SG6051 (sg6051-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6051 (sg6051-il) Reynolds number: 200,000 Max Cl/Cd: 82.21 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6051-il-200000.txt Download as CSV file: xf-sg6051-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SG6051
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4048 0.09125 0.08804 -0.0457 1.0000 0.0480
-8.750 -0.4307 0.09049 0.08738 -0.0412 1.0000 0.0479
-8.500 -0.4447 0.08789 0.08484 -0.0409 0.9983 0.0484
-8.250 -0.4399 0.08149 0.07845 -0.0495 0.9922 0.0501
-8.000 -0.4313 0.07065 0.06749 -0.0667 0.9844 0.0518
-7.750 -0.4510 0.05084 0.04699 -0.0787 0.9745 0.0321
-7.500 -0.4345 0.04362 0.03928 -0.0829 0.9712 0.0314
-7.250 -0.4211 0.03792 0.03302 -0.0840 0.9644 0.0312
-7.000 -0.3970 0.03199 0.02635 -0.0859 0.9611 0.0311
-6.750 -0.3667 0.02761 0.02117 -0.0874 0.9587 0.0326
-6.500 -0.3415 0.02477 0.01791 -0.0877 0.9538 0.0355
-6.250 -0.3104 0.02404 0.01699 -0.0887 0.9493 0.0413
-6.000 -0.2780 0.02271 0.01552 -0.0903 0.9461 0.0486
-5.750 -0.2442 0.02155 0.01413 -0.0919 0.9436 0.0568
-5.500 -0.2189 0.02116 0.01366 -0.0917 0.9371 0.0632
-5.250 -0.1885 0.01999 0.01225 -0.0923 0.9328 0.0678
-5.000 -0.1572 0.01901 0.01126 -0.0931 0.9296 0.0730
-4.750 -0.1308 0.01844 0.01057 -0.0929 0.9238 0.0774
-4.500 -0.1034 0.01759 0.00966 -0.0928 0.9187 0.0817
-4.250 -0.0745 0.01694 0.00903 -0.0931 0.9149 0.0885
-4.000 -0.0484 0.01651 0.00853 -0.0928 0.9092 0.0945
-3.750 -0.0222 0.01594 0.00801 -0.0926 0.9038 0.1048
-3.500 0.0057 0.01540 0.00750 -0.0926 0.8999 0.1215
-3.250 0.0310 0.01471 0.00708 -0.0926 0.8943 0.1703
-3.000 0.0543 0.01355 0.00696 -0.0925 0.8888 0.4279
-2.750 0.0807 0.01322 0.00684 -0.0921 0.8849 0.5045
-2.500 0.1061 0.01304 0.00685 -0.0917 0.8793 0.5636
-2.250 0.1311 0.01280 0.00684 -0.0910 0.8738 0.6318
-2.000 0.1550 0.01249 0.00680 -0.0897 0.8699 0.7152
-1.750 0.1745 0.01233 0.00696 -0.0872 0.8640 0.8164
-1.500 0.2000 0.01227 0.00703 -0.0856 0.8588 0.9209
-1.250 0.2647 0.01225 0.00694 -0.0929 0.8567 0.9956
-1.000 0.2970 0.01223 0.00677 -0.0940 0.8526 1.0000
-0.750 0.3199 0.01234 0.00679 -0.0935 0.8454 1.0000
-0.500 0.3442 0.01232 0.00666 -0.0927 0.8406 1.0000
-0.250 0.3687 0.01243 0.00668 -0.0923 0.8347 1.0000
0.000 0.3938 0.01250 0.00668 -0.0919 0.8286 1.0000
0.250 0.4201 0.01249 0.00658 -0.0914 0.8245 1.0000
0.500 0.4457 0.01266 0.00672 -0.0913 0.8177 1.0000
0.750 0.4723 0.01270 0.00670 -0.0910 0.8123 1.0000
1.000 0.4997 0.01270 0.00662 -0.0907 0.8086 1.0000
1.250 0.5256 0.01290 0.00683 -0.0907 0.8008 1.0000
1.500 0.5531 0.01289 0.00677 -0.0905 0.7959 1.0000
1.750 0.5799 0.01300 0.00687 -0.0904 0.7896 1.0000
2.000 0.6070 0.01303 0.00689 -0.0902 0.7831 1.0000
2.250 0.6351 0.01299 0.00681 -0.0900 0.7783 1.0000
2.500 0.6615 0.01311 0.00697 -0.0899 0.7699 1.0000
2.750 0.6899 0.01302 0.00684 -0.0897 0.7648 1.0000
