GOE 384 AIRFOIL (goe384-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 384 AIRFOIL (goe384-il) Reynolds number: 100,000 Max Cl/Cd: 39.54 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe384-il-100000-n5.txt Download as CSV file: xf-goe384-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 384 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
------ -------- --------- --------- -------- -------- --------
-10.750 0.0111 0.10996 0.10431 -0.0930 0.7957 0.0879
-10.500 0.0096 0.10675 0.10106 -0.0952 0.7882 0.0883
-10.000 0.0111 0.09670 0.09091 -0.0993 0.7749 0.0723
-9.750 0.0218 0.09426 0.08844 -0.0996 0.7678 0.0728
-9.250 0.0094 0.08343 0.07751 -0.1062 0.7566 0.0647
-9.000 0.0165 0.08065 0.07471 -0.1072 0.7505 0.0644
-8.750 0.0197 0.07728 0.07133 -0.1090 0.7444 0.0639
-8.500 0.0190 0.07327 0.06728 -0.1114 0.7394 0.0635
-8.250 0.0113 0.06820 0.06218 -0.1157 0.7341 0.0631
-8.000 -0.0072 0.06173 0.05561 -0.1214 0.7285 0.0630
-7.750 -0.0231 0.05544 0.04904 -0.1249 0.7241 0.0632
-7.500 -0.0309 0.05031 0.04353 -0.1262 0.7205 0.0635
-7.250 -0.0317 0.04629 0.03915 -0.1264 0.7155 0.0637
-7.000 -0.0274 0.04276 0.03519 -0.1259 0.7101 0.0640
-6.750 -0.0187 0.03945 0.03132 -0.1252 0.7055 0.0645
-6.500 -0.0008 0.03762 0.02920 -0.1246 0.7007 0.0653
-6.250 0.0192 0.03678 0.02832 -0.1241 0.6939 0.0663
-6.000 0.0403 0.03557 0.02691 -0.1236 0.6884 0.0675
-5.500 0.0815 0.03265 0.02335 -0.1224 0.6788 0.0698
-5.250 0.1031 0.03128 0.02163 -0.1218 0.6742 0.0708
-5.000 0.1271 0.03002 0.01998 -0.1214 0.6703 0.0722
-4.750 0.1540 0.02935 0.01924 -0.1215 0.6668 0.0737
-4.500 0.1775 0.02884 0.01866 -0.1210 0.6623 0.0753
-4.250 0.2014 0.02820 0.01787 -0.1206 0.6575 0.0771
-4.000 0.2275 0.02744 0.01687 -0.1203 0.6533 0.0787
-3.750 0.2554 0.02673 0.01596 -0.1203 0.6496 0.0805
-3.500 0.2816 0.02634 0.01555 -0.1202 0.6455 0.0826
-3.250 0.3047 0.02605 0.01523 -0.1195 0.6402 0.0851
-3.000 0.3307 0.02563 0.01468 -0.1192 0.6356 0.0876
-2.750 0.3586 0.02514 0.01411 -0.1192 0.6315 0.0898
-2.500 0.3872 0.02477 0.01369 -0.1194 0.6279 0.0929
-2.250 0.4082 0.02466 0.01361 -0.1184 0.6221 0.0964
-2.000 0.4327 0.02439 0.01332 -0.1178 0.6169 0.0998
-1.750 0.4599 0.02404 0.01296 -0.1177 0.6123 0.1035
-1.500 0.4884 0.02379 0.01259 -0.1178 0.6083 0.1090
-1.250 0.5070 0.02371 0.01266 -0.1165 0.6022 0.1140
-1.000 0.5310 0.02357 0.01250 -0.1159 0.5968 0.1207
-0.750 0.5584 0.02328 0.01218 -0.1159 0.5922 0.1297
-0.500 0.5829 0.02312 0.01206 -0.1154 0.5871 0.1422
-0.250 0.6022 0.02310 0.01219 -0.1142 0.5803 0.1598
0.000 0.6274 0.02275 0.01209 -0.1140 0.5749 0.2205
