GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il) Reynolds number: 50,000 Max Cl/Cd: 41.19 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe124-il-50000-n5.txt Download as CSV file: xf-goe124-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 124 (MVA H.4) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2975 0.11056 0.10377 -0.0276 1.0000 0.0853
-8.250 -0.3032 0.11014 0.10349 -0.0299 1.0000 0.0864
-8.000 -0.3071 0.10959 0.10309 -0.0336 1.0000 0.0870
-7.750 -0.2927 0.10310 0.09663 -0.0299 1.0000 0.0889
-7.500 -0.2839 0.09958 0.09315 -0.0284 1.0000 0.0925
-7.250 -0.2843 0.09763 0.09132 -0.0281 1.0000 0.0963
-7.000 -0.2910 0.09669 0.09052 -0.0286 1.0000 0.0997
-6.750 -0.3022 0.09688 0.09085 -0.0309 1.0000 0.1015
-6.500 -0.3093 0.09680 0.09087 -0.0342 1.0000 0.1022
-6.250 -0.3102 0.09201 0.08617 -0.0265 1.0000 0.1044
-6.000 -0.2866 0.08789 0.08202 -0.0295 0.9920 0.1100
-5.750 -0.2465 0.08432 0.07832 -0.0451 0.9787 0.1178
-5.500 -0.2275 0.07975 0.07375 -0.0439 0.9724 0.1224
-5.250 -0.1898 0.07599 0.06987 -0.0547 0.9620 0.1338
-5.000 -0.1551 0.07281 0.06657 -0.0627 0.9516 0.1480
-4.750 -0.1337 0.06875 0.06254 -0.0621 0.9453 0.1563
-4.500 -0.1017 0.06528 0.05898 -0.0678 0.9357 0.1684
-4.250 -0.0674 0.06192 0.05552 -0.0734 0.9276 0.1832
-4.000 -0.0350 0.05880 0.05232 -0.0779 0.9190 0.1994
-3.750 -0.0011 0.05613 0.04952 -0.0832 0.9097 0.2259
-3.250 0.1167 0.04724 0.03952 -0.1039 0.8942 0.1315
-3.000 0.1598 0.04294 0.03490 -0.1082 0.8871 0.0973
-2.750 0.2038 0.03993 0.03130 -0.1126 0.8786 0.0854
-2.500 0.2403 0.03758 0.02870 -0.1152 0.8712 0.0828
-2.250 0.2743 0.03576 0.02654 -0.1172 0.8618 0.0828
-2.000 0.3124 0.03393 0.02433 -0.1195 0.8548 0.0828
-1.750 0.3438 0.03251 0.02258 -0.1205 0.8448 0.0813
-1.500 0.3797 0.03103 0.02073 -0.1218 0.8376 0.0798
-1.250 0.4098 0.02997 0.01937 -0.1222 0.8274 0.0789
-1.000 0.4406 0.02902 0.01812 -0.1225 0.8182 0.0785
-0.750 0.4723 0.02811 0.01691 -0.1226 0.8091 0.0785
-0.500 0.4998 0.02748 0.01608 -0.1222 0.7973 0.0803
-0.250 0.5283 0.02691 0.01526 -0.1216 0.7863 0.0836
0.000 0.5585 0.02629 0.01437 -0.1209 0.7766 0.0860
0.500 0.6114 0.02546 0.01332 -0.1194 0.7535 0.0892
0.750 0.6403 0.02500 0.01276 -0.1189 0.7448 0.0922
1.000 0.6663 0.02488 0.01259 -0.1184 0.7331 0.0962
1.250 0.6932 0.02476 0.01242 -0.1179 0.7227 0.1037
1.500 0.7221 0.02446 0.01216 -0.1176 0.7139 0.1200
1.750 0.7488 0.02424 0.01230 -0.1175 0.7023 0.1764
2.250 0.7960 0.02299 0.01218 -0.1146 0.6828 1.0000
2.500 0.8211 0.02337 0.01241 -0.1140 0.6708 1.0000
