GOE 207 (AVIATIK V8) AIRFOIL (goe207-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 207 (AVIATIK V8) AIRFOIL (goe207-il) Reynolds number: 200,000 Max Cl/Cd: 70.43 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe207-il-200000.txt Download as CSV file: xf-goe207-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 207 (AVIATIK V8) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2312 0.09830 0.09526 -0.0148 1.0000 0.0302
-7.500 -0.2241 0.09577 0.09279 -0.0162 1.0000 0.0308
-7.250 -0.2187 0.09346 0.09056 -0.0176 1.0000 0.0313
-7.000 -0.1941 0.09017 0.08728 -0.0252 0.9687 0.0320
-6.750 -0.1555 0.08753 0.08452 -0.0404 0.9264 0.0324
-6.500 -0.1381 0.08378 0.08069 -0.0431 0.8943 0.0326
-6.250 -0.1315 0.08003 0.07687 -0.0401 0.8656 0.0328
-6.000 -0.1210 0.07704 0.07378 -0.0396 0.8388 0.0331
-5.750 -0.1071 0.07428 0.07091 -0.0406 0.8125 0.0337
-5.250 -0.0700 0.06891 0.06526 -0.0455 0.7657 0.0354
-5.000 -0.0471 0.06618 0.06238 -0.0489 0.7444 0.0363
-4.750 -0.0139 0.06384 0.05982 -0.0549 0.7244 0.0375
-4.500 0.0328 0.06198 0.05761 -0.0642 0.7060 0.0381
-4.250 0.0434 0.05807 0.05367 -0.0629 0.6893 0.0384
-4.000 0.0611 0.05510 0.05062 -0.0633 0.6730 0.0389
-3.750 0.0846 0.05256 0.04796 -0.0650 0.6574 0.0397
-3.500 0.1120 0.05020 0.04544 -0.0674 0.6425 0.0409
-3.250 0.1441 0.04807 0.04312 -0.0704 0.6284 0.0431
-3.000 0.1959 0.04722 0.04181 -0.0762 0.6148 0.0447
-2.750 0.2135 0.04373 0.03828 -0.0766 0.6030 0.0452
-2.500 0.2372 0.04132 0.03579 -0.0776 0.5902 0.0461
-2.250 0.2655 0.03938 0.03373 -0.0791 0.5781 0.0476
-2.000 0.2969 0.03771 0.03184 -0.0808 0.5670 0.0498
-1.750 0.3431 0.03765 0.03126 -0.0832 0.5557 0.0526
-1.500 0.3654 0.03445 0.02811 -0.0843 0.5448 0.0535
-1.250 0.3920 0.03268 0.02620 -0.0853 0.5347 0.0551
-1.000 0.4226 0.03140 0.02476 -0.0863 0.5236 0.0585
-0.750 0.4596 0.03062 0.02363 -0.0873 0.5129 0.0624
-0.500 0.4860 0.02879 0.02168 -0.0882 0.5030 0.0640
-0.250 0.5158 0.02759 0.02039 -0.0890 0.4918 0.0671
0.000 0.5516 0.02760 0.01997 -0.0892 0.4817 0.0725
0.250 0.5785 0.02560 0.01793 -0.0902 0.4720 0.0745
0.500 0.6080 0.02466 0.01690 -0.0908 0.4615 0.0790
0.750 0.6395 0.02400 0.01592 -0.0911 0.4526 0.0853
1.000 0.6683 0.02301 0.01489 -0.0917 0.4423 0.0908
1.250 0.6984 0.02232 0.01398 -0.0920 0.4333 0.0998
1.500 0.7274 0.02167 0.01320 -0.0924 0.4241 0.1140
1.750 0.7559 0.02105 0.01248 -0.0928 0.4152 0.1312
2.000 0.7843 0.02052 0.01180 -0.0931 0.4069 0.1582
2.250 0.8123 0.01983 0.01108 -0.0936 0.3984 0.1908
