GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il) Reynolds number: 50,000 Max Cl/Cd: 39.62 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe122-il-50000-n5.txt Download as CSV file: xf-goe122-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 122 (MVA H.2) AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4129 0.11646 0.10968 -0.0059 1.0000 0.0788
-8.750 -0.4159 0.11532 0.10865 -0.0100 1.0000 0.0804
-8.500 -0.4191 0.11404 0.10748 -0.0145 1.0000 0.0810
-8.250 -0.3954 0.10614 0.09954 -0.0095 1.0000 0.0862
-8.000 -0.3899 0.10314 0.09660 -0.0108 1.0000 0.0903
-7.750 -0.3903 0.10111 0.09466 -0.0141 1.0000 0.0940
-7.500 -0.3884 0.09970 0.09334 -0.0230 1.0000 0.0956
-7.250 -0.3774 0.09409 0.08779 -0.0194 1.0000 0.0979
-7.000 -0.3670 0.09037 0.08408 -0.0188 1.0000 0.1019
-6.750 -0.3586 0.08738 0.08113 -0.0224 1.0000 0.1074
-6.500 -0.3486 0.08467 0.07845 -0.0310 1.0000 0.1112
-6.000 -0.3252 0.07853 0.07230 -0.0365 1.0000 0.1256
-5.750 -0.3198 0.07406 0.06799 -0.0301 1.0000 0.1313
-5.500 -0.3085 0.07118 0.06511 -0.0342 1.0000 0.1422
-5.250 -0.3001 0.06815 0.06215 -0.0323 1.0000 0.1493
-4.500 -0.2687 0.05991 0.05385 -0.0352 1.0000 0.1878
-4.250 -0.2601 0.05736 0.05134 -0.0340 1.0000 0.2043
-4.000 -0.1937 0.04865 0.04140 -0.0474 1.0000 0.0817
-3.750 -0.1796 0.04576 0.03852 -0.0466 1.0000 0.0778
-3.500 -0.1589 0.04266 0.03519 -0.0473 1.0000 0.0735
-3.250 -0.1159 0.03870 0.03062 -0.0518 0.9933 0.0701
-3.000 -0.0688 0.03567 0.02714 -0.0567 0.9818 0.0731
-2.750 -0.0205 0.03259 0.02338 -0.0611 0.9705 0.0714
-2.500 0.0255 0.03015 0.02037 -0.0647 0.9591 0.0711
-2.250 0.0704 0.02839 0.01818 -0.0681 0.9485 0.0756
-2.000 0.1141 0.02674 0.01608 -0.0708 0.9375 0.0768
-1.750 0.1546 0.02540 0.01437 -0.0728 0.9250 0.0775
-1.500 0.1928 0.02431 0.01298 -0.0743 0.9119 0.0786
-1.250 0.2302 0.02347 0.01184 -0.0753 0.8982 0.0806
-1.000 0.2652 0.02263 0.01094 -0.0763 0.8835 0.0867
-0.750 0.2979 0.02206 0.01021 -0.0766 0.8678 0.0920
-0.500 0.3289 0.02158 0.00955 -0.0765 0.8515 0.0957
-0.250 0.3585 0.02108 0.00901 -0.0763 0.8350 0.1019
0.000 0.3860 0.02074 0.00861 -0.0757 0.8165 0.1119
0.250 0.4134 0.02021 0.00827 -0.0752 0.7983 0.1452
0.750 0.4681 0.01808 0.00776 -0.0736 0.7630 1.0000
1.000 0.4944 0.01820 0.00761 -0.0727 0.7450 1.0000
1.250 0.5201 0.01838 0.00758 -0.0718 0.7260 1.0000
1.500 0.5459 0.01856 0.00756 -0.0709 0.7077 1.0000
1.750 0.5717 0.01876 0.00758 -0.0700 0.6901 1.0000
2.000 0.5976 0.01898 0.00765 -0.0692 0.6734 1.0000
2.250 0.6234 0.01924 0.00776 -0.0685 0.6572 1.0000
2.500 0.6492 0.01954 0.00793 -0.0678 0.6412 1.0000
