GOE 413 AIRFOIL (goe413-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 413 AIRFOIL (goe413-il) Reynolds number: 100,000 Max Cl/Cd: 52.27 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe413-il-100000-n5.txt Download as CSV file: xf-goe413-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 413 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2761 0.11712 0.11158 -0.0460 1.0000 0.0684
-11.000 -0.2741 0.11337 0.10787 -0.0479 1.0000 0.0684
-10.000 -0.4760 0.04967 0.04302 -0.1072 0.9194 0.0630
-9.750 -0.4678 0.04666 0.03981 -0.1096 0.9081 0.0635
-9.500 -0.4564 0.04423 0.03721 -0.1110 0.8971 0.0640
-9.250 -0.4442 0.04192 0.03470 -0.1121 0.8867 0.0645
-9.000 -0.4302 0.03968 0.03220 -0.1129 0.8770 0.0650
-8.750 -0.4146 0.03763 0.02989 -0.1135 0.8674 0.0655
-8.500 -0.3966 0.03575 0.02775 -0.1139 0.8582 0.0659
-8.250 -0.3769 0.03411 0.02585 -0.1141 0.8493 0.0664
-8.000 -0.3557 0.03263 0.02413 -0.1141 0.8399 0.0669
-7.750 -0.3331 0.03130 0.02256 -0.1141 0.8322 0.0674
-7.500 -0.3102 0.03014 0.02119 -0.1141 0.8224 0.0682
-7.250 -0.2859 0.02906 0.01983 -0.1140 0.8151 0.0691
-7.000 -0.2621 0.02810 0.01885 -0.1137 0.8053 0.0700
-6.750 -0.2373 0.02723 0.01795 -0.1134 0.7971 0.0709
-6.500 -0.2124 0.02644 0.01711 -0.1132 0.7883 0.0717
-6.250 -0.1871 0.02569 0.01629 -0.1129 0.7797 0.0725
-6.000 -0.1612 0.02498 0.01549 -0.1127 0.7724 0.0734
-5.750 -0.1356 0.02435 0.01480 -0.1125 0.7629 0.0743
-5.500 -0.1091 0.02373 0.01406 -0.1122 0.7560 0.0753
-5.250 -0.0831 0.02320 0.01349 -0.1121 0.7466 0.0766
-5.000 -0.0567 0.02261 0.01289 -0.1120 0.7393 0.0783
-4.750 -0.0299 0.02212 0.01237 -0.1120 0.7319 0.0802
-4.500 -0.0028 0.02168 0.01186 -0.1119 0.7238 0.0823
-4.250 0.0250 0.02121 0.01130 -0.1118 0.7179 0.0842
-4.000 0.0522 0.02081 0.01091 -0.1120 0.7094 0.0865
-3.750 0.0801 0.02042 0.01046 -0.1120 0.7028 0.0896
-3.500 0.1084 0.02003 0.01004 -0.1120 0.6971 0.0941
-3.250 0.1361 0.01969 0.00978 -0.1122 0.6895 0.1028
-3.000 0.1644 0.01932 0.00949 -0.1123 0.6835 0.1228
-2.750 0.1930 0.01906 0.00929 -0.1124 0.6779 0.1543
-2.500 0.2211 0.01895 0.00921 -0.1124 0.6710 0.1794
-2.250 0.2497 0.01883 0.00909 -0.1124 0.6652 0.2029
-2.000 0.2786 0.01873 0.00895 -0.1124 0.6603 0.2236
-1.750 0.3064 0.01873 0.00899 -0.1125 0.6533 0.2399
-1.500 0.3348 0.01869 0.00893 -0.1124 0.6474 0.2552
-1.250 0.3637 0.01864 0.00880 -0.1124 0.6425 0.2703
-1.000 0.3916 0.01866 0.00885 -0.1124 0.6362 0.2867
-0.750 0.4195 0.01866 0.00889 -0.1123 0.6300 0.3038
-0.500 0.4481 0.01863 0.00885 -0.1123 0.6246 0.3234
-0.250 0.4764 0.01863 0.00887 -0.1122 0.6192 0.3450
0.000 0.5035 0.01869 0.00900 -0.1121 0.6124 0.3698
0.250 0.5313 0.01866 0.00905 -0.1119 0.6067 0.3983
0.500 0.5600 0.01863 0.00903 -0.1118 0.6019 0.4293
0.750 0.5864 0.01871 0.00927 -0.1116 0.5954 0.4585
1.000 0.6134 0.01877 0.00943 -0.1113 0.5894 0.4904
1.250 0.6414 0.01879 0.00948 -0.1110 0.5842 0.5248
