SG6051 (sg6051-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6051 (sg6051-il) Reynolds number: 100,000 Max Cl/Cd: 58.14 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6051-il-100000.txt Download as CSV file: xf-sg6051-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3919 0.09871 0.09409 -0.0440 1.0000 0.1046
-8.750 -0.4177 0.09703 0.09258 -0.0439 1.0000 0.1066
-8.500 -0.4484 0.09621 0.09190 -0.0408 1.0000 0.1070
-8.250 -0.4786 0.09529 0.09111 -0.0374 1.0000 0.1071
-8.000 -0.5091 0.09318 0.08907 -0.0376 1.0000 0.1075
-7.750 -0.5411 0.09028 0.08613 -0.0396 1.0000 0.1080
-7.500 -0.5263 0.08667 0.08267 -0.0336 1.0000 0.1102
-7.250 -0.5233 0.08484 0.08088 -0.0295 1.0000 0.1129
-7.000 -0.5309 0.08210 0.07815 -0.0287 1.0000 0.1160
-6.750 -0.5630 0.07685 0.07247 -0.0378 1.0000 0.1230
-6.500 -0.5507 0.07329 0.06921 -0.0331 1.0000 0.1253
-6.250 -0.5414 0.07111 0.06703 -0.0314 0.9992 0.1324
-6.000 -0.5196 0.06629 0.06208 -0.0362 0.9948 0.1470
-5.750 -0.4897 0.04799 0.04229 -0.0488 0.9904 0.0831
-5.500 -0.4571 0.04038 0.03373 -0.0515 0.9872 0.0712
-5.250 -0.4199 0.03679 0.02936 -0.0542 0.9841 0.0770
-5.000 -0.3894 0.03386 0.02598 -0.0557 0.9800 0.0840
-4.750 -0.3536 0.03207 0.02362 -0.0575 0.9759 0.0921
-4.500 -0.3149 0.02990 0.02113 -0.0601 0.9729 0.0986
-4.250 -0.2809 0.02878 0.01967 -0.0615 0.9686 0.1057
-4.000 -0.2475 0.02746 0.01820 -0.0629 0.9642 0.1121
-3.750 -0.2092 0.02663 0.01719 -0.0651 0.9603 0.1208
-3.500 -0.1693 0.02566 0.01627 -0.0678 0.9573 0.1315
-3.250 -0.1430 0.02503 0.01568 -0.0679 0.9513 0.1438
-3.000 -0.1068 0.02433 0.01506 -0.0699 0.9471 0.1652
-2.750 -0.0660 0.02283 0.01437 -0.0732 0.9444 0.2696
-2.500 -0.0406 0.02170 0.01466 -0.0728 0.9400 0.5985
-2.250 -0.0185 0.02147 0.01489 -0.0710 0.9343 0.7306
-2.000 0.0116 0.02138 0.01514 -0.0695 0.9302 0.9103
-1.750 0.0546 0.02161 0.01510 -0.0734 0.9241 1.0000
-1.500 0.0864 0.02188 0.01512 -0.0749 0.9178 1.0000
-1.250 0.1299 0.02211 0.01508 -0.0786 0.9140 1.0000
-1.000 0.1474 0.02255 0.01535 -0.0774 0.9054 1.0000
-0.750 0.1868 0.02278 0.01540 -0.0801 0.9006 1.0000
-0.500 0.2107 0.02322 0.01570 -0.0800 0.8932 1.0000
-0.250 0.2441 0.02351 0.01585 -0.0816 0.8871 1.0000
0.000 0.2895 0.02365 0.01587 -0.0852 0.8837 1.0000
0.250 0.3016 0.02427 0.01641 -0.0830 0.8736 1.0000
0.500 0.3446 0.02440 0.01645 -0.0861 0.8697 1.0000
0.750 0.3593 0.02505 0.01704 -0.0844 0.8602 1.0000
1.000 0.3996 0.02518 0.01712 -0.0869 0.8556 1.0000
1.250 0.4180 0.02580 0.01770 -0.0858 0.8466 1.0000
1.500 0.4558 0.02594 0.01782 -0.0878 0.8413 1.0000
1.750 0.4782 0.02647 0.01834 -0.0873 0.8329 1.0000
2.000 0.5136 0.02662 0.01848 -0.0888 0.8268 1.0000
2.250 0.5585 0.02640 0.01826 -0.0915 0.8235 1.0000
2.500 0.5720 0.02714 0.01902 -0.0896 0.8118 1.0000
2.750 0.5962 0.02757 0.01948 -0.0891 0.8031 1.0000
