GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 549 AIRFOIL (goe549-il) Reynolds number: 100,000 Max Cl/Cd: 43.04 at α=11.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe549-il-100000.txt Download as CSV file: xf-goe549-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 549 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2541 0.11605 0.11128 -0.0448 1.0000 0.1029
-10.000 -0.2793 0.11594 0.11134 -0.0472 1.0000 0.1043
-9.750 -0.3062 0.11573 0.11131 -0.0475 1.0000 0.1046
-9.500 -0.2700 0.10874 0.10429 -0.0435 1.0000 0.1068
-9.250 -0.2675 0.10683 0.10245 -0.0403 1.0000 0.1088
-9.000 -0.2790 0.10610 0.10183 -0.0367 1.0000 0.1102
-8.750 -0.2979 0.10602 0.10189 -0.0326 1.0000 0.1114
-8.500 -0.2913 0.10317 0.09908 -0.0364 0.9949 0.1163
-8.250 -0.3065 0.09856 0.09456 -0.0563 0.9756 0.1208
-8.000 -0.2459 0.09351 0.08941 -0.0495 0.9777 0.1269
-7.750 -0.2500 0.08909 0.08502 -0.0671 0.9585 0.1360
-7.500 -0.2100 0.08402 0.07992 -0.0651 0.9554 0.1399
-7.250 -0.1810 0.07977 0.07564 -0.0711 0.9472 0.1483
-7.000 -0.1655 0.07427 0.07013 -0.0804 0.9338 0.1556
-6.750 -0.1561 0.06870 0.06443 -0.0936 0.9181 0.1689
-6.500 -0.1126 0.06574 0.06149 -0.0915 0.9154 0.1746
-6.250 -0.0990 0.06194 0.05762 -0.0963 0.9014 0.1880
-6.000 -0.0860 0.05891 0.05452 -0.0990 0.8880 0.2027
-5.750 -0.0707 0.05643 0.05198 -0.0998 0.8763 0.2186
-5.500 -0.0859 0.03967 0.03342 -0.1116 0.8595 0.1069
-5.250 -0.0591 0.03579 0.02914 -0.1122 0.8530 0.0971
-5.000 -0.0447 0.03311 0.02582 -0.1105 0.8417 0.0932
-4.750 -0.0172 0.03102 0.02331 -0.1105 0.8353 0.0937
-4.500 0.0025 0.02944 0.02122 -0.1090 0.8253 0.0919
-4.250 0.0320 0.02783 0.01925 -0.1088 0.8194 0.0917
-4.000 0.0531 0.02682 0.01809 -0.1077 0.8099 0.0931
-3.750 0.0847 0.02569 0.01681 -0.1079 0.8049 0.0968
-3.500 0.1047 0.02512 0.01613 -0.1065 0.7952 0.0987
-3.250 0.1358 0.02412 0.01496 -0.1064 0.7899 0.1009
-3.000 0.1571 0.02371 0.01447 -0.1052 0.7812 0.1034
-2.750 0.1848 0.02281 0.01359 -0.1047 0.7753 0.1075
-2.500 0.2067 0.02241 0.01325 -0.1036 0.7680 0.1143
-2.250 0.2308 0.02190 0.01276 -0.1027 0.7611 0.1260
-2.000 0.2563 0.02118 0.01214 -0.1019 0.7557 0.1539
-1.750 0.2671 0.01972 0.01225 -0.0994 0.7475 0.4737
-1.500 0.2918 0.01928 0.01213 -0.0976 0.7426 0.6218
-1.250 0.3076 0.01932 0.01246 -0.0949 0.7343 0.7128
-1.000 0.3417 0.01883 0.01226 -0.0943 0.7288 0.8376
-0.750 0.4565 0.01839 0.01166 -0.1100 0.7222 1.0000
-0.500 0.4717 0.01858 0.01163 -0.1084 0.7148 1.0000
-0.250 0.4938 0.01873 0.01155 -0.1075 0.7086 1.0000
0.000 0.5124 0.01906 0.01173 -0.1061 0.7006 1.0000
0.250 0.5416 0.01903 0.01146 -0.1060 0.6956 1.0000
0.500 0.5571 0.01958 0.01193 -0.1042 0.6866 1.0000
0.750 0.5862 0.01959 0.01174 -0.1041 0.6812 1.0000
1.000 0.6037 0.02014 0.01223 -0.1025 0.6728 1.0000
1.250 0.6317 0.02022 0.01215 -0.1023 0.6667 1.0000
1.500 0.6515 0.02072 0.01258 -0.1010 0.6589 1.0000
1.750 0.6780 0.02090 0.01264 -0.1006 0.6522 1.0000
2.000 0.7005 0.02131 0.01299 -0.0997 0.6449 1.0000