3.000 0.7163 0.01312 0.00699 -0.0896 0.7557 1.0000
3.250 0.7449 0.01299 0.00683 -0.0893 0.7499 1.0000
3.500 0.7713 0.01306 0.00695 -0.0891 0.7401 1.0000
3.750 0.7992 0.01300 0.00689 -0.0889 0.7325 1.0000
4.000 0.8265 0.01295 0.00687 -0.0886 0.7229 1.0000
4.250 0.8534 0.01295 0.00691 -0.0883 0.7125 1.0000
4.500 0.8811 0.01288 0.00686 -0.0881 0.7027 1.0000
4.750 0.9086 0.01279 0.00679 -0.0877 0.6913 1.0000
5.000 0.9350 0.01277 0.00682 -0.0873 0.6779 1.0000
5.250 0.9614 0.01274 0.00684 -0.0868 0.6633 1.0000
5.500 0.9878 0.01271 0.00682 -0.0863 0.6469 1.0000
5.750 1.0129 0.01276 0.00693 -0.0857 0.6269 1.0000
6.000 1.0381 0.01282 0.00700 -0.0850 0.6049 1.0000
6.250 1.0620 0.01295 0.00713 -0.0842 0.5765 1.0000
6.500 1.0844 0.01319 0.00730 -0.0830 0.5403 1.0000
6.750 1.1051 0.01359 0.00757 -0.0817 0.4963 1.0000
7.000 1.1227 0.01422 0.00797 -0.0799 0.4424 1.0000
7.250 1.1366 0.01511 0.00858 -0.0777 0.3806 1.0000
7.500 1.1466 0.01626 0.00938 -0.0750 0.3142 1.0000
7.750 1.1538 0.01757 0.01033 -0.0719 0.2511 1.0000
8.000 1.1593 0.01896 0.01138 -0.0687 0.1933 1.0000
8.250 1.1634 0.02041 0.01253 -0.0653 0.1451 1.0000
8.500 1.1643 0.02185 0.01376 -0.0613 0.1138 1.0000
8.750 1.1671 0.02334 0.01513 -0.0578 0.0940 1.0000
9.000 1.1722 0.02480 0.01654 -0.0549 0.0810 1.0000
9.250 1.1759 0.02645 0.01812 -0.0520 0.0719 1.0000
9.500 1.1879 0.02756 0.01934 -0.0502 0.0643 1.0000
9.750 1.1933 0.02925 0.02101 -0.0478 0.0586 1.0000
10.000 1.2048 0.03048 0.02233 -0.0461 0.0532 1.0000
10.250 1.2094 0.03246 0.02425 -0.0437 0.0487 1.0000
10.500 1.2218 0.03370 0.02568 -0.0422 0.0448 1.0000
10.750 1.2314 0.03526 0.02726 -0.0406 0.0414 1.0000
11.000 1.2418 0.03729 0.02931 -0.0386 0.0381 1.0000
11.250 1.2535 0.03874 0.03092 -0.0371 0.0353 1.0000
11.500 1.2639 0.04030 0.03253 -0.0358 0.0328 1.0000
11.750 1.2829 0.04273 0.03495 -0.0345 0.0304 1.0000
12.000 1.2945 0.04452 0.03699 -0.0330 0.0293 1.0000
12.250 1.3064 0.04664 0.03936 -0.0315 0.0281 1.0000
12.500 1.3157 0.04884 0.04177 -0.0300 0.0270 1.0000
12.750 1.3218 0.05099 0.04408 -0.0286 0.0260 1.0000
13.000 1.3272 0.05316 0.04633 -0.0273 0.0249 1.0000
13.250 1.3356 0.05653 0.04982 -0.0261 0.0239 1.0000
13.500 1.3310 0.06100 0.05461 -0.0243 0.0235 1.0000
13.750 1.3214 0.06444 0.05834 -0.0226 0.0234 1.0000
14.000 1.3094 0.06830 0.06249 -0.0213 0.0232 1.0000
14.250 1.2953 0.07261 0.06709 -0.0203 0.0232 1.0000
14.500 1.2789 0.07734 0.07209 -0.0198 0.0231 1.0000
14.750 1.2606 0.08250 0.07750 -0.0199 0.0231 1.0000
15.000 1.2409 0.08810 0.08334 -0.0206 0.0232 1.0000
15.250 1.2202 0.09419 0.08966 -0.0220 0.0232 1.0000
15.500 1.1989 0.10087 0.09655 -0.0242 0.0233 1.0000
15.750 1.1773 0.10812 0.10399 -0.0271 0.0234 1.0000
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Polar data table (+)
Polar graphs
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