3.000 0.6315 0.02749 0.01945 -0.0902 0.7967 1.0000
3.250 0.6538 0.02794 0.01993 -0.0894 0.7869 1.0000
3.500 0.6924 0.02757 0.01964 -0.0906 0.7813 1.0000
3.750 0.7145 0.02793 0.02006 -0.0897 0.7706 1.0000
4.000 0.7563 0.02719 0.01940 -0.0909 0.7657 1.0000
4.250 0.7783 0.02744 0.01975 -0.0898 0.7542 1.0000
4.500 0.8229 0.02630 0.01871 -0.0910 0.7500 1.0000
4.750 0.8459 0.02633 0.01884 -0.0898 0.7377 1.0000
5.000 0.8730 0.02605 0.01868 -0.0889 0.7263 1.0000
5.250 0.9168 0.02455 0.01729 -0.0895 0.7205 1.0000
5.500 0.9440 0.02406 0.01693 -0.0883 0.7073 1.0000
5.750 0.9733 0.02335 0.01634 -0.0873 0.6937 1.0000
6.000 1.0039 0.02248 0.01559 -0.0863 0.6792 1.0000
6.250 1.0357 0.02146 0.01466 -0.0853 0.6629 1.0000
6.500 1.0609 0.02087 0.01420 -0.0837 0.6416 1.0000
6.750 1.0893 0.02009 0.01347 -0.0823 0.6181 1.0000
7.000 1.1120 0.01972 0.01316 -0.0804 0.5880 1.0000
7.250 1.1308 0.01962 0.01313 -0.0780 0.5486 1.0000
7.500 1.1477 0.01974 0.01314 -0.0753 0.4982 1.0000
7.750 1.1587 0.02033 0.01346 -0.0720 0.4315 1.0000
8.000 1.1618 0.02155 0.01420 -0.0678 0.3536 1.0000
8.250 1.1579 0.02331 0.01542 -0.0629 0.2778 1.0000
8.500 1.1508 0.02529 0.01691 -0.0578 0.2178 1.0000
8.750 1.1442 0.02735 0.01857 -0.0530 0.1770 1.0000
9.000 1.1434 0.02939 0.02035 -0.0492 0.1472 1.0000
9.250 1.1476 0.03128 0.02206 -0.0463 0.1265 1.0000
9.500 1.1572 0.03314 0.02376 -0.0440 0.1116 1.0000
9.750 1.1713 0.03485 0.02541 -0.0423 0.0991 1.0000
10.000 1.1898 0.03658 0.02718 -0.0411 0.0888 1.0000
10.250 1.2113 0.03849 0.02911 -0.0403 0.0796 1.0000
10.500 1.2402 0.04079 0.03132 -0.0407 0.0710 1.0000
10.750 1.2570 0.04271 0.03355 -0.0392 0.0654 1.0000
11.000 1.2889 0.04585 0.03667 -0.0404 0.0591 1.0000
11.250 1.2993 0.04826 0.03951 -0.0381 0.0562 1.0000
11.500 1.3131 0.05126 0.04284 -0.0365 0.0538 1.0000
11.750 1.3239 0.05408 0.04587 -0.0349 0.0517 1.0000
12.000 1.3431 0.05969 0.05158 -0.0355 0.0490 1.0000
12.250 1.3284 0.06187 0.05417 -0.0309 0.0485 1.0000
12.500 1.3139 0.06477 0.05744 -0.0271 0.0480 1.0000
12.750 1.2990 0.06826 0.06128 -0.0240 0.0478 1.0000
13.000 1.2829 0.07224 0.06557 -0.0215 0.0477 1.0000
13.250 1.2650 0.07655 0.07018 -0.0195 0.0478 1.0000
13.500 1.2452 0.08121 0.07511 -0.0181 0.0479 1.0000
13.750 1.2244 0.08626 0.08041 -0.0175 0.0481 1.0000
14.000 1.2028 0.09174 0.08610 -0.0175 0.0483 1.0000
14.250 1.1817 0.09768 0.09223 -0.0182 0.0486 1.0000
14.500 1.1636 0.10425 0.09895 -0.0194 0.0490 1.0000
14.750 1.1365 0.10990 0.10484 -0.0221 0.0495 1.0000
15.000 1.0205 0.13699 0.13242 -0.0420 0.0579 1.0000
15.250 1.0063 0.14643 0.14186 -0.0469 0.0592 1.0000
15.500 1.0020 0.15358 0.14900 -0.0496 0.0599 1.0000
15.750 0.6926 0.16983 0.16533 -0.0441 0.1370 1.0000
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Polar data table (+)
Polar graphs
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