GOE 480 AIRFOIL (goe480-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 480 AIRFOIL (goe480-il) Reynolds number: 100,000 Max Cl/Cd: 57.33 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe480-il-100000-n5.txt Download as CSV file: xf-goe480-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 480 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2700 0.12422 0.11892 -0.0452 1.0000 0.0707
-10.750 -0.2841 0.12308 0.11787 -0.0466 1.0000 0.0711
-10.500 -0.2927 0.12126 0.11614 -0.0468 1.0000 0.0713
-10.250 -0.2893 0.11759 0.11254 -0.0451 1.0000 0.0717
-10.000 -0.2730 0.11401 0.10897 -0.0419 1.0000 0.0730
-9.750 -0.2662 0.11182 0.10683 -0.0405 0.9991 0.0747
-9.500 -0.2464 0.10829 0.10328 -0.0442 0.9929 0.0786
-9.250 -0.2384 0.10505 0.10003 -0.0519 0.9838 0.0831
-9.000 -0.2362 0.10168 0.09666 -0.0614 0.9711 0.0840
-8.500 -0.1885 0.09308 0.08802 -0.0627 0.9618 0.0871
-8.250 -0.1695 0.09001 0.08493 -0.0651 0.9535 0.0899
-8.000 -0.1524 0.08658 0.08148 -0.0696 0.9455 0.0930
-7.750 -0.1571 0.08292 0.07778 -0.0832 0.9253 0.0976
-7.500 -0.1404 0.07826 0.07309 -0.0877 0.9173 0.0985
-7.250 -0.1165 0.07586 0.07070 -0.0839 0.9119 0.1006
-7.000 -0.0943 0.07289 0.06769 -0.0863 0.9050 0.1031
-6.750 -0.0894 0.06540 0.06001 -0.0965 0.8904 0.0817
-6.500 -0.0740 0.06184 0.05637 -0.0996 0.8808 0.0803
-6.250 -0.0568 0.05779 0.05219 -0.1041 0.8719 0.0798
-6.000 -0.0427 0.05383 0.04809 -0.1074 0.8619 0.0779
-5.750 -0.0254 0.04823 0.04219 -0.1125 0.8536 0.0752
-5.500 -0.0102 0.04392 0.03759 -0.1151 0.8442 0.0746
-5.250 0.0114 0.04118 0.03464 -0.1165 0.8370 0.0756
-5.000 0.0312 0.03795 0.03108 -0.1177 0.8296 0.0756
-4.750 0.0508 0.03467 0.02738 -0.1184 0.8217 0.0750
-4.500 0.0761 0.03192 0.02421 -0.1193 0.8163 0.0749
-4.250 0.0955 0.03015 0.02214 -0.1187 0.8077 0.0751
-4.000 0.1213 0.02876 0.02049 -0.1188 0.8014 0.0764
-3.750 0.1458 0.02748 0.01894 -0.1186 0.7948 0.0777
-3.500 0.1696 0.02625 0.01742 -0.1181 0.7874 0.0784
-3.250 0.1979 0.02498 0.01583 -0.1182 0.7819 0.0787
-3.000 0.2211 0.02409 0.01471 -0.1174 0.7741 0.0792
-2.750 0.2480 0.02321 0.01359 -0.1171 0.7676 0.0799
-2.500 0.2757 0.02244 0.01260 -0.1169 0.7616 0.0806
-2.250 0.3000 0.02191 0.01191 -0.1161 0.7537 0.0818
-2.000 0.3288 0.02138 0.01118 -0.1160 0.7478 0.0835
-1.750 0.3534 0.02089 0.01062 -0.1153 0.7403 0.0848
-1.500 0.3796 0.02036 0.01006 -0.1148 0.7333 0.0860
-1.250 0.4079 0.01989 0.00954 -0.1146 0.7275 0.0873
-1.000 0.4310 0.01961 0.00929 -0.1137 0.7190 0.0886
-0.750 0.4589 0.01926 0.00890 -0.1134 0.7128 0.0903
-0.500 0.4830 0.01906 0.00869 -0.1125 0.7050 0.0922
-0.250 0.5088 0.01884 0.00844 -0.1119 0.6976 0.0948
0.000 0.5356 0.01864 0.00820 -0.1115 0.6910 0.0986
0.250 0.5592 0.01851 0.00813 -0.1106 0.6825 0.1032
0.500 0.5877 0.01831 0.00788 -0.1104 0.6763 0.1086
0.750 0.6109 0.01827 0.00790 -0.1094 0.6673 0.1150
1.000 0.6387 0.01810 0.00778 -0.1091 0.6603 0.1298
1.250 0.6636 0.01801 0.00784 -0.1085 0.6520 0.1737
