0.00888 -0.0840 0.6750 1.0000
2.250 0.6193 0.01755 0.00899 -0.0834 0.6672 1.0000
2.500 0.6465 0.01755 0.00890 -0.0833 0.6615 1.0000
2.750 0.6692 0.01778 0.00915 -0.0826 0.6527 1.0000
3.000 0.6969 0.01779 0.00909 -0.0826 0.6466 1.0000
3.250 0.7202 0.01803 0.00936 -0.0820 0.6376 1.0000
3.500 0.7479 0.01806 0.00933 -0.0819 0.6310 1.0000
3.750 0.7716 0.01829 0.00959 -0.0814 0.6218 1.0000
4.000 0.7995 0.01832 0.00959 -0.0813 0.6148 1.0000
4.250 0.8231 0.01858 0.00989 -0.0808 0.6051 1.0000
4.500 0.8513 0.01862 0.00989 -0.0808 0.5980 1.0000
4.750 0.8742 0.01891 0.01025 -0.0801 0.5878 1.0000
5.000 0.9008 0.01904 0.01037 -0.0799 0.5795 1.0000
5.250 0.9252 0.01927 0.01065 -0.0794 0.5698 1.0000
5.500 0.9500 0.01949 0.01090 -0.0790 0.5604 1.0000
5.750 0.9761 0.01965 0.01106 -0.0787 0.5513 1.0000
6.000 0.9991 0.01995 0.01143 -0.0780 0.5405 1.0000
6.250 1.0239 0.02017 0.01166 -0.0776 0.5304 1.0000
6.500 1.0483 0.02039 0.01190 -0.0770 0.5196 1.0000
6.750 1.0701 0.02073 0.01231 -0.0761 0.5074 1.0000
7.000 1.0928 0.02104 0.01265 -0.0754 0.4957 1.0000
7.250 1.1158 0.02133 0.01295 -0.0746 0.4842 1.0000
7.500 1.1371 0.02168 0.01335 -0.0736 0.4718 1.0000
7.750 1.1567 0.02210 0.01383 -0.0724 0.4586 1.0000
8.000 1.1759 0.02253 0.01430 -0.0711 0.4453 1.0000
8.250 1.1944 0.02298 0.01479 -0.0698 0.4319 1.0000
8.500 1.2119 0.02347 0.01531 -0.0682 0.4184 1.0000
8.750 1.2279 0.02400 0.01587 -0.0665 0.4046 1.0000
9.000 1.2421 0.02459 0.01648 -0.0645 0.3904 1.0000
9.250 1.2526 0.02525 0.01717 -0.0620 0.3760 1.0000
9.500 1.2610 0.02601 0.01798 -0.0593 0.3612 1.0000
9.750 1.2691 0.02687 0.01887 -0.0567 0.3462 1.0000
10.000 1.2767 0.02784 0.01987 -0.0543 0.3308 1.0000
10.250 1.2834 0.02893 0.02099 -0.0519 0.3152 1.0000
10.500 1.2892 0.03016 0.02224 -0.0497 0.2993 1.0000
10.750 1.2941 0.03152 0.02363 -0.0475 0.2832 1.0000
11.000 1.2978 0.03305 0.02515 -0.0455 0.2669 1.0000
11.250 1.3005 0.03474 0.02685 -0.0435 0.2505 1.0000
11.500 1.3024 0.03659 0.02871 -0.0417 0.2338 1.0000
11.750 1.3033 0.03860 0.03072 -0.0401 0.2172 1.0000
12.000 1.3031 0.04078 0.03291 -0.0385 0.2012 1.0000
12.250 1.3021 0.04313 0.03525 -0.0371 0.1862 1.0000
12.500 1.3005 0.04562 0.03775 -0.0358 0.1723 1.0000
12.750 1.2981 0.04826 0.04039 -0.0346 0.1597 1.0000
13.250 1.2928 0.05388 0.04607 -0.0328 0.1367 1.0000
13.500 1.2902 0.05684 0.04908 -0.0322 0.1265 1.0000
13.750 1.2864 0.06006 0.05233 -0.0317 0.1174 1.0000
14.000 1.2816 0.06349 0.05578 -0.0314 0.1087 1.0000
14.250 1.2784 0.06686 0.05923 -0.0312 0.1002 1.0000
14.500 1.2726 0.07063 0.06301 -0.0312 0.0930 1.0000
14.750 1.2677 0.07441 0.06689 -0.0314 0.0855 1.0000
15.000 1.2625 0.07833 0.07086 -0.0318 0.0790 1.0000
15.250 1.2557 0.08254 0.07512 -0.0324 0.0732 1.0000
15.500 1.2509 0.08659 0.07926 -0.0330 0.0676 1.0000
15.750 1.2438 0.09105 0.08377 -0.0339 0.0630 1.0000
16.000 1.2385 0.09531 0.08812 -0.0349 0.0587 1.0000
16.250 1.2326 0.09974 0.09264 -0.0360 0.0548 1.0000
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Polar data table (+)
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