SG6040 (sg6040-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6040 (sg6040-il) Reynolds number: 100,000 Max Cl/Cd: 50.51 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6040-il-100000.txt Download as CSV file: xf-sg6040-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SG6040
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4430 0.10040 0.09530 -0.0615 1.0000 0.0846
-11.250 -0.4337 0.09813 0.09303 -0.0598 1.0000 0.0828
-11.000 -0.6278 0.07013 0.06472 -0.0747 1.0000 0.0627
-10.750 -0.6465 0.06736 0.06197 -0.0723 1.0000 0.0623
-10.500 -0.6686 0.06531 0.05994 -0.0687 1.0000 0.0619
-10.250 -0.7004 0.06397 0.05860 -0.0636 1.0000 0.0617
-10.000 -0.7269 0.06207 0.05665 -0.0591 1.0000 0.0614
-9.750 -0.7479 0.05983 0.05431 -0.0552 1.0000 0.0609
-9.500 -0.7669 0.05727 0.05161 -0.0515 1.0000 0.0605
-9.250 -0.7823 0.05448 0.04861 -0.0482 1.0000 0.0601
-9.000 -0.7934 0.05151 0.04539 -0.0452 1.0000 0.0598
-8.750 -0.7995 0.04858 0.04214 -0.0425 1.0000 0.0596
-8.500 -0.8010 0.04588 0.03909 -0.0402 1.0000 0.0602
-8.250 -0.7982 0.04329 0.03610 -0.0381 1.0000 0.0610
-8.000 -0.7915 0.04094 0.03330 -0.0363 1.0000 0.0619
-7.750 -0.7713 0.03843 0.03028 -0.0365 0.9974 0.0629
-7.500 -0.7375 0.03602 0.02779 -0.0388 0.9925 0.0648
-7.250 -0.7041 0.03439 0.02601 -0.0408 0.9867 0.0676
-7.000 -0.6681 0.03283 0.02413 -0.0428 0.9814 0.0716
-6.750 -0.6371 0.03149 0.02285 -0.0442 0.9750 0.0779
-6.500 -0.6010 0.03024 0.02156 -0.0464 0.9699 0.0878
-6.250 -0.5734 0.02899 0.02037 -0.0470 0.9626 0.1023
-6.000 -0.5371 0.02786 0.01933 -0.0495 0.9575 0.1298
-5.750 -0.5127 0.02711 0.01858 -0.0498 0.9492 0.1562
-5.500 -0.4751 0.02648 0.01806 -0.0527 0.9437 0.1880
-5.250 -0.4521 0.02579 0.01758 -0.0527 0.9356 0.2129
-5.000 -0.4165 0.02504 0.01704 -0.0548 0.9298 0.2481
-4.750 -0.3921 0.02421 0.01656 -0.0550 0.9222 0.2930
-4.500 -0.3654 0.02298 0.01624 -0.0556 0.9156 0.4101
-4.250 -0.3384 0.02342 0.01721 -0.0546 0.9086 0.5424
-4.000 -0.3119 0.02412 0.01783 -0.0536 0.9002 0.5910
-3.750 -0.2715 0.02491 0.01850 -0.0546 0.8955 0.6251
-3.500 -0.2579 0.02547 0.01903 -0.0514 0.8849 0.6439
-3.250 -0.2209 0.02606 0.01955 -0.0517 0.8799 0.6644
-3.000 -0.2060 0.02653 0.01996 -0.0490 0.8699 0.6803
-2.750 -0.1720 0.02689 0.02025 -0.0489 0.8643 0.6978
-2.500 -0.1536 0.02727 0.02056 -0.0468 0.8554 0.7131
-2.250 -0.1247 0.02753 0.02074 -0.0461 0.8488 0.7293
-2.000 -0.0861 0.02771 0.02086 -0.0464 0.8451 0.7463
-1.750 -0.0828 0.02815 0.02132 -0.0415 0.8333 0.7577
-1.500 -0.0477 0.02820 0.02131 -0.0412 0.8292 0.7738
-1.250 -0.0411 0.02849 0.02157 -0.0374 0.8181 0.7862
-1.000 -0.0060 0.02831 0.02130 -0.0380 0.8134 0.7996
-0.750 0.0069 0.02850 0.02146 -0.0353 0.8039 0.8100
-0.500 0.0377 0.02828 0.02118 -0.0354 0.7978 0.8193
-0.250 0.0829 0.02784 0.02065 -0.0380 0.7949 0.8283
0.000 0.0856 0.02814 0.02094 -0.0343 0.7826 0.8361
0.250 0.1291 0.02767 0.02040 -0.0366 0.7792 0.8433
0.500 0.1731 0.02724 0.01989 -0.0392 0.7756 0.8497
0.750 0.1773 0.02751 0.02017 -0.0357 0.7637 0.8571
1.000 0.2286 0.02694 0.01952 -0.0396 0.7612 0.8635
1.250 0.2274 0.02737 0.01997 -0.0353 0.7485 0.8707
1.500 0.2758 0.02680 0.01936 -0.0384 0.7454 0.8768
1.750 0.3272 0.02614 0.01865 -0.0420 0.7431 0.8820
2.000 0.3250 0.02670 0.01925 -0.0377 0.7299 0.8904