1.500 0.6903 0.01769 0.00782 -0.1083 0.6443 0.2704
2.000 0.7650 0.01632 0.00793 -0.1118 0.6276 1.0000
2.250 0.7890 0.01648 0.00799 -0.1109 0.6192 1.0000
2.500 0.8135 0.01662 0.00803 -0.1101 0.6107 1.0000
2.750 0.8374 0.01680 0.00813 -0.1092 0.6020 1.0000
3.000 0.8619 0.01695 0.00818 -0.1083 0.5934 1.0000
3.250 0.8852 0.01715 0.00833 -0.1073 0.5843 1.0000
3.500 0.9100 0.01730 0.00839 -0.1066 0.5758 1.0000
3.750 0.9326 0.01753 0.00859 -0.1055 0.5662 1.0000
4.000 0.9579 0.01768 0.00865 -0.1048 0.5579 1.0000
4.250 0.9794 0.01795 0.00892 -0.1036 0.5478 1.0000
4.500 1.0045 0.01813 0.00901 -0.1029 0.5396 1.0000
4.750 1.0256 0.01843 0.00933 -0.1016 0.5294 1.0000
5.000 1.0496 0.01867 0.00951 -0.1008 0.5210 1.0000
5.250 1.0711 0.01897 0.00982 -0.0996 0.5114 1.0000
5.500 1.0940 0.01925 0.01009 -0.0987 0.5026 1.0000
5.750 1.1157 0.01957 0.01040 -0.0975 0.4933 1.0000
6.000 1.1374 0.01990 0.01073 -0.0964 0.4843 1.0000
6.250 1.1590 0.02023 0.01107 -0.0953 0.4753 1.0000
6.500 1.1796 0.02061 0.01148 -0.0940 0.4662 1.0000
6.750 1.2011 0.02095 0.01181 -0.0929 0.4574 1.0000
7.000 1.2200 0.02137 0.01229 -0.0914 0.4479 1.0000
7.250 1.2415 0.02173 0.01263 -0.0903 0.4395 1.0000
7.500 1.2591 0.02220 0.01319 -0.0887 0.4302 1.0000
7.750 1.2803 0.02259 0.01356 -0.0875 0.4222 1.0000
8.000 1.2961 0.02310 0.01418 -0.0856 0.4125 1.0000
8.250 1.3157 0.02353 0.01459 -0.0843 0.4043 1.0000
8.500 1.3299 0.02408 0.01525 -0.0822 0.3944 1.0000
8.750 1.3457 0.02457 0.01576 -0.0803 0.3852 1.0000
9.000 1.3570 0.02509 0.01632 -0.0777 0.3747 1.0000
9.250 1.3667 0.02570 0.01699 -0.0749 0.3641 1.0000
9.500 1.3779 0.02628 0.01756 -0.0724 0.3540 1.0000
9.750 1.3864 0.02700 0.01837 -0.0698 0.3436 1.0000
10.000 1.3957 0.02774 0.01916 -0.0673 0.3338 1.0000
10.250 1.4042 0.02853 0.01996 -0.0648 0.3238 1.0000
10.500 1.4100 0.02949 0.02102 -0.0623 0.3130 1.0000
10.750 1.4160 0.03048 0.02205 -0.0598 0.3024 1.0000
11.000 1.4204 0.03160 0.02319 -0.0574 0.2915 1.0000
11.250 1.4239 0.03289 0.02458 -0.0551 0.2804 1.0000
11.500 1.4269 0.03427 0.02601 -0.0530 0.2693 1.0000
11.750 1.4281 0.03583 0.02758 -0.0508 0.2579 1.0000
12.000 1.4283 0.03761 0.02946 -0.0489 0.2457 1.0000
12.250 1.4276 0.03956 0.03147 -0.0472 0.2333 1.0000
12.500 1.4258 0.04171 0.03367 -0.0456 0.2207 1.0000
12.750 1.4225 0.04410 0.03610 -0.0442 0.2077 1.0000
13.000 1.4174 0.04678 0.03882 -0.0429 0.1935 1.0000
13.250 1.4108 0.04978 0.04185 -0.0419 0.1780 1.0000
13.500 1.4025 0.05311 0.04521 -0.0411 0.1614 1.0000
13.750 1.3917 0.05690 0.04898 -0.0406 0.1441 1.0000
14.000 1.3790 0.06113 0.05317 -0.0404 0.1284 1.0000
14.250 1.3657 0.06564 0.05765 -0.0405 0.1156 1.0000
14.500 1.3526 0.07036 0.06236 -0.0409 0.1056 1.0000
15.000 1.3282 0.08011 0.07217 -0.0423 0.0913 1.0000
15.250 1.3152 0.08531 0.07738 -0.0433 0.0863 1.0000
15.500 1.3073 0.08990 0.08206 -0.0443 0.0811 1.0000
15.750 1.2975 0.09482 0.08703 -0.0454 0.0770 1.0000
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