GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il) Reynolds number: 500,000 Max Cl/Cd: 86.98 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe121-il-500000-n5.txt Download as CSV file: xf-goe121-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 121 (MVA H.1) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3818 0.08839 0.08612 -0.0234 1.0000 0.0149
-8.000 -0.3873 0.08507 0.08285 -0.0236 1.0000 0.0154
-7.750 -0.4033 0.07743 0.07526 -0.0281 1.0000 0.0167
-7.250 -0.3598 0.07268 0.07050 -0.0361 0.9944 0.0175
-7.000 -0.3341 0.06984 0.06764 -0.0411 0.9880 0.0182
-6.750 -0.3076 0.06544 0.06320 -0.0483 0.9784 0.0191
-6.500 -0.2761 0.05880 0.05648 -0.0590 0.9669 0.0204
-6.250 -0.2319 0.04635 0.04380 -0.0774 0.9537 0.0228
-6.000 -0.1960 0.04259 0.03992 -0.0838 0.9450 0.0235
-5.750 -0.1592 0.03984 0.03706 -0.0889 0.9359 0.0242
-5.500 -0.1230 0.03690 0.03397 -0.0937 0.9236 0.0252
-5.250 -0.0776 0.01770 0.01336 -0.1086 0.9133 0.0269
-5.000 -0.0483 0.01617 0.01150 -0.1094 0.9008 0.0276
-4.750 -0.0201 0.01485 0.00985 -0.1099 0.8900 0.0281
-4.500 0.0075 0.01384 0.00858 -0.1100 0.8787 0.0285
-4.250 0.0349 0.01306 0.00758 -0.1099 0.8660 0.0289
-4.000 0.0622 0.01244 0.00676 -0.1098 0.8518 0.0293
-3.750 0.0894 0.01192 0.00605 -0.1095 0.8348 0.0296
-3.500 0.1163 0.01149 0.00544 -0.1092 0.8128 0.0299
-3.250 0.1428 0.01114 0.00489 -0.1088 0.7858 0.0301
-3.000 0.1695 0.01085 0.00439 -0.1084 0.7626 0.0303
-2.500 0.2241 0.01033 0.00359 -0.1079 0.7326 0.0305
-2.250 0.2517 0.01008 0.00325 -0.1077 0.7217 0.0307
-2.000 0.2794 0.00968 0.00275 -0.1076 0.7110 0.0316
-1.750 0.3070 0.00946 0.00244 -0.1074 0.6986 0.0321
-1.500 0.3346 0.00930 0.00219 -0.1072 0.6819 0.0325
-1.250 0.3620 0.00918 0.00199 -0.1070 0.6608 0.0331
-1.000 0.3888 0.00916 0.00181 -0.1066 0.6225 0.0340
-0.750 0.4134 0.00938 0.00167 -0.1059 0.5490 0.0352
-0.500 0.4396 0.00951 0.00162 -0.1055 0.5124 0.0369
-0.250 0.4664 0.00960 0.00159 -0.1052 0.4870 0.0391
0.250 0.5207 0.00965 0.00162 -0.1049 0.4443 0.0761
0.500 0.5477 0.00979 0.00168 -0.1046 0.4209 0.0887
0.750 0.5745 0.00995 0.00175 -0.1044 0.3948 0.0958
1.000 0.6013 0.01012 0.00181 -0.1041 0.3708 0.0998
1.250 0.6281 0.01026 0.00188 -0.1039 0.3527 0.1041
1.500 0.6551 0.01037 0.00196 -0.1037 0.3377 0.1096
1.750 0.6821 0.01048 0.00203 -0.1035 0.3247 0.1134
2.000 0.7091 0.01060 0.00211 -0.1033 0.3114 0.1182
2.250 0.7362 0.01069 0.00219 -0.1031 0.3012 0.1227
2.500 0.7632 0.01080 0.00229 -0.1029 0.2912 0.1254
2.750 0.7902 0.01091 0.00239 -0.1027 0.2804 0.1288
3.000 0.8171 0.01103 0.00251 -0.1025 0.2680 0.1366
3.250 0.8439 0.01109 0.00270 -0.1024 0.2518 0.2049
3.500 0.8703 0.01124 0.00290 -0.1022 0.2276 0.2730
3.750 0.8949 0.01162 0.00318 -0.1019 0.1846 0.3309
4.000 0.9156 0.01060 0.00344 -0.1005 0.1764 1.0000
4.250 0.9420 0.01083 0.00365 -0.1002 0.1702 1.0000
4.500 0.9676 0.01118 0.00391 -0.0998 0.1567 1.0000
4.750 0.9933 0.01148 0.00418 -0.0994 0.1458 1.0000
