GOE 412 AIRFOIL (goe412-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 412 AIRFOIL (goe412-il) Reynolds number: 100,000 Max Cl/Cd: 55.76 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe412-il-100000-n5.txt Download as CSV file: xf-goe412-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 412 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2534 0.09526 0.09014 -0.0744 0.9724 0.0509
-9.250 -0.2410 0.09143 0.08630 -0.0773 0.9659 0.0507
-9.000 -0.2334 0.08572 0.08058 -0.0836 0.9601 0.0508
-8.750 -0.2313 0.08070 0.07556 -0.0882 0.9499 0.0509
-8.500 -0.2279 0.07607 0.07093 -0.0924 0.9400 0.0508
-8.250 -0.2197 0.07113 0.06596 -0.0976 0.9315 0.0505
-8.000 -0.2180 0.06616 0.06094 -0.1018 0.9199 0.0501
-7.750 -0.2165 0.05980 0.05446 -0.1072 0.9095 0.0497
-7.500 -0.2156 0.05140 0.04573 -0.1134 0.9010 0.0492
-7.250 -0.2172 0.04518 0.03908 -0.1153 0.8900 0.0491
-7.000 -0.2082 0.03926 0.03247 -0.1173 0.8836 0.0500
-6.750 -0.1968 0.03539 0.02794 -0.1171 0.8754 0.0508
-6.500 -0.1726 0.03274 0.02487 -0.1179 0.8714 0.0513
-6.250 -0.1529 0.03113 0.02302 -0.1173 0.8644 0.0518
-6.000 -0.1276 0.02958 0.02121 -0.1175 0.8593 0.0524
-5.750 -0.0986 0.02809 0.01946 -0.1182 0.8559 0.0532
-5.500 -0.0764 0.02701 0.01816 -0.1175 0.8491 0.0541
-5.250 -0.0493 0.02587 0.01680 -0.1176 0.8442 0.0552
-5.000 -0.0190 0.02481 0.01549 -0.1181 0.8407 0.0572
-4.750 0.0060 0.02401 0.01444 -0.1177 0.8348 0.0593
-4.500 0.0324 0.02335 0.01377 -0.1176 0.8293 0.0611
-4.250 0.0623 0.02262 0.01295 -0.1180 0.8255 0.0633
-4.000 0.0899 0.02200 0.01223 -0.1179 0.8208 0.0658
-3.750 0.1147 0.02151 0.01161 -0.1173 0.8145 0.0690
-3.500 0.1434 0.02093 0.01103 -0.1175 0.8102 0.0734
-3.250 0.1747 0.02036 0.01037 -0.1180 0.8070 0.0819
-3.000 0.1963 0.02016 0.01022 -0.1170 0.7996 0.0931
-2.750 0.2243 0.01983 0.00991 -0.1171 0.7948 0.1095
-2.500 0.2551 0.01951 0.00957 -0.1175 0.7912 0.1266
-2.250 0.2787 0.01945 0.00951 -0.1169 0.7846 0.1431
-2.000 0.3052 0.01926 0.00933 -0.1167 0.7792 0.1623
-1.750 0.3347 0.01894 0.00908 -0.1170 0.7752 0.1879
-1.500 0.3600 0.01879 0.00908 -0.1167 0.7696 0.2189
-1.250 0.3850 0.01867 0.00911 -0.1162 0.7635 0.2604
-1.000 0.4142 0.01843 0.00894 -0.1165 0.7592 0.3129
-0.750 0.4417 0.01816 0.00886 -0.1164 0.7545 0.3754
-0.500 0.4635 0.01793 0.00902 -0.1155 0.7478 0.4774
-0.250 0.4856 0.01715 0.00905 -0.1137 0.7432 0.7147
0.000 0.5521 0.01673 0.00879 -0.1208 0.7402 1.0000
0.250 0.5716 0.01704 0.00900 -0.1194 0.7327 1.0000
0.500 0.5978 0.01713 0.00896 -0.1190 0.7272 1.0000
0.750 0.6275 0.01714 0.00881 -0.1191 0.7229 1.0000
1.000 0.6467 0.01745 0.00907 -0.1177 0.7146 1.0000
1.250 0.6748 0.01747 0.00897 -0.1175 0.7090 1.0000
1.500 0.6979 0.01765 0.00908 -0.1166 0.7016 1.0000
1.750 0.7233 0.01774 0.00909 -0.1161 0.6946 1.0000
2.000 0.7507 0.01779 0.00905 -0.1158 0.6886 1.0000
2.250 0.7723 0.01802 0.00925 -0.1147 0.6804 1.0000
2.500 0.8025 0.01796 0.00909 -0.1149 0.6747 1.0000
