SG6050 (sg6050-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6050 (sg6050-il) Reynolds number: 50,000 Max Cl/Cd: 8.21 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6050-il-50000.txt Download as CSV file: xf-sg6050-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3396 0.11697 0.10995 -0.0303 1.0000 0.3487
-9.750 -0.3110 0.11152 0.10444 -0.0302 1.0000 0.3565
-9.500 -0.3338 0.11095 0.10401 -0.0291 1.0000 0.3647
-9.250 -0.3223 0.10687 0.09995 -0.0285 1.0000 0.3689
-9.000 -0.3213 0.10435 0.09748 -0.0270 1.0000 0.3732
-8.750 -0.5981 0.08225 0.07630 -0.0405 1.0000 0.1920
-8.500 -0.6194 0.07800 0.07205 -0.0390 1.0000 0.1898
-8.250 -0.6414 0.07331 0.06734 -0.0378 1.0000 0.1881
-8.000 -0.6656 0.06761 0.06151 -0.0375 1.0000 0.1861
-7.750 -0.6852 0.06145 0.05506 -0.0376 1.0000 0.1853
-7.500 -0.6940 0.05586 0.04901 -0.0378 1.0000 0.1867
-7.250 -0.6944 0.05071 0.04320 -0.0382 1.0000 0.1898
-7.000 -0.6816 0.04836 0.04073 -0.0373 1.0000 0.1954
-6.750 -0.6674 0.04597 0.03805 -0.0369 1.0000 0.2012
-6.500 -0.6519 0.04281 0.03422 -0.0373 1.0000 0.2076
-6.250 -0.6333 0.04158 0.03304 -0.0365 1.0000 0.2143
-6.000 -0.6133 0.03941 0.03026 -0.0368 1.0000 0.2223
-5.750 -0.5939 0.03848 0.02944 -0.0360 1.0000 0.2307
-5.500 -0.5723 0.03697 0.02759 -0.0361 1.0000 0.2399
-5.250 -0.5514 0.03612 0.02666 -0.0357 1.0000 0.2515
-5.000 -0.5307 0.03548 0.02603 -0.0352 1.0000 0.2651
-4.750 -0.5094 0.03487 0.02540 -0.0348 1.0000 0.2813
-4.500 -0.4881 0.03448 0.02502 -0.0343 1.0000 0.3030
-4.250 -0.4675 0.03439 0.02501 -0.0336 1.0000 0.3334
-4.000 -0.4481 0.03443 0.02524 -0.0325 1.0000 0.3725
-3.750 -0.4285 0.03431 0.02525 -0.0313 1.0000 0.4301
-3.500 -0.4108 0.03429 0.02539 -0.0296 1.0000 0.4812
-3.250 -0.3943 0.03440 0.02561 -0.0277 1.0000 0.5211
-3.000 -0.3773 0.03456 0.02580 -0.0260 1.0000 0.5555
-2.750 -0.3599 0.03476 0.02600 -0.0246 1.0000 0.5874
-2.500 -0.3435 0.03499 0.02628 -0.0229 1.0000 0.6165
-2.250 -0.3151 0.03550 0.02679 -0.0232 0.9953 0.6505
-2.000 -0.2812 0.03611 0.02741 -0.0245 0.9868 0.6877
-1.750 -0.2508 0.03668 0.02799 -0.0250 0.9789 0.7217
-1.500 -0.2177 0.03731 0.02861 -0.0261 0.9709 0.7525
-1.250 -0.1942 0.03759 0.02890 -0.0261 0.9628 0.7778
-1.000 -0.1625 0.03818 0.02945 -0.0274 0.9547 0.8069
-0.750 -0.1407 0.03853 0.02984 -0.0269 0.9466 0.8382
-0.500 -0.1129 0.03903 0.03038 -0.0273 0.9382 0.8827
-0.250 -0.0555 0.03987 0.03120 -0.0344 0.9278 0.9590
0.000 -0.0125 0.04005 0.03110 -0.0431 0.9170 1.0000
