SG6051 (sg6051-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6051 (sg6051-il) Reynolds number: 500,000 Max Cl/Cd: 102.29 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6051-il-500000-n5.txt Download as CSV file: xf-sg6051-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7780 0.04677 0.04406 -0.0701 1.0000 0.0050
-11.750 -0.7974 0.04020 0.03719 -0.0759 0.9757 0.0049
-11.500 -0.8033 0.03599 0.03264 -0.0768 0.9543 0.0050
-11.250 -0.8035 0.03273 0.02904 -0.0760 0.9394 0.0050
-11.000 -0.7976 0.03011 0.02611 -0.0750 0.9283 0.0050
-10.750 -0.7862 0.02791 0.02363 -0.0743 0.9189 0.0051
-10.500 -0.7713 0.02611 0.02157 -0.0735 0.9114 0.0052
-10.250 -0.7533 0.02456 0.01980 -0.0730 0.9042 0.0053
-10.000 -0.7340 0.02323 0.01826 -0.0725 0.8982 0.0054
-9.750 -0.7124 0.02202 0.01686 -0.0722 0.8919 0.0056
-9.500 -0.6903 0.02094 0.01559 -0.0719 0.8862 0.0057
-9.250 -0.6671 0.01995 0.01441 -0.0717 0.8811 0.0059
-9.000 -0.6430 0.01903 0.01332 -0.0716 0.8758 0.0061
-8.750 -0.6185 0.01821 0.01233 -0.0714 0.8709 0.0063
-8.500 -0.5932 0.01745 0.01142 -0.0713 0.8664 0.0065
-8.250 -0.5673 0.01675 0.01058 -0.0713 0.8616 0.0068
-8.000 -0.5412 0.01610 0.00979 -0.0713 0.8572 0.0070
-7.750 -0.5152 0.01544 0.00900 -0.0713 0.8532 0.0075
-7.500 -0.4882 0.01487 0.00835 -0.0715 0.8486 0.0080
-7.250 -0.4611 0.01437 0.00775 -0.0716 0.8441 0.0087
-7.000 -0.4339 0.01391 0.00719 -0.0717 0.8402 0.0096
-6.750 -0.4065 0.01343 0.00666 -0.0719 0.8364 0.0117
-6.500 -0.3787 0.01302 0.00623 -0.0721 0.8319 0.0154
-6.250 -0.3507 0.01272 0.00591 -0.0723 0.8276 0.0197
-6.000 -0.3227 0.01248 0.00563 -0.0726 0.8239 0.0229
-5.750 -0.2941 0.01227 0.00536 -0.0729 0.8197 0.0257
-5.500 -0.2656 0.01202 0.00508 -0.0732 0.8151 0.0282
-5.250 -0.2372 0.01184 0.00487 -0.0735 0.8110 0.0314
-5.000 -0.2086 0.01168 0.00466 -0.0738 0.8071 0.0345
-4.750 -0.1799 0.01145 0.00443 -0.0742 0.8025 0.0383
-4.500 -0.1511 0.01127 0.00421 -0.0745 0.7982 0.0412
-4.250 -0.1224 0.01109 0.00395 -0.0748 0.7944 0.0429
-4.000 -0.0935 0.01081 0.00365 -0.0751 0.7902 0.0466
-3.750 -0.0646 0.01061 0.00344 -0.0755 0.7856 0.0505
-3.500 -0.0356 0.01047 0.00324 -0.0758 0.7814 0.0541
-3.250 -0.0067 0.01027 0.00303 -0.0762 0.7775 0.0611
-3.000 0.0225 0.01009 0.00287 -0.0766 0.7729 0.0701
-2.750 0.0515 0.00990 0.00272 -0.0770 0.7684 0.0871
-2.500 0.0803 0.00969 0.00257 -0.0774 0.7645 0.1137
-2.250 0.1094 0.00944 0.00244 -0.0779 0.7599 0.1547
-2.000 0.1381 0.00907 0.00231 -0.0785 0.7551 0.2285
-1.750 0.1665 0.00863 0.00223 -0.0790 0.7509 0.3453
-1.500 0.1956 0.00851 0.00220 -0.0794 0.7462 0.3890
-1.250 0.2248 0.00841 0.00216 -0.0798 0.7411 0.4174
-1.000 0.2538 0.00832 0.00211 -0.0802 0.7361 0.4449
-0.750 0.2828 0.00815 0.00209 -0.0807 0.7310 0.4899
-0.500 0.3112 0.00785 0.00209 -0.0810 0.7256 0.5753
-0.250 0.3382 0.00745 0.00212 -0.0810 0.7209 0.7057
0.000 0.3640 0.00717 0.00217 -0.0805 0.7159 0.8025
0.250 0.3893 0.00705 0.00220 -0.0797 0.7105 0.8611
0.500 0.4141 0.00699 0.00219 -0.0788 0.7056 0.9076
0.750 0.4422 0.00693 0.00218 -0.0787 0.6998 0.9458
1.000 0.4753 0.00693 0.00215 -0.0799 0.6937 0.9760
1.250 0.5091 0.00695 0.00215 -0.0813 0.6871 0.9949
1.500 0.5397 0.00698 0.00214 -0.0821 0.6796 1.0000
1.750 0.5681 0.00704 0.00216 -0.0823 0.6724 1.0000
2.000 0.5965 0.00712 0.00220 -0.0826 0.6640 1.0000
2.250 0.6249 0.00719 0.00225 -0.0828 0.6548 1.0000
2.500 0.6532 0.00728 0.00230 -0.0830 0.6452 1.0000
2.750 0.6816 0.00738 0.00236 -0.0833 0.6346 1.0000