2.250 0.3758 0.02601 0.01852 -0.0412 0.7273 0.8964
2.500 0.3779 0.02659 0.01915 -0.0377 0.7147 0.9048
2.750 0.4277 0.02591 0.01844 -0.0409 0.7116 0.9112
3.250 0.4828 0.02583 0.01842 -0.0412 0.6961 0.9274
3.500 0.5405 0.02508 0.01766 -0.0456 0.6932 0.9324
3.750 0.5503 0.02576 0.01843 -0.0438 0.6810 0.9445
4.000 0.6116 0.02502 0.01768 -0.0490 0.6774 0.9490
4.250 0.6367 0.02557 0.01834 -0.0497 0.6663 0.9601
4.500 0.6987 0.02490 0.01768 -0.0553 0.6615 0.9650
4.750 0.7371 0.02525 0.01813 -0.0581 0.6514 0.9745
5.000 0.7967 0.02466 0.01756 -0.0635 0.6449 0.9795
5.250 0.8408 0.02483 0.01784 -0.0673 0.6341 0.9885
5.500 0.9036 0.02399 0.01697 -0.0729 0.6266 0.9937
5.750 0.9009 0.02448 0.01756 -0.0690 0.6150 1.0000
6.000 0.9286 0.02400 0.01704 -0.0689 0.6071 1.0000
6.250 0.9409 0.02412 0.01718 -0.0669 0.5958 1.0000
6.500 0.9644 0.02422 0.01732 -0.0666 0.5842 1.0000
6.750 1.0060 0.02371 0.01677 -0.0686 0.5735 1.0000
7.000 1.0355 0.02358 0.01664 -0.0688 0.5607 1.0000
7.250 1.0582 0.02368 0.01678 -0.0681 0.5469 1.0000
7.500 1.0839 0.02367 0.01679 -0.0677 0.5332 1.0000
7.750 1.1107 0.02361 0.01673 -0.0674 0.5192 1.0000
8.000 1.1363 0.02354 0.01666 -0.0668 0.5044 1.0000
8.250 1.1589 0.02353 0.01664 -0.0657 0.4884 1.0000
8.500 1.1775 0.02358 0.01670 -0.0640 0.4713 1.0000
8.750 1.1931 0.02370 0.01684 -0.0618 0.4533 1.0000
9.000 1.2061 0.02388 0.01703 -0.0592 0.4341 1.0000
9.250 1.2169 0.02410 0.01723 -0.0563 0.4142 1.0000
9.500 1.2244 0.02439 0.01744 -0.0529 0.3936 1.0000
9.750 1.2233 0.02500 0.01808 -0.0485 0.3713 1.0000
10.000 1.2240 0.02569 0.01868 -0.0445 0.3471 1.0000
10.250 1.2207 0.02670 0.01964 -0.0404 0.3204 1.0000
10.500 1.2166 0.02796 0.02075 -0.0366 0.2929 1.0000
10.750 1.2111 0.02953 0.02211 -0.0331 0.2657 1.0000
11.000 1.2055 0.03137 0.02381 -0.0299 0.2393 1.0000
11.250 1.2012 0.03338 0.02560 -0.0272 0.2164 1.0000
11.500 1.1991 0.03544 0.02752 -0.0249 0.1962 1.0000
11.750 1.1996 0.03750 0.02943 -0.0230 0.1789 1.0000
12.000 1.2030 0.03949 0.03131 -0.0214 0.1640 1.0000
12.250 1.2092 0.04142 0.03315 -0.0201 0.1510 1.0000
12.500 1.2182 0.04327 0.03492 -0.0189 0.1398 1.0000
12.750 1.2325 0.04492 0.03641 -0.0181 0.1297 1.0000
13.000 1.2403 0.04683 0.03844 -0.0171 0.1220 1.0000
13.250 1.2576 0.04851 0.04006 -0.0165 0.1145 1.0000
13.500 1.2683 0.05038 0.04204 -0.0157 0.1085 1.0000
13.750 1.2923 0.05202 0.04358 -0.0155 0.1023 1.0000
14.000 1.2967 0.05431 0.04611 -0.0145 0.0983 1.0000
14.250 1.3133 0.05608 0.04788 -0.0141 0.0939 1.0000
14.500 1.3340 0.05835 0.05020 -0.0139 0.0899 1.0000
14.750 1.3319 0.06116 0.05331 -0.0129 0.0876 1.0000
15.000 1.3333 0.06394 0.05629 -0.0122 0.0851 1.0000
15.250 1.3392 0.06657 0.05905 -0.0117 0.0828 1.0000
15.500 1.3678 0.06918 0.06157 -0.0120 0.0796 1.0000
15.750 1.3509 0.07305 0.06577 -0.0112 0.0789 1.0000
16.000 1.3318 0.07741 0.07048 -0.0109 0.0783 1.0000
16.250 1.3110 0.08229 0.07567 -0.0112 0.0777 1.0000
16.500 1.2875 0.08778 0.08146 -0.0121 0.0773 1.0000
16.750 1.2606 0.09409 0.08807 -0.0138 0.0771 1.0000
17.000 1.2292 0.10147 0.09573 -0.0166 0.0772 1.0000
17.250 1.1932 0.11019 0.10472 -0.0206 0.0776 1.0000
17.500 1.1523 0.12062 0.11539 -0.0262 0.0783 1.0000
17.750 1.1076 0.13306 0.12803 -0.0334 0.0792 1.0000
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