0.250 0.0332 0.04109 0.03172 -0.0497 0.9071 1.0000
0.500 0.0626 0.04202 0.03238 -0.0522 0.8973 1.0000
0.750 0.0913 0.04310 0.03324 -0.0542 0.8878 1.0000
1.000 0.1312 0.04432 0.03425 -0.0577 0.8776 1.0000
1.250 0.1459 0.04529 0.03509 -0.0573 0.8680 1.0000
1.500 0.1830 0.04655 0.03620 -0.0601 0.8577 1.0000
1.750 0.2018 0.04762 0.03717 -0.0602 0.8478 1.0000
2.000 0.2265 0.04885 0.03831 -0.0611 0.8378 1.0000
2.250 0.2648 0.05011 0.03946 -0.0639 0.8272 1.0000
2.500 0.2722 0.05133 0.04063 -0.0624 0.8176 1.0000
2.750 0.3046 0.05262 0.04185 -0.0642 0.8069 1.0000
3.000 0.3241 0.05390 0.04310 -0.0644 0.7967 1.0000
3.250 0.3416 0.05529 0.04445 -0.0643 0.7864 1.0000
3.500 0.3795 0.05655 0.04566 -0.0665 0.7752 1.0000
3.750 0.3856 0.05804 0.04716 -0.0651 0.7653 1.0000
4.000 0.4072 0.05946 0.04856 -0.0655 0.7542 1.0000
4.250 0.4499 0.06063 0.04972 -0.0680 0.7431 1.0000
4.500 0.4459 0.06242 0.05153 -0.0657 0.7330 1.0000
4.750 0.4681 0.06391 0.05304 -0.0660 0.7220 1.0000
5.000 0.5042 0.06513 0.05428 -0.0677 0.7112 1.0000
5.250 0.5015 0.06716 0.05633 -0.0658 0.7009 1.0000
5.500 0.5246 0.06870 0.05792 -0.0662 0.6901 1.0000
5.750 0.5562 0.06997 0.05922 -0.0672 0.6790 1.0000
6.000 0.5525 0.07228 0.06158 -0.0656 0.6690 1.0000
6.250 0.5749 0.07388 0.06323 -0.0659 0.6579 1.0000
6.500 0.6146 0.07482 0.06424 -0.0672 0.6461 1.0000
6.750 0.6003 0.07776 0.06722 -0.0652 0.6366 1.0000
7.000 0.6190 0.07946 0.06899 -0.0651 0.6248 1.0000
7.250 0.6525 0.08058 0.07020 -0.0658 0.6127 1.0000
7.500 0.6524 0.08310 0.07278 -0.0648 0.6018 1.0000
7.750 0.6601 0.08540 0.07515 -0.0642 0.5906 1.0000
8.000 0.6826 0.08696 0.07680 -0.0642 0.5782 1.0000
8.250 0.7162 0.08782 0.07777 -0.0645 0.5653 1.0000
8.500 0.7065 0.09119 0.08121 -0.0635 0.5546 1.0000
8.750 0.7148 0.09354 0.08364 -0.0630 0.5424 1.0000
9.000 0.7334 0.09534 0.08554 -0.0627 0.5299 1.0000
9.250 0.7587 0.09651 0.08684 -0.0624 0.5162 1.0000
9.500 0.7827 0.09774 0.08819 -0.0621 0.5031 1.0000
9.750 0.7674 0.10197 0.09248 -0.0615 0.4915 1.0000
10.000 0.7751 0.10455 0.09515 -0.0610 0.4789 1.0000
10.250 0.7905 0.10647 0.09719 -0.0606 0.4655 1.0000
10.500 0.8099 0.10796 0.09880 -0.0599 0.4515 1.0000
10.750 0.8348 0.10885 0.09983 -0.0591 0.4375 1.0000
11.000 0.8609 0.10932 0.10046 -0.0580 0.4230 1.0000
11.250 0.8234 0.11684 0.10797 -0.0591 0.4136 1.0000
11.500 0.8324 0.11937 0.11060 -0.0587 0.4004 1.0000
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