1.500 0.6691 0.01886 0.00960 -0.1108 0.5790 0.5611
1.750 0.6949 0.01898 0.00985 -0.1104 0.5725 0.5982
2.000 0.7210 0.01898 0.00997 -0.1098 0.5667 0.6381
2.250 0.7463 0.01890 0.01002 -0.1088 0.5620 0.6889
2.500 0.7670 0.01894 0.01032 -0.1070 0.5559 0.7615
2.750 0.7854 0.01885 0.01045 -0.1045 0.5497 0.8614
3.000 0.8163 0.01882 0.01038 -0.1048 0.5442 1.0000
3.250 0.8446 0.01907 0.01054 -0.1049 0.5386 1.0000
3.500 0.8708 0.01939 0.01085 -0.1048 0.5315 1.0000
3.750 0.8990 0.01959 0.01096 -0.1048 0.5256 1.0000
4.000 0.9272 0.01981 0.01109 -0.1048 0.5202 1.0000
4.250 0.9521 0.02018 0.01149 -0.1046 0.5127 1.0000
4.500 0.9794 0.02040 0.01165 -0.1044 0.5065 1.0000
4.750 1.0067 0.02064 0.01182 -0.1043 0.5007 1.0000
5.000 1.0308 0.02103 0.01226 -0.1039 0.4931 1.0000
5.250 1.0577 0.02124 0.01242 -0.1037 0.4868 1.0000
5.500 1.0825 0.02156 0.01273 -0.1032 0.4795 1.0000
5.750 1.1067 0.02186 0.01304 -0.1027 0.4711 1.0000
6.000 1.1323 0.02206 0.01317 -0.1022 0.4635 1.0000
6.250 1.1541 0.02242 0.01358 -0.1014 0.4534 1.0000
6.500 1.1781 0.02265 0.01376 -0.1008 0.4446 1.0000
6.750 1.1992 0.02304 0.01417 -0.0999 0.4345 1.0000
7.000 1.2216 0.02337 0.01447 -0.0991 0.4257 1.0000
7.250 1.2421 0.02379 0.01490 -0.0981 0.4160 1.0000
7.500 1.2626 0.02421 0.01532 -0.0971 0.4071 1.0000
7.750 1.2819 0.02468 0.01579 -0.0960 0.3977 1.0000
8.000 1.3006 0.02520 0.01632 -0.0948 0.3890 1.0000
8.250 1.3179 0.02574 0.01686 -0.0935 0.3799 1.0000
8.500 1.3337 0.02637 0.01750 -0.0921 0.3709 1.0000
8.750 1.3472 0.02701 0.01814 -0.0903 0.3623 1.0000
9.000 1.3611 0.02775 0.01890 -0.0887 0.3546 1.0000
9.250 1.3735 0.02861 0.01980 -0.0870 0.3465 1.0000
9.500 1.3854 0.02949 0.02067 -0.0854 0.3384 1.0000
9.750 1.3943 0.03061 0.02185 -0.0838 0.3292 1.0000
10.000 1.4043 0.03170 0.02294 -0.0823 0.3210 1.0000
10.250 1.4122 0.03304 0.02436 -0.0808 0.3127 1.0000
10.500 1.4205 0.03433 0.02564 -0.0794 0.3047 1.0000
10.750 1.4246 0.03605 0.02744 -0.0780 0.2949 1.0000
11.000 1.4291 0.03776 0.02917 -0.0766 0.2859 1.0000
11.250 1.4317 0.03973 0.03122 -0.0754 0.2763 1.0000
11.500 1.4327 0.04192 0.03347 -0.0743 0.2661 1.0000
11.750 1.4314 0.04436 0.03590 -0.0732 0.2551 1.0000
12.000 1.4293 0.04709 0.03873 -0.0724 0.2438 1.0000
12.250 1.4268 0.04992 0.04161 -0.0717 0.2329 1.0000
12.500 1.4219 0.05307 0.04478 -0.0711 0.2212 1.0000
12.750 1.4152 0.05656 0.04829 -0.0707 0.2081 1.0000
13.000 1.4066 0.06040 0.05215 -0.0704 0.1935 1.0000
13.250 1.3958 0.06464 0.05639 -0.0704 0.1777 1.0000
13.500 1.3834 0.06921 0.06093 -0.0705 0.1611 1.0000
13.750 1.3691 0.07414 0.06581 -0.0708 0.1453 1.0000
14.000 1.3547 0.07923 0.07085 -0.0713 0.1323 1.0000
14.250 1.3411 0.08432 0.07592 -0.0719 0.1227 1.0000
14.500 1.3290 0.08933 0.08091 -0.0726 0.1158 1.0000
14.750 1.3202 0.09396 0.08557 -0.0734 0.1107 1.0000
15.000 1.3128 0.09845 0.09007 -0.0741 0.1067 1.0000
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