2.500 0.8406 0.01922 0.01035 -0.0938 0.3910 0.2219
2.750 0.8701 0.01912 0.01010 -0.0937 0.3837 0.2310
3.000 0.9047 0.01869 0.00916 -0.0915 0.3779 0.0763
3.250 0.9326 0.01853 0.00883 -0.0913 0.3723 0.0763
3.500 0.9609 0.01830 0.00857 -0.0911 0.3660 0.0744
3.750 0.9886 0.01817 0.00838 -0.0910 0.3607 0.0740
4.000 1.0162 0.01819 0.00835 -0.0910 0.3560 0.0759
4.250 1.0440 0.01818 0.00843 -0.0910 0.3509 0.0807
4.500 1.0715 0.01819 0.00844 -0.0910 0.3462 0.0911
4.750 1.0992 0.01837 0.00848 -0.0910 0.3421 0.1120
5.000 1.1202 0.01721 0.00866 -0.0895 0.3382 1.0000
5.250 1.1472 0.01754 0.00894 -0.0894 0.3338 1.0000
5.500 1.1740 0.01789 0.00922 -0.0894 0.3300 1.0000
5.750 1.2009 0.01836 0.00957 -0.0893 0.3267 1.0000
6.000 1.2274 0.01880 0.01004 -0.0893 0.3235 1.0000
6.250 1.2536 0.01913 0.01043 -0.0892 0.3194 1.0000
6.500 1.2796 0.01937 0.01063 -0.0890 0.3143 1.0000
6.750 1.3055 0.01977 0.01094 -0.0889 0.3092 1.0000
7.000 1.3306 0.01999 0.01129 -0.0886 0.3043 1.0000
7.250 1.3559 0.02020 0.01151 -0.0884 0.2990 1.0000
7.500 1.3811 0.02058 0.01178 -0.0882 0.2938 1.0000
7.750 1.4054 0.02076 0.01215 -0.0878 0.2885 1.0000
8.000 1.4299 0.02097 0.01239 -0.0875 0.2832 1.0000
8.250 1.4539 0.02130 0.01269 -0.0871 0.2778 1.0000
8.500 1.4772 0.02142 0.01298 -0.0866 0.2707 1.0000
8.750 1.4996 0.02161 0.01316 -0.0860 0.2624 1.0000
9.000 1.5221 0.02172 0.01341 -0.0855 0.2527 1.0000
9.250 1.5438 0.02192 0.01368 -0.0848 0.2404 1.0000
9.500 1.5648 0.02224 0.01402 -0.0841 0.2258 1.0000
9.750 1.5841 0.02277 0.01452 -0.0832 0.2068 1.0000
10.000 1.6010 0.02358 0.01522 -0.0821 0.1720 1.0000
10.250 1.5902 0.02671 0.01778 -0.0783 0.1048 1.0000
10.750 1.5688 0.03193 0.02279 -0.0708 0.0448 1.0000
11.000 1.5645 0.03444 0.02542 -0.0689 0.0415 1.0000
11.250 1.5627 0.03705 0.02818 -0.0678 0.0397 1.0000
11.500 1.5604 0.04001 0.03134 -0.0673 0.0387 1.0000
11.750 1.5556 0.04351 0.03504 -0.0673 0.0380 1.0000
12.000 1.5480 0.04762 0.03934 -0.0677 0.0373 1.0000
12.250 1.5375 0.05230 0.04422 -0.0685 0.0369 1.0000
12.500 1.5245 0.05753 0.04963 -0.0697 0.0365 1.0000
12.750 1.5088 0.06320 0.05549 -0.0709 0.0362 1.0000
13.000 1.4914 0.06920 0.06167 -0.0723 0.0360 1.0000
13.250 1.4727 0.07542 0.06806 -0.0738 0.0358 1.0000
13.500 1.4535 0.08180 0.07460 -0.0753 0.0357 1.0000
13.750 1.4346 0.08834 0.08130 -0.0770 0.0355 1.0000
14.000 1.4168 0.09487 0.08798 -0.0788 0.0354 1.0000
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Polar data table (+)
Polar graphs
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