SG6042 (sg6042-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6042 (sg6042-il) Reynolds number: 50,000 Max Cl/Cd: 39.47 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6042-il-50000-n5.txt Download as CSV file: xf-sg6042-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SG6042
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3689 0.10477 0.09815 -0.0324 1.0000 0.1078
-7.750 -0.4011 0.10497 0.09855 -0.0317 1.0000 0.1116
-7.500 -0.4202 0.10358 0.09730 -0.0308 1.0000 0.1119
-7.250 -0.4055 0.09546 0.08908 -0.0301 1.0000 0.0650
-7.000 -0.4282 0.09079 0.08449 -0.0348 1.0000 0.0561
-6.750 -0.4283 0.08814 0.08190 -0.0327 1.0000 0.0550
-6.500 -0.4317 0.08488 0.07868 -0.0327 1.0000 0.0543
-6.250 -0.4335 0.08156 0.07539 -0.0331 1.0000 0.0534
-6.000 -0.4341 0.07777 0.07160 -0.0345 1.0000 0.0530
-5.750 -0.4321 0.07369 0.06748 -0.0362 1.0000 0.0526
-5.500 -0.4267 0.06953 0.06323 -0.0381 1.0000 0.0522
-5.250 -0.4179 0.06516 0.05873 -0.0403 1.0000 0.0517
-5.000 -0.3927 0.05958 0.05286 -0.0459 0.9961 0.0508
-4.750 -0.3622 0.05388 0.04671 -0.0517 0.9916 0.0496
-4.500 -0.3294 0.04868 0.04094 -0.0566 0.9874 0.0489
-4.250 -0.2954 0.04455 0.03626 -0.0604 0.9838 0.0491
-4.000 -0.2633 0.04151 0.03272 -0.0630 0.9794 0.0516
-3.750 -0.2278 0.03855 0.02909 -0.0657 0.9757 0.0543
-3.500 -0.1910 0.03594 0.02578 -0.0679 0.9725 0.0559
-3.250 -0.1603 0.03393 0.02340 -0.0689 0.9679 0.0579
-3.000 -0.1281 0.03269 0.02199 -0.0702 0.9634 0.0630
-2.750 -0.0919 0.03141 0.02021 -0.0715 0.9598 0.0690
-2.500 -0.0648 0.03030 0.01912 -0.0716 0.9542 0.0750
-2.250 -0.0329 0.02945 0.01809 -0.0724 0.9494 0.0862
-2.000 0.0000 0.02875 0.01732 -0.0735 0.9448 0.1047
-1.750 0.0295 0.02806 0.01663 -0.0741 0.9387 0.1331
-1.500 0.0655 0.02725 0.01599 -0.0761 0.9341 0.1840
-1.250 0.0973 0.02576 0.01566 -0.0779 0.9293 0.3897
-1.000 0.1089 0.02478 0.01597 -0.0731 0.9226 0.7610
-0.750 0.1439 0.02443 0.01559 -0.0736 0.9158 1.0000
-0.500 0.1741 0.02470 0.01549 -0.0745 0.9079 1.0000
-0.250 0.2110 0.02502 0.01545 -0.0765 0.9021 1.0000
0.000 0.2382 0.02529 0.01548 -0.0768 0.8932 1.0000
0.250 0.2752 0.02559 0.01552 -0.0788 0.8872 1.0000
0.500 0.3015 0.02588 0.01563 -0.0789 0.8777 1.0000
0.750 0.3355 0.02615 0.01571 -0.0803 0.8705 1.0000
1.000 0.3652 0.02642 0.01585 -0.0809 0.8614 1.0000
1.250 0.3948 0.02670 0.01601 -0.0814 0.8524 1.0000
1.500 0.4297 0.02689 0.01610 -0.0827 0.8446 1.0000
1.750 0.4557 0.02719 0.01632 -0.0826 0.8340 1.0000
2.000 0.4955 0.02724 0.01631 -0.0846 0.8275 1.0000
2.250 0.5197 0.02752 0.01656 -0.0841 0.8155 1.0000
2.500 0.5475 0.02772 0.01674 -0.0841 0.8044 1.0000
2.750 0.5881 0.02755 0.01658 -0.0858 0.7972 1.0000
