SG6051 (sg6051-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6051 (sg6051-il) Reynolds number: 50,000 Max Cl/Cd: 34.3 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6051-il-50000-n5.txt Download as CSV file: xf-sg6051-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4050 0.10352 0.09659 -0.0462 1.0000 0.0506
-9.500 -0.4084 0.09936 0.09252 -0.0479 1.0000 0.0506
-9.250 -0.4142 0.09526 0.08852 -0.0494 1.0000 0.0507
-9.000 -0.4235 0.09139 0.08476 -0.0504 1.0000 0.0506
-8.750 -0.4381 0.08801 0.08152 -0.0503 1.0000 0.0503
-8.500 -0.4583 0.08514 0.07878 -0.0492 1.0000 0.0498
-8.250 -0.4783 0.08182 0.07556 -0.0486 1.0000 0.0492
-8.000 -0.4969 0.07827 0.07205 -0.0479 1.0000 0.0487
-7.750 -0.5136 0.07459 0.06836 -0.0471 1.0000 0.0484
-7.500 -0.5270 0.07069 0.06439 -0.0465 1.0000 0.0483
-7.250 -0.5364 0.06662 0.06017 -0.0461 1.0000 0.0487
-7.000 -0.5413 0.06237 0.05569 -0.0459 1.0000 0.0493
-6.750 -0.5277 0.05623 0.04900 -0.0495 0.9952 0.0507
-6.500 -0.5077 0.05029 0.04227 -0.0527 0.9897 0.0526
-6.250 -0.4826 0.04675 0.03838 -0.0551 0.9851 0.0566
-6.000 -0.4565 0.04364 0.03482 -0.0568 0.9802 0.0607
-5.750 -0.4272 0.04012 0.03035 -0.0585 0.9755 0.0666
-5.500 -0.3963 0.03791 0.02797 -0.0603 0.9719 0.0718
-5.250 -0.3673 0.03590 0.02534 -0.0611 0.9668 0.0785
-5.000 -0.3365 0.03410 0.02333 -0.0624 0.9624 0.0841
-4.750 -0.3021 0.03270 0.02155 -0.0639 0.9588 0.0919
-4.500 -0.2729 0.03143 0.02012 -0.0645 0.9540 0.0978
-4.250 -0.2420 0.03053 0.01895 -0.0653 0.9491 0.1073
-4.000 -0.2086 0.02953 0.01791 -0.0667 0.9453 0.1156
-3.750 -0.1768 0.02878 0.01706 -0.0679 0.9409 0.1293
-3.500 -0.1481 0.02808 0.01627 -0.0685 0.9353 0.1456
-3.250 -0.1141 0.02725 0.01550 -0.0703 0.9312 0.1771
-3.000 -0.0790 0.02592 0.01495 -0.0727 0.9282 0.2900
-2.750 -0.0579 0.02531 0.01494 -0.0718 0.9215 0.4720
-2.500 -0.0315 0.02481 0.01495 -0.0711 0.9169 0.6023
-2.250 -0.0050 0.02441 0.01506 -0.0693 0.9135 0.7513
-2.000 0.0497 0.02436 0.01513 -0.0732 0.9091 1.0000
-1.750 0.0783 0.02451 0.01492 -0.0743 0.9028 1.0000
-1.500 0.1155 0.02465 0.01470 -0.0768 0.8986 1.0000
-1.250 0.1343 0.02497 0.01476 -0.0759 0.8901 1.0000
-1.000 0.1684 0.02517 0.01470 -0.0776 0.8854 1.0000
-0.750 0.1915 0.02550 0.01483 -0.0774 0.8780 1.0000
-0.500 0.2211 0.02578 0.01490 -0.0783 0.8721 1.0000
-0.250 0.2526 0.02604 0.01498 -0.0794 0.8669 1.0000
0.000 0.2741 0.02645 0.01526 -0.0788 0.8589 1.0000
0.250 0.3086 0.02667 0.01533 -0.0804 0.8544 1.0000
0.500 0.3276 0.02716 0.01572 -0.0793 0.8457 1.0000
0.750 0.3599 0.02741 0.01587 -0.0805 0.8405 1.0000
1.000 0.3814 0.02788 0.01628 -0.0798 0.8324 1.0000
1.250 0.4113 0.02818 0.01651 -0.0805 0.8264 1.0000
1.500 0.4351 0.02862 0.01692 -0.0802 0.8189 1.0000
1.750 0.4625 0.02898 0.01724 -0.0805 0.8120 1.0000
2.000 0.4881 0.02939 0.01765 -0.0805 0.8050 1.0000
