SG6042 (sg6042-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6042 (sg6042-il) Reynolds number: 100,000 Max Cl/Cd: 62.91 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6042-il-100000.txt Download as CSV file: xf-sg6042-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3849 0.10623 0.10162 -0.0324 1.0000 0.0818
-8.000 -0.4079 0.10564 0.10114 -0.0312 1.0000 0.0822
-7.750 -0.4303 0.10485 0.10046 -0.0295 1.0000 0.0824
-7.500 -0.4484 0.10308 0.09876 -0.0309 1.0000 0.0826
-7.250 -0.4637 0.10038 0.09608 -0.0349 1.0000 0.0828
-7.000 -0.4315 0.09527 0.09102 -0.0221 1.0000 0.0860
-6.750 -0.4358 0.09313 0.08893 -0.0201 1.0000 0.0880
-6.500 -0.4428 0.09083 0.08669 -0.0193 1.0000 0.0907
-6.250 -0.4500 0.08821 0.08412 -0.0203 1.0000 0.0929
-6.000 -0.4589 0.08419 0.08002 -0.0307 1.0000 0.0967
-5.750 -0.4593 0.07955 0.07541 -0.0311 1.0000 0.0987
-5.500 -0.4551 0.07762 0.07357 -0.0259 1.0000 0.1015
-5.250 -0.4500 0.07491 0.07086 -0.0259 1.0000 0.1063
-5.000 -0.4384 0.06931 0.06502 -0.0349 1.0000 0.1139
-4.750 -0.4322 0.06702 0.06283 -0.0316 1.0000 0.1170
-4.500 -0.4118 0.06259 0.05805 -0.0387 1.0000 0.1290
-4.250 -0.4030 0.05988 0.05548 -0.0362 1.0000 0.1321
-4.000 -0.3819 0.05625 0.05162 -0.0400 1.0000 0.1456
-3.750 -0.3672 0.05386 0.04926 -0.0391 0.9999 0.1524
-3.500 -0.3247 0.05004 0.04516 -0.0462 0.9947 0.1775
-3.250 -0.2912 0.04749 0.04252 -0.0495 0.9889 0.2087
-3.000 -0.2034 0.03452 0.02728 -0.0603 0.9879 0.0783
-2.750 -0.1562 0.03106 0.02292 -0.0635 0.9846 0.0717
-2.500 -0.1206 0.02951 0.02109 -0.0652 0.9786 0.0742
-2.250 -0.0789 0.02838 0.01961 -0.0677 0.9739 0.0788
-2.000 -0.0440 0.02737 0.01824 -0.0687 0.9677 0.0824
-1.750 -0.0063 0.02632 0.01724 -0.0707 0.9625 0.0940
-1.500 0.0295 0.02543 0.01639 -0.0721 0.9569 0.1138
-1.250 0.0636 0.02464 0.01589 -0.0737 0.9505 0.1619
-1.000 0.0998 0.02245 0.01590 -0.0757 0.9473 0.6084
-0.750 0.1189 0.02168 0.01580 -0.0721 0.9383 1.0000
-0.500 0.1643 0.02218 0.01590 -0.0757 0.9326 1.0000
-0.250 0.1926 0.02243 0.01591 -0.0763 0.9226 1.0000
0.000 0.2320 0.02282 0.01606 -0.0787 0.9156 1.0000
0.250 0.2657 0.02311 0.01617 -0.0802 0.9065 1.0000
0.500 0.2991 0.02343 0.01634 -0.0816 0.8979 1.0000
0.750 0.3392 0.02367 0.01643 -0.0840 0.8903 1.0000
1.000 0.3686 0.02395 0.01661 -0.0845 0.8801 1.0000
1.250 0.4150 0.02403 0.01659 -0.0878 0.8739 1.0000
1.500 0.4422 0.02424 0.01674 -0.0878 0.8623 1.0000
1.750 0.4784 0.02433 0.01677 -0.0892 0.8532 1.0000
2.000 0.5200 0.02422 0.01663 -0.0914 0.8450 1.0000
2.250 0.5503 0.02430 0.01669 -0.0917 0.8337 1.0000
2.500 0.6014 0.02380 0.01618 -0.0950 0.8283 1.0000
2.750 0.6307 0.02374 0.01613 -0.0949 0.8160 1.0000
3.000 0.6900 0.02268 0.01512 -0.0992 0.8122 1.0000