3.000 0.6131 0.02772 0.01676 -0.0852 0.7842 1.0000
3.250 0.6401 0.02782 0.01689 -0.0848 0.7717 1.0000
3.500 0.6696 0.02781 0.01691 -0.0847 0.7596 1.0000
3.750 0.7037 0.02759 0.01677 -0.0851 0.7484 1.0000
4.250 0.7689 0.02705 0.01638 -0.0852 0.7223 1.0000
4.500 0.7995 0.02678 0.01622 -0.0848 0.7071 1.0000
4.750 0.8275 0.02656 0.01609 -0.0840 0.6900 1.0000
5.000 0.8519 0.02645 0.01607 -0.0827 0.6702 1.0000
5.250 0.8819 0.02612 0.01585 -0.0820 0.6500 1.0000
5.500 0.9112 0.02583 0.01564 -0.0812 0.6275 1.0000
5.750 0.9404 0.02558 0.01544 -0.0804 0.6018 1.0000
6.000 0.9666 0.02551 0.01541 -0.0792 0.5722 1.0000
6.250 0.9929 0.02550 0.01537 -0.0781 0.5393 1.0000
6.500 1.0138 0.02579 0.01560 -0.0763 0.5032 1.0000
6.750 1.0340 0.02620 0.01589 -0.0745 0.4658 1.0000
7.000 1.0507 0.02681 0.01640 -0.0724 0.4285 1.0000
7.250 1.0651 0.02759 0.01703 -0.0701 0.3923 1.0000
7.500 1.0783 0.02851 0.01780 -0.0678 0.3586 1.0000
7.750 1.0904 0.02955 0.01870 -0.0655 0.3272 1.0000
8.000 1.1021 0.03068 0.01975 -0.0633 0.2986 1.0000
8.250 1.1142 0.03187 0.02087 -0.0613 0.2728 1.0000
8.500 1.1258 0.03314 0.02202 -0.0593 0.2506 1.0000
8.750 1.1391 0.03442 0.02330 -0.0576 0.2299 1.0000
9.000 1.1522 0.03575 0.02464 -0.0560 0.2117 1.0000
9.250 1.1662 0.03712 0.02600 -0.0545 0.1958 1.0000
9.500 1.1808 0.03850 0.02742 -0.0532 0.1814 1.0000
9.750 1.1960 0.03994 0.02891 -0.0519 0.1685 1.0000
10.000 1.2120 0.04142 0.03046 -0.0508 0.1573 1.0000
10.250 1.2269 0.04293 0.03198 -0.0496 0.1473 1.0000
10.500 1.2419 0.04455 0.03380 -0.0484 0.1376 1.0000
10.750 1.2579 0.04628 0.03568 -0.0473 0.1294 1.0000
11.000 1.2707 0.04796 0.03741 -0.0461 0.1219 1.0000
11.250 1.2833 0.05000 0.03972 -0.0449 0.1151 1.0000
11.500 1.2953 0.05188 0.04172 -0.0437 0.1091 1.0000
11.750 1.3040 0.05417 0.04424 -0.0423 0.1037 1.0000
12.000 1.3089 0.05654 0.04687 -0.0408 0.0986 1.0000
12.250 1.3233 0.05846 0.04872 -0.0400 0.0941 1.0000
12.500 1.3174 0.06177 0.05252 -0.0382 0.0907 1.0000
12.750 1.3134 0.06497 0.05603 -0.0368 0.0874 1.0000
13.000 1.3132 0.06782 0.05906 -0.0357 0.0843 1.0000
13.250 1.3214 0.07033 0.06157 -0.0350 0.0814 1.0000
13.500 1.3031 0.07508 0.06676 -0.0342 0.0800 1.0000
13.750 1.2829 0.08036 0.07241 -0.0343 0.0787 1.0000
14.000 1.2599 0.08634 0.07871 -0.0352 0.0778 1.0000
14.250 1.2328 0.09338 0.08604 -0.0373 0.0774 1.0000
14.500 1.1991 0.10224 0.09514 -0.0413 0.0776 1.0000
14.750 1.1571 0.11395 0.10705 -0.0480 0.0786 1.0000
15.000 1.1089 0.12944 0.12264 -0.0577 0.0797 1.0000
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Polar data table (+)
Polar graphs
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