2.250 0.7246 0.02163 0.01322 -0.0990 0.6374 1.0000
2.500 0.7509 0.02191 0.01341 -0.0986 0.6310 1.0000
2.750 0.7712 0.02241 0.01389 -0.0974 0.6225 1.0000
3.000 0.8039 0.02245 0.01378 -0.0978 0.6173 1.0000
3.250 0.8176 0.02324 0.01464 -0.0958 0.6074 1.0000
3.500 0.8499 0.02328 0.01454 -0.0961 0.6020 1.0000
3.750 0.8635 0.02410 0.01544 -0.0942 0.5922 1.0000
4.000 0.8952 0.02415 0.01538 -0.0944 0.5865 1.0000
4.250 0.9088 0.02500 0.01632 -0.0925 0.5770 1.0000
4.500 0.9399 0.02503 0.01627 -0.0927 0.5712 1.0000
4.750 0.9539 0.02587 0.01720 -0.0908 0.5619 1.0000
5.000 0.9838 0.02595 0.01721 -0.0908 0.5559 1.0000
5.250 0.9987 0.02677 0.01812 -0.0891 0.5473 1.0000
5.500 1.0271 0.02687 0.01819 -0.0889 0.5409 1.0000
5.750 1.0442 0.02758 0.01898 -0.0875 0.5331 1.0000
6.000 1.0688 0.02788 0.01928 -0.0869 0.5263 1.0000
6.250 1.0931 0.02825 0.01967 -0.0863 0.5201 1.0000
6.500 1.1094 0.02894 0.02044 -0.0847 0.5121 1.0000
6.750 1.1465 0.02864 0.02009 -0.0857 0.5076 1.0000
7.000 1.1485 0.03012 0.02176 -0.0825 0.4985 1.0000
7.250 1.1825 0.02995 0.02156 -0.0831 0.4936 1.0000
7.500 1.1883 0.03127 0.02306 -0.0804 0.4856 1.0000
7.750 1.2164 0.03137 0.02319 -0.0803 0.4800 1.0000
8.000 1.2380 0.03196 0.02384 -0.0794 0.4744 1.0000
8.250 1.2462 0.03312 0.02514 -0.0771 0.4670 1.0000
8.500 1.2925 0.03219 0.02415 -0.0790 0.4623 1.0000
8.750 1.2827 0.03419 0.02639 -0.0745 0.4537 1.0000
9.000 1.3277 0.03320 0.02536 -0.0761 0.4481 1.0000
9.250 1.3234 0.03496 0.02730 -0.0723 0.4406 1.0000
9.500 1.3538 0.03482 0.02723 -0.0724 0.4346 1.0000
9.750 1.3718 0.03543 0.02794 -0.0711 0.4285 1.0000
10.000 1.3752 0.03667 0.02933 -0.0682 0.4216 1.0000
10.250 1.4340 0.03526 0.02785 -0.0715 0.4162 1.0000
10.500 1.3984 0.03833 0.03121 -0.0643 0.4089 1.0000
10.750 1.4661 0.03583 0.02864 -0.0681 0.4003 1.0000
11.000 1.4382 0.03829 0.03134 -0.0615 0.3936 1.0000
11.250 1.4805 0.03654 0.02956 -0.0622 0.3822 1.0000
11.500 1.5137 0.03517 0.02812 -0.0619 0.3694 1.0000
11.750 1.4974 0.03652 0.02965 -0.0563 0.3619 1.0000
12.000 1.5121 0.03637 0.02952 -0.0542 0.3516 1.0000
12.250 1.5304 0.03592 0.02901 -0.0525 0.3397 1.0000
12.500 1.5091 0.03792 0.03124 -0.0477 0.3324 1.0000
12.750 1.5158 0.03838 0.03173 -0.0454 0.3220 1.0000
13.000 1.5143 0.03950 0.03294 -0.0428 0.3124 1.0000
13.250 1.5017 0.04169 0.03530 -0.0400 0.3043 1.0000
13.500 1.5054 0.04268 0.03635 -0.0382 0.2938 1.0000
13.750 1.4857 0.04584 0.03971 -0.0360 0.2849 1.0000
14.000 1.4735 0.04860 0.04259 -0.0345 0.2746 1.0000
14.250 1.4623 0.05142 0.04549 -0.0333 0.2628 1.0000
14.500 1.4466 0.05497 0.04911 -0.0325 0.2499 1.0000
14.750 1.4272 0.05935 0.05357 -0.0323 0.2361 1.0000
15.000 1.4048 0.06450 0.05881 -0.0326 0.2213 1.0000
15.250 1.3807 0.07028 0.06465 -0.0333 0.2048 1.0000
15.500 1.3568 0.07628 0.07063 -0.0343 0.1853 1.0000
15.750 1.3347 0.08221 0.07639 -0.0354 0.1637 1.0000
16.000 1.3123 0.08847 0.08248 -0.0368 0.1439 1.0000
16.250 1.2911 0.09466 0.08840 -0.0382 0.1271 1.0000
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