0.250 0.6546 0.02197 0.01197 -0.1142 0.5708 0.4325
0.500 0.6636 0.02162 0.01253 -0.1108 0.5636 0.6514
0.750 0.7309 0.02130 0.01272 -0.1172 0.5569 0.9918
1.000 0.7614 0.02134 0.01253 -0.1178 0.5521 1.0000
1.250 0.7699 0.02175 0.01293 -0.1148 0.5441 1.0000
1.500 0.7903 0.02187 0.01291 -0.1136 0.5383 1.0000
1.750 0.8089 0.02209 0.01301 -0.1121 0.5324 1.0000
2.000 0.8223 0.02246 0.01333 -0.1099 0.5252 1.0000
2.250 0.8447 0.02257 0.01330 -0.1091 0.5201 1.0000
2.500 0.8586 0.02297 0.01365 -0.1071 0.5133 1.0000
2.750 0.8750 0.02328 0.01388 -0.1054 0.5068 1.0000
3.000 0.8994 0.02334 0.01379 -0.1049 0.5023 1.0000
3.250 0.9078 0.02394 0.01438 -0.1021 0.4950 1.0000
3.500 0.9252 0.02422 0.01458 -0.1006 0.4896 1.0000
3.750 0.9501 0.02433 0.01453 -0.1002 0.4857 1.0000
4.000 0.9581 0.02506 0.01527 -0.0976 0.4794 1.0000
4.250 0.9759 0.02546 0.01560 -0.0963 0.4744 1.0000
4.500 1.0010 0.02560 0.01560 -0.0961 0.4705 1.0000
4.750 1.0140 0.02628 0.01626 -0.0943 0.4652 1.0000
5.000 1.0292 0.02690 0.01685 -0.0929 0.4601 1.0000
5.250 1.0513 0.02724 0.01709 -0.0924 0.4562 1.0000
5.500 1.0805 0.02733 0.01704 -0.0927 0.4531 1.0000
5.750 1.0885 0.02838 0.01815 -0.0907 0.4483 1.0000
6.000 1.1032 0.02915 0.01890 -0.0894 0.4440 1.0000
6.250 1.1246 0.02961 0.01929 -0.0889 0.4403 1.0000
6.500 1.1529 0.02976 0.01934 -0.0892 0.4372 1.0000
6.750 1.1669 0.03063 0.02022 -0.0880 0.4333 1.0000
7.000 1.1749 0.03182 0.02146 -0.0862 0.4290 1.0000
7.250 1.1914 0.03261 0.02225 -0.0853 0.4255 1.0000
7.500 1.2143 0.03308 0.02268 -0.0851 0.4226 1.0000
7.750 1.2430 0.03327 0.02280 -0.0855 0.4201 1.0000
8.000 1.2595 0.03413 0.02367 -0.0847 0.4170 1.0000
8.250 1.2550 0.03612 0.02580 -0.0820 0.4126 1.0000
8.500 1.2637 0.03745 0.02717 -0.0806 0.4089 1.0000
8.750 1.2827 0.03815 0.02787 -0.0801 0.4058 1.0000
9.000 1.3094 0.03844 0.02812 -0.0803 0.4034 1.0000
9.250 1.3418 0.03846 0.02808 -0.0810 0.4015 1.0000
9.500 1.3205 0.04175 0.03158 -0.0774 0.3973 1.0000
9.750 1.2953 0.04569 0.03572 -0.0740 0.3923 1.0000
10.000 1.3028 0.04734 0.03741 -0.0730 0.3888 1.0000
10.250 1.3270 0.04767 0.03774 -0.0729 0.3864 1.0000
10.500 1.3590 0.04745 0.03748 -0.0734 0.3846 1.0000
10.750 1.3950 0.04705 0.03704 -0.0742 0.3831 1.0000
11.000 1.2174 0.06615 0.05674 -0.0658 0.3680 1.0000
11.250 1.2500 0.06532 0.05590 -0.0659 0.3670 1.0000
11.500 1.2862 0.06416 0.05471 -0.0660 0.3661 1.0000
11.750 1.3245 0.06287 0.05341 -0.0663 0.3653 1.0000
12.250 1.0820 0.09969 0.09078 -0.0638 0.3307 1.0000
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Polar data table (+)
Polar graphs
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