3.000 0.7098 0.00748 0.00245 -0.0835 0.6231 1.0000
3.250 0.7379 0.00760 0.00253 -0.0837 0.6103 1.0000
3.500 0.7659 0.00773 0.00263 -0.0839 0.5965 1.0000
3.750 0.7936 0.00788 0.00274 -0.0840 0.5801 1.0000
4.000 0.8209 0.00808 0.00287 -0.0841 0.5598 1.0000
4.250 0.8480 0.00829 0.00301 -0.0842 0.5385 1.0000
4.500 0.8743 0.00857 0.00320 -0.0841 0.5105 1.0000
4.750 0.8993 0.00896 0.00343 -0.0838 0.4721 1.0000
5.000 0.9237 0.00942 0.00371 -0.0835 0.4307 1.0000
5.250 0.9465 0.01002 0.00407 -0.0829 0.3789 1.0000
5.500 0.9670 0.01083 0.00455 -0.0821 0.3135 1.0000
5.750 0.9879 0.01158 0.00502 -0.0813 0.2594 1.0000
6.000 1.0102 0.01216 0.00544 -0.0807 0.2235 1.0000
6.250 1.0320 0.01276 0.00589 -0.0800 0.1890 1.0000
6.500 1.0531 0.01339 0.00636 -0.0792 0.1558 1.0000
6.750 1.0740 0.01401 0.00684 -0.0783 0.1278 1.0000
7.000 1.0950 0.01458 0.00732 -0.0775 0.1063 1.0000
7.250 1.1157 0.01515 0.00782 -0.0766 0.0879 1.0000
7.500 1.1353 0.01576 0.00835 -0.0755 0.0715 1.0000
7.750 1.1546 0.01636 0.00889 -0.0743 0.0577 1.0000
8.000 1.1732 0.01697 0.00945 -0.0731 0.0468 1.0000
8.250 1.1910 0.01758 0.01003 -0.0717 0.0387 1.0000
8.500 1.2093 0.01812 0.01060 -0.0704 0.0342 1.0000
8.750 1.2249 0.01873 0.01122 -0.0686 0.0304 1.0000
9.000 1.2401 0.01930 0.01184 -0.0667 0.0279 1.0000
9.250 1.2543 0.01999 0.01254 -0.0648 0.0251 1.0000
9.500 1.2688 0.02071 0.01330 -0.0630 0.0229 1.0000
9.750 1.2840 0.02141 0.01407 -0.0615 0.0210 1.0000
10.000 1.2979 0.02224 0.01493 -0.0598 0.0191 1.0000
10.250 1.3114 0.02311 0.01586 -0.0582 0.0175 1.0000
10.500 1.3258 0.02395 0.01677 -0.0568 0.0160 1.0000
10.750 1.3387 0.02492 0.01778 -0.0553 0.0145 1.0000
11.000 1.3506 0.02600 0.01891 -0.0537 0.0133 1.0000
11.250 1.3632 0.02703 0.02003 -0.0523 0.0123 1.0000
11.500 1.3750 0.02816 0.02122 -0.0509 0.0113 1.0000
11.750 1.3850 0.02945 0.02255 -0.0494 0.0104 1.0000
12.000 1.3952 0.03074 0.02392 -0.0479 0.0098 1.0000
12.250 1.4050 0.03209 0.02536 -0.0466 0.0093 1.0000
12.500 1.4141 0.03353 0.02689 -0.0452 0.0088 1.0000
12.750 1.4222 0.03506 0.02851 -0.0439 0.0085 1.0000
13.000 1.4292 0.03674 0.03025 -0.0426 0.0081 1.0000
13.250 1.4343 0.03862 0.03224 -0.0412 0.0078 1.0000
13.500 1.4374 0.04073 0.03445 -0.0398 0.0075 1.0000
13.750 1.4424 0.04269 0.03653 -0.0387 0.0074 1.0000
14.000 1.4467 0.04477 0.03872 -0.0377 0.0071 1.0000
14.250 1.4502 0.04698 0.04104 -0.0367 0.0069 1.0000
14.500 1.4531 0.04930 0.04347 -0.0359 0.0067 1.0000
14.750 1.4552 0.05177 0.04606 -0.0352 0.0065 1.0000
15.000 1.4567 0.05442 0.04882 -0.0347 0.0063 1.0000
15.250 1.4574 0.05723 0.05174 -0.0343 0.0061 1.0000
15.500 1.4567 0.06031 0.05493 -0.0340 0.0059 1.0000
15.750 1.4539 0.06372 0.05846 -0.0339 0.0058 1.0000
16.000 1.4496 0.06745 0.06233 -0.0341 0.0057 1.0000
16.250 1.4430 0.07162 0.06662 -0.0344 0.0056 1.0000
16.500 1.4341 0.07625 0.07138 -0.0351 0.0055 1.0000
16.750 1.4252 0.08100 0.07627 -0.0360 0.0054 1.0000
17.000 1.4183 0.08562 0.08104 -0.0370 0.0054 1.0000
17.250 1.4102 0.09056 0.08612 -0.0384 0.0053 1.0000
17.500 1.4011 0.09579 0.09151 -0.0400 0.0053 1.0000
17.750 1.3905 0.10136 0.09723 -0.0420 0.0052 1.0000
18.000 1.3792 0.10723 0.10325 -0.0442 0.0052 1.0000
18.250 1.3673 0.11337 0.10953 -0.0467 0.0051 1.0000
18.500 1.3544 0.11986 0.11617 -0.0496 0.0051 1.0000
18.750 1.3413 0.12652 0.12298 -0.0528 0.0050 1.0000
19.000 1.3275 0.13347 0.13007 -0.0563 0.0050 1.0000
19.250 1.3138 0.14060 0.13734 -0.0601 0.0050 1.0000
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