2.750 0.8218 0.01824 0.00938 -0.1134 0.6651 1.0000
3.000 0.8516 0.01816 0.00921 -0.1135 0.6585 1.0000
3.250 0.8709 0.01844 0.00951 -0.1119 0.6486 1.0000
3.500 0.8993 0.01842 0.00941 -0.1118 0.6415 1.0000
3.750 0.9193 0.01867 0.00969 -0.1104 0.6316 1.0000
4.000 0.9450 0.01875 0.00974 -0.1099 0.6236 1.0000
4.250 0.9673 0.01893 0.00993 -0.1089 0.6139 1.0000
4.500 0.9901 0.01911 0.01011 -0.1079 0.6046 1.0000
4.750 1.0149 0.01923 0.01022 -0.1073 0.5959 1.0000
5.000 1.0354 0.01950 0.01053 -0.1060 0.5858 1.0000
5.250 1.0601 0.01961 0.01061 -0.1053 0.5762 1.0000
5.500 1.0807 0.01984 0.01087 -0.1040 0.5647 1.0000
5.750 1.1006 0.02009 0.01116 -0.1026 0.5525 1.0000
6.000 1.1218 0.02032 0.01138 -0.1014 0.5408 1.0000
6.250 1.1442 0.02052 0.01158 -0.1004 0.5296 1.0000
6.500 1.1622 0.02088 0.01198 -0.0988 0.5172 1.0000
6.750 1.1806 0.02122 0.01236 -0.0972 0.5046 1.0000
7.000 1.1985 0.02157 0.01272 -0.0955 0.4912 1.0000
7.250 1.2151 0.02195 0.01310 -0.0936 0.4769 1.0000
7.500 1.2295 0.02237 0.01352 -0.0914 0.4620 1.0000
7.750 1.2431 0.02286 0.01399 -0.0891 0.4466 1.0000
8.000 1.2565 0.02341 0.01453 -0.0869 0.4312 1.0000
8.250 1.2695 0.02402 0.01515 -0.0847 0.4160 1.0000
8.500 1.2820 0.02469 0.01580 -0.0825 0.4012 1.0000
8.750 1.2940 0.02542 0.01652 -0.0803 0.3868 1.0000
9.000 1.3053 0.02623 0.01734 -0.0781 0.3722 1.0000
9.250 1.3159 0.02710 0.01824 -0.0760 0.3579 1.0000
9.500 1.3257 0.02806 0.01919 -0.0738 0.3436 1.0000
9.750 1.3348 0.02909 0.02022 -0.0717 0.3296 1.0000
10.000 1.3437 0.03017 0.02131 -0.0696 0.3164 1.0000
10.250 1.3526 0.03131 0.02244 -0.0676 0.3044 1.0000
10.500 1.3620 0.03246 0.02367 -0.0658 0.2931 1.0000
10.750 1.3712 0.03367 0.02494 -0.0641 0.2824 1.0000
11.000 1.3794 0.03496 0.02625 -0.0623 0.2722 1.0000
11.250 1.3865 0.03635 0.02769 -0.0606 0.2614 1.0000
11.500 1.3932 0.03782 0.02922 -0.0590 0.2507 1.0000
11.750 1.3984 0.03942 0.03085 -0.0573 0.2401 1.0000
12.000 1.4016 0.04119 0.03264 -0.0556 0.2294 1.0000
12.250 1.4045 0.04308 0.03459 -0.0541 0.2180 1.0000
12.500 1.4072 0.04503 0.03659 -0.0527 0.2075 1.0000
12.750 1.4091 0.04710 0.03868 -0.0513 0.1983 1.0000
13.000 1.4106 0.04927 0.04090 -0.0500 0.1891 1.0000
13.250 1.4120 0.05155 0.04325 -0.0489 0.1799 1.0000
13.750 1.4101 0.05677 0.04860 -0.0470 0.1605 1.0000
14.000 1.4081 0.05965 0.05156 -0.0462 0.1498 1.0000
14.250 1.4054 0.06272 0.05473 -0.0457 0.1386 1.0000
14.500 1.4055 0.06564 0.05782 -0.0454 0.1232 1.0000
14.750 1.3997 0.06929 0.06150 -0.0451 0.1022 1.0000
15.000 1.3864 0.07397 0.06606 -0.0452 0.0905 1.0000
15.250 1.3730 0.07883 0.07087 -0.0454 0.0829 1.0000
15.500 1.3621 0.08348 0.07557 -0.0457 0.0759 1.0000
15.750 1.3484 0.08866 0.08080 -0.0463 0.0701 1.0000
16.000 1.3404 0.09321 0.08550 -0.0470 0.0621 1.0000
16.250 1.3301 0.09823 0.09066 -0.0479 0.0551 1.0000
16.500 1.3179 0.10366 0.09618 -0.0492 0.0495 1.0000
16.750 1.3062 0.10914 0.10176 -0.0508 0.0450 1.0000
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