2.250 0.5134 0.02979 0.01805 -0.0804 0.7974 1.0000
2.500 0.5392 0.03020 0.01847 -0.0803 0.7902 1.0000
2.750 0.5647 0.03059 0.01890 -0.0802 0.7823 1.0000
3.000 0.5878 0.03106 0.01941 -0.0797 0.7739 1.0000
3.250 0.6167 0.03130 0.01971 -0.0799 0.7668 1.0000
3.500 0.6371 0.03185 0.02031 -0.0790 0.7569 1.0000
3.750 0.6704 0.03186 0.02044 -0.0797 0.7508 1.0000
4.000 0.6889 0.03245 0.02111 -0.0785 0.7396 1.0000
4.250 0.7152 0.03270 0.02146 -0.0782 0.7309 1.0000
4.500 0.7439 0.03277 0.02168 -0.0780 0.7223 1.0000
4.750 0.7642 0.03321 0.02224 -0.0769 0.7106 1.0000
5.000 0.7898 0.03334 0.02251 -0.0762 0.7003 1.0000
5.250 0.8235 0.03297 0.02234 -0.0764 0.6917 1.0000
5.500 0.8448 0.03319 0.02271 -0.0751 0.6787 1.0000
5.750 0.8680 0.03324 0.02294 -0.0739 0.6655 1.0000
6.000 0.8928 0.03312 0.02300 -0.0727 0.6518 1.0000
6.250 0.9187 0.03284 0.02295 -0.0715 0.6374 1.0000
6.500 0.9454 0.03242 0.02273 -0.0702 0.6216 1.0000
6.750 0.9739 0.03176 0.02227 -0.0690 0.6043 1.0000
7.000 0.9917 0.03171 0.02244 -0.0666 0.5820 1.0000
7.250 1.0166 0.03111 0.02201 -0.0647 0.5576 1.0000
7.500 1.0344 0.03096 0.02200 -0.0622 0.5272 1.0000
7.750 1.0503 0.03094 0.02205 -0.0594 0.4900 1.0000
8.000 1.0646 0.03104 0.02212 -0.0563 0.4458 1.0000
8.250 1.0749 0.03158 0.02246 -0.0530 0.3948 1.0000
8.500 1.0796 0.03271 0.02331 -0.0496 0.3419 1.0000
8.750 1.0802 0.03436 0.02465 -0.0462 0.2929 1.0000
9.000 1.0792 0.03635 0.02637 -0.0432 0.2496 1.0000
9.250 1.0780 0.03855 0.02834 -0.0406 0.2116 1.0000
9.500 1.0776 0.04086 0.03045 -0.0383 0.1810 1.0000
9.750 1.0789 0.04317 0.03267 -0.0362 0.1559 1.0000
10.000 1.0805 0.04554 0.03488 -0.0343 0.1372 1.0000
10.250 1.0852 0.04776 0.03709 -0.0327 0.1210 1.0000
10.500 1.0910 0.04994 0.03925 -0.0311 0.1086 1.0000
10.750 1.0994 0.05199 0.04132 -0.0295 0.0984 1.0000
11.000 1.1105 0.05392 0.04339 -0.0281 0.0886 1.0000
11.250 1.1245 0.05575 0.04529 -0.0267 0.0811 1.0000
11.500 1.1390 0.05761 0.04731 -0.0255 0.0742 1.0000
11.750 1.1544 0.05966 0.04954 -0.0243 0.0680 1.0000
12.000 1.1677 0.06188 0.05194 -0.0232 0.0630 1.0000
12.250 1.1801 0.06428 0.05441 -0.0222 0.0588 1.0000
12.500 1.1858 0.06739 0.05794 -0.0210 0.0553 1.0000
12.750 1.1896 0.07051 0.06132 -0.0200 0.0526 1.0000
13.000 1.1922 0.07345 0.06436 -0.0193 0.0502 1.0000
13.250 1.1914 0.07712 0.06821 -0.0186 0.0483 1.0000
13.500 1.1797 0.08178 0.07329 -0.0182 0.0472 1.0000
13.750 1.1659 0.08684 0.07870 -0.0184 0.0465 1.0000
14.000 1.1496 0.09240 0.08458 -0.0191 0.0460 1.0000
14.250 1.1304 0.09855 0.09101 -0.0207 0.0458 1.0000
14.500 1.1087 0.10546 0.09818 -0.0233 0.0458 1.0000
14.750 1.0849 0.11337 0.10633 -0.0271 0.0460 1.0000
15.000 1.0594 0.12253 0.11567 -0.0323 0.0464 1.0000
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Polar data table (+)
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