3.250 0.7208 0.02239 0.01487 -0.0990 0.7994 1.0000
3.500 0.7564 0.02192 0.01445 -0.0995 0.7875 1.0000
3.750 0.8129 0.02061 0.01320 -0.1029 0.7814 1.0000
4.000 0.8480 0.01998 0.01265 -0.1030 0.7679 1.0000
4.250 0.8832 0.01932 0.01205 -0.1031 0.7535 1.0000
4.500 0.9201 0.01859 0.01137 -0.1034 0.7378 1.0000
4.750 0.9509 0.01808 0.01093 -0.1028 0.7186 1.0000
5.000 0.9804 0.01763 0.01051 -0.1020 0.6961 1.0000
5.250 1.0097 0.01728 0.01017 -0.1012 0.6707 1.0000
5.500 1.0369 0.01709 0.00997 -0.1001 0.6411 1.0000
5.750 1.0613 0.01707 0.00989 -0.0986 0.6065 1.0000
6.000 1.0839 0.01723 0.00991 -0.0969 0.5669 1.0000
6.250 1.1028 0.01759 0.01010 -0.0947 0.5229 1.0000
6.500 1.1184 0.01816 0.01044 -0.0921 0.4755 1.0000
6.750 1.1317 0.01890 0.01092 -0.0893 0.4271 1.0000
7.000 1.1437 0.01980 0.01153 -0.0864 0.3811 1.0000
7.250 1.1550 0.02082 0.01227 -0.0836 0.3395 1.0000
7.500 1.1668 0.02190 0.01312 -0.0810 0.3023 1.0000
7.750 1.1795 0.02303 0.01404 -0.0786 0.2710 1.0000
8.000 1.1934 0.02419 0.01502 -0.0765 0.2445 1.0000
8.250 1.2087 0.02538 0.01604 -0.0746 0.2226 1.0000
8.500 1.2253 0.02661 0.01718 -0.0730 0.2032 1.0000
8.750 1.2430 0.02784 0.01838 -0.0717 0.1867 1.0000
9.000 1.2622 0.02915 0.01965 -0.0705 0.1722 1.0000
9.250 1.2825 0.03053 0.02099 -0.0697 0.1594 1.0000
9.500 1.3067 0.03209 0.02245 -0.0695 0.1477 1.0000
9.750 1.3226 0.03331 0.02386 -0.0678 0.1379 1.0000
10.000 1.3432 0.03495 0.02560 -0.0671 0.1288 1.0000
10.250 1.3693 0.03679 0.02731 -0.0674 0.1200 1.0000
10.500 1.3800 0.03817 0.02905 -0.0649 0.1132 1.0000
10.750 1.4046 0.04027 0.03109 -0.0651 0.1060 1.0000
11.000 1.4130 0.04188 0.03306 -0.0624 0.1005 1.0000
11.250 1.4416 0.04454 0.03557 -0.0634 0.0940 1.0000
11.500 1.4403 0.04628 0.03781 -0.0594 0.0907 1.0000
11.750 1.4457 0.04818 0.03999 -0.0566 0.0866 1.0000
12.000 1.4688 0.05094 0.04270 -0.0570 0.0821 1.0000
12.250 1.4628 0.05374 0.04591 -0.0531 0.0803 1.0000
12.500 1.4508 0.05631 0.04889 -0.0487 0.0787 1.0000
12.750 1.4388 0.05913 0.05207 -0.0449 0.0770 1.0000
13.000 1.4282 0.06208 0.05531 -0.0418 0.0753 1.0000
13.250 1.4213 0.06505 0.05849 -0.0395 0.0737 1.0000
13.500 1.4160 0.06824 0.06186 -0.0377 0.0723 1.0000
13.750 1.4062 0.07196 0.06577 -0.0361 0.0714 1.0000
14.000 1.3910 0.07631 0.07034 -0.0348 0.0708 1.0000
14.250 1.3673 0.08133 0.07563 -0.0340 0.0707 1.0000
14.500 1.2720 0.09377 0.08875 -0.0371 0.0744 1.0000
14.750 1.2071 0.10735 0.10259 -0.0441 0.0778 1.0000
15.000 1.1624 0.12035 0.11571 -0.0519 0.0799 1.0000
15.250 1.1297 0.13299 0.12838 -0.0592 0.0811 1.0000
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Polar data table (+)
Polar graphs
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