2.750 0.8470 0.02370 0.01260 -0.1135 0.6597 1.0000
3.000 0.8743 0.02389 0.01265 -0.1129 0.6501 1.0000
3.250 0.8995 0.02427 0.01299 -0.1123 0.6384 1.0000
3.500 0.9245 0.02467 0.01336 -0.1118 0.6266 1.0000
3.750 0.9505 0.02499 0.01363 -0.1112 0.6160 1.0000
4.000 0.9769 0.02529 0.01391 -0.1106 0.6057 1.0000
4.250 1.0010 0.02581 0.01447 -0.1101 0.5938 1.0000
4.500 1.0260 0.02627 0.01494 -0.1095 0.5830 1.0000
4.750 1.0529 0.02654 0.01522 -0.1090 0.5738 1.0000
5.000 1.0760 0.02718 0.01596 -0.1084 0.5620 1.0000
5.250 1.1003 0.02777 0.01662 -0.1079 0.5518 1.0000
5.500 1.1267 0.02815 0.01706 -0.1074 0.5434 1.0000
5.750 1.1489 0.02891 0.01795 -0.1068 0.5322 1.0000
6.000 1.1726 0.02942 0.01856 -0.1060 0.5215 1.0000
6.250 1.1979 0.02966 0.01884 -0.1052 0.5106 1.0000
6.500 1.2206 0.03003 0.01934 -0.1042 0.4976 1.0000
6.750 1.2422 0.03044 0.01986 -0.1030 0.4835 1.0000
7.000 1.2634 0.03084 0.02036 -0.1018 0.4692 1.0000
7.250 1.2842 0.03125 0.02092 -0.1006 0.4548 1.0000
7.500 1.3045 0.03167 0.02145 -0.0992 0.4398 1.0000
7.750 1.3242 0.03219 0.02212 -0.0979 0.4255 1.0000
8.000 1.3434 0.03281 0.02289 -0.0966 0.4118 1.0000
8.250 1.3617 0.03343 0.02370 -0.0951 0.3972 1.0000
8.500 1.3787 0.03408 0.02450 -0.0935 0.3812 1.0000
8.750 1.3942 0.03479 0.02533 -0.0917 0.3637 1.0000
9.000 1.4083 0.03555 0.02619 -0.0897 0.3453 1.0000
9.250 1.4173 0.03667 0.02745 -0.0874 0.3248 1.0000
9.500 1.4233 0.03793 0.02887 -0.0848 0.3028 1.0000
9.750 1.4268 0.03936 0.03037 -0.0821 0.2807 1.0000
10.000 1.4252 0.04111 0.03224 -0.0791 0.2588 1.0000
10.250 1.4241 0.04301 0.03414 -0.0766 0.2386 1.0000
10.500 1.4229 0.04525 0.03642 -0.0745 0.2197 1.0000
10.750 1.4216 0.04764 0.03880 -0.0727 0.2042 1.0000
11.000 1.4195 0.05025 0.04138 -0.0711 0.1909 1.0000
11.250 1.4163 0.05310 0.04417 -0.0698 0.1787 1.0000
11.500 1.4114 0.05622 0.04723 -0.0687 0.1666 1.0000
12.000 1.3968 0.06341 0.05442 -0.0674 0.1427 1.0000
12.250 1.3886 0.06740 0.05850 -0.0673 0.1315 1.0000
12.500 1.3806 0.07144 0.06259 -0.0673 0.1217 1.0000
12.750 1.3737 0.07536 0.06655 -0.0672 0.1132 1.0000
13.000 1.3671 0.07957 0.07097 -0.0674 0.1046 1.0000
13.250 1.3601 0.08364 0.07503 -0.0676 0.0970 1.0000
13.500 1.3522 0.08829 0.07994 -0.0683 0.0888 1.0000
13.750 1.3454 0.09270 0.08442 -0.0689 0.0820 1.0000
14.000 1.3385 0.09737 0.08925 -0.0698 0.0753 1.0000
14.250 1.3324 0.10195 0.09392 -0.0708 0.0699 1.0000
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Polar data table (+)
Polar graphs
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