2.750 0.6752 0.01988 0.00820 -0.0672 0.6258 1.0000
3.000 0.7014 0.02024 0.00848 -0.0667 0.6113 1.0000
3.250 0.7275 0.02063 0.00884 -0.0663 0.5970 1.0000
3.500 0.7533 0.02104 0.00926 -0.0658 0.5829 1.0000
3.750 0.7789 0.02145 0.00966 -0.0653 0.5685 1.0000
4.000 0.8041 0.02184 0.01004 -0.0647 0.5536 1.0000
4.250 0.8291 0.02220 0.01044 -0.0640 0.5382 1.0000
4.500 0.8538 0.02254 0.01077 -0.0633 0.5223 1.0000
4.750 0.8781 0.02292 0.01118 -0.0625 0.5060 1.0000
5.000 0.9027 0.02333 0.01163 -0.0618 0.4913 1.0000
5.250 0.9276 0.02379 0.01221 -0.0612 0.4786 1.0000
5.500 0.9522 0.02433 0.01287 -0.0607 0.4660 1.0000
5.750 0.9767 0.02488 0.01356 -0.0602 0.4533 1.0000
6.000 1.0011 0.02546 0.01431 -0.0596 0.4408 1.0000
6.250 1.0252 0.02605 0.01504 -0.0589 0.4280 1.0000
6.500 1.0481 0.02659 0.01572 -0.0581 0.4118 1.0000
6.750 1.0701 0.02709 0.01634 -0.0570 0.3933 1.0000
7.000 1.0916 0.02755 0.01694 -0.0559 0.3744 1.0000
7.250 1.1114 0.02809 0.01770 -0.0548 0.3531 1.0000
7.500 1.1300 0.02852 0.01826 -0.0535 0.3291 1.0000
7.750 1.1494 0.02917 0.01918 -0.0524 0.3084 1.0000
8.000 1.1674 0.02978 0.01999 -0.0511 0.2847 1.0000
8.250 1.1837 0.03054 0.02101 -0.0498 0.2542 1.0000
8.500 1.1951 0.03164 0.02203 -0.0481 0.2076 1.0000
8.750 1.1995 0.03365 0.02365 -0.0461 0.1602 1.0000
9.000 1.2045 0.03596 0.02587 -0.0443 0.1128 1.0000
9.250 1.2051 0.03856 0.02826 -0.0424 0.0914 1.0000
9.500 1.2025 0.04125 0.03085 -0.0404 0.0814 1.0000
9.750 1.1989 0.04398 0.03362 -0.0385 0.0747 1.0000
10.000 1.1939 0.04705 0.03675 -0.0372 0.0700 1.0000
10.250 1.1887 0.05034 0.04009 -0.0363 0.0670 1.0000
10.500 1.1872 0.05344 0.04340 -0.0356 0.0633 1.0000
10.750 1.1843 0.05679 0.04692 -0.0352 0.0598 1.0000
11.000 1.1805 0.06030 0.05047 -0.0349 0.0569 1.0000
11.250 1.1820 0.06332 0.05362 -0.0339 0.0544 1.0000
11.500 1.1859 0.06620 0.05677 -0.0330 0.0519 1.0000
11.750 1.1884 0.06931 0.06006 -0.0324 0.0490 1.0000
12.000 1.1916 0.07232 0.06315 -0.0315 0.0463 1.0000
12.250 1.2052 0.07466 0.06556 -0.0290 0.0439 1.0000
12.500 1.2041 0.07869 0.06994 -0.0292 0.0430 1.0000
12.750 1.1984 0.08333 0.07490 -0.0301 0.0421 1.0000
13.000 1.1895 0.08850 0.08037 -0.0317 0.0414 1.0000
13.250 1.1781 0.09419 0.08633 -0.0339 0.0409 1.0000
13.500 1.1645 0.10045 0.09285 -0.0367 0.0406 1.0000
13.750 1.1491 0.10734 0.09996 -0.0402 0.0406 1.0000
14.000 1.1324 0.11488 0.10771 -0.0444 0.0407 1.0000
14.250 1.1146 0.12317 0.11619 -0.0492 0.0411 1.0000
14.500 1.0965 0.13223 0.12540 -0.0546 0.0416 1.0000
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Polar data table (+)
Polar graphs
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