5.000 1.0191 0.01178 0.00442 -0.0991 0.1331 1.0000
5.250 1.0424 0.01242 0.00481 -0.0984 0.0863 1.0000
5.500 1.0672 0.01284 0.00519 -0.0979 0.0784 1.0000
5.750 1.0927 0.01314 0.00553 -0.0975 0.0721 1.0000
6.000 1.1177 0.01351 0.00591 -0.0970 0.0629 1.0000
6.250 1.1398 0.01429 0.00648 -0.0962 0.0269 1.0000
6.500 1.1639 0.01476 0.00697 -0.0956 0.0217 1.0000
6.750 1.1878 0.01525 0.00751 -0.0949 0.0184 1.0000
7.000 1.2119 0.01568 0.00799 -0.0943 0.0167 1.0000
7.250 1.2354 0.01618 0.00851 -0.0936 0.0149 1.0000
7.500 1.2574 0.01686 0.00924 -0.0927 0.0130 1.0000
7.750 1.2802 0.01739 0.00984 -0.0919 0.0123 1.0000
8.000 1.3026 0.01797 0.01049 -0.0910 0.0115 1.0000
8.250 1.3242 0.01859 0.01118 -0.0901 0.0108 1.0000
8.500 1.3454 0.01923 0.01187 -0.0891 0.0101 1.0000
8.750 1.3654 0.01996 0.01265 -0.0880 0.0094 1.0000
9.000 1.3826 0.02098 0.01374 -0.0865 0.0088 1.0000
9.250 1.4018 0.02170 0.01455 -0.0853 0.0084 1.0000
9.500 1.4193 0.02256 0.01552 -0.0838 0.0081 1.0000
9.750 1.4356 0.02347 0.01653 -0.0822 0.0077 1.0000
10.000 1.4508 0.02442 0.01756 -0.0804 0.0074 1.0000
10.250 1.4648 0.02540 0.01863 -0.0786 0.0072 1.0000
10.500 1.4772 0.02642 0.01973 -0.0765 0.0069 1.0000
10.750 1.4860 0.02746 0.02085 -0.0739 0.0067 1.0000
11.000 1.4928 0.02865 0.02213 -0.0712 0.0065 1.0000
11.250 1.4960 0.03015 0.02372 -0.0682 0.0063 1.0000
11.500 1.4943 0.03216 0.02587 -0.0652 0.0061 1.0000
11.750 1.4999 0.03370 0.02753 -0.0632 0.0060 1.0000
12.000 1.5042 0.03544 0.02940 -0.0613 0.0059 1.0000
12.250 1.5071 0.03742 0.03152 -0.0596 0.0057 1.0000
12.500 1.5086 0.03963 0.03387 -0.0582 0.0056 1.0000
12.750 1.5090 0.04210 0.03648 -0.0570 0.0054 1.0000
13.000 1.5079 0.04487 0.03939 -0.0560 0.0053 1.0000
13.250 1.5057 0.04792 0.04259 -0.0554 0.0052 1.0000
13.500 1.5024 0.05122 0.04603 -0.0551 0.0051 1.0000
13.750 1.4984 0.05475 0.04971 -0.0551 0.0051 1.0000
14.000 1.4932 0.05857 0.05367 -0.0553 0.0050 1.0000
14.250 1.4869 0.06269 0.05793 -0.0559 0.0049 1.0000
14.500 1.4797 0.06712 0.06251 -0.0569 0.0049 1.0000
14.750 1.4715 0.07188 0.06742 -0.0582 0.0048 1.0000
15.000 1.4622 0.07700 0.07268 -0.0598 0.0048 1.0000
15.250 1.4526 0.08236 0.07818 -0.0616 0.0047 1.0000
15.500 1.4421 0.08797 0.08393 -0.0637 0.0047 1.0000
15.750 1.4305 0.09388 0.08999 -0.0660 0.0047 1.0000
16.000 1.4188 0.09999 0.09626 -0.0686 0.0046 1.0000
16.250 1.4063 0.10637 0.10277 -0.0714 0.0046 1.0000
16.500 1.3932 0.11298 0.10952 -0.0744 0.0046 1.0000
16.750 1.3799 0.11979 0.11647 -0.0776 0.0046 1.0000
17.000 1.3656 0.12701 0.12383 -0.0812 0.0046 1.0000
17.250 1.3525 0.13419 0.13115 -0.0850 0.0045 1.0000
17.500 1.3383 0.14180 0.13889 -0.0891 0.0045 1.0000
17.750 1.3228 0.15005 0.14729 -0.0938 0.0045 1.0000
18.000 1.3076 0.15866 0.15602 -0.0989 0.0045 1.0000
18.250 1.2887 0.16881 0.16634 -0.1051 0.0045 1.0000
18.500 1.2631 0.18170 0.17943 -0.1131 0.0046 1.0000
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