GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.71 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe121-il-1000000-n5.txt Download as CSV file: xf-goe121-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5106 0.16737 0.16560 0.0072 1.0000 0.0041
-14.000 -0.5063 0.16294 0.16117 0.0056 1.0000 0.0044
-13.750 -0.5064 0.15695 0.15519 0.0038 1.0000 0.0047
-13.500 -0.5007 0.15351 0.15175 0.0024 1.0000 0.0049
-13.250 -0.4936 0.15050 0.14875 0.0011 1.0000 0.0050
-13.000 -0.4868 0.14743 0.14568 -0.0002 1.0000 0.0051
-12.750 -0.4804 0.14422 0.14248 -0.0014 1.0000 0.0053
-7.250 -0.2956 0.02092 0.01807 -0.1060 0.9321 0.0209
-7.000 -0.2667 0.01864 0.01544 -0.1078 0.9173 0.0214
-6.750 -0.2396 0.01737 0.01392 -0.1084 0.9067 0.0217
-6.500 -0.2126 0.01660 0.01298 -0.1086 0.8965 0.0220
-6.250 -0.1858 0.01562 0.01180 -0.1089 0.8865 0.0221
-6.000 -0.1590 0.01478 0.01075 -0.1090 0.8753 0.0222
-5.750 -0.1319 0.01405 0.00984 -0.1090 0.8642 0.0223
-5.500 -0.1046 0.01342 0.00905 -0.1091 0.8537 0.0224
-5.250 -0.0780 0.01125 0.00647 -0.1096 0.8418 0.0235
-5.000 -0.0511 0.01070 0.00576 -0.1095 0.8219 0.0239
-4.750 -0.0248 0.01038 0.00523 -0.1091 0.7877 0.0243
-4.500 0.0017 0.01013 0.00479 -0.1088 0.7585 0.0247
-4.250 0.0290 0.00989 0.00440 -0.1086 0.7390 0.0250
-4.000 0.0565 0.00965 0.00404 -0.1084 0.7241 0.0254
-3.750 0.0842 0.00941 0.00369 -0.1083 0.7124 0.0257
-3.500 0.1121 0.00917 0.00336 -0.1082 0.7018 0.0259
-3.250 0.1401 0.00894 0.00305 -0.1082 0.6922 0.0262
-3.000 0.1681 0.00874 0.00276 -0.1081 0.6809 0.0264
-2.750 0.1958 0.00857 0.00250 -0.1080 0.6622 0.0266
-2.500 0.2231 0.00849 0.00226 -0.1077 0.6272 0.0268
-2.250 0.2484 0.00869 0.00209 -0.1072 0.5398 0.0270
-2.000 0.2756 0.00869 0.00193 -0.1070 0.5103 0.0272
-1.750 0.3032 0.00866 0.00181 -0.1069 0.4919 0.0275
-1.500 0.3309 0.00863 0.00169 -0.1068 0.4747 0.0280
-1.250 0.3585 0.00863 0.00159 -0.1066 0.4514 0.0283
-1.000 0.3855 0.00872 0.00150 -0.1064 0.4131 0.0286
-0.750 0.4125 0.00884 0.00145 -0.1062 0.3741 0.0289
-0.500 0.4396 0.00893 0.00141 -0.1060 0.3470 0.0295
-0.250 0.4670 0.00901 0.00140 -0.1059 0.3272 0.0301
0.000 0.4946 0.00906 0.00139 -0.1057 0.3141 0.0306
0.250 0.5223 0.00909 0.00136 -0.1056 0.3035 0.0330
0.500 0.5499 0.00914 0.00137 -0.1055 0.2926 0.0371
1.000 0.6051 0.00917 0.00149 -0.1053 0.2697 0.0859
1.250 0.6323 0.00930 0.00155 -0.1051 0.2535 0.0893
1.500 0.6575 0.00973 0.00172 -0.1047 0.1899 0.0928
1.750 0.6841 0.00995 0.00186 -0.1044 0.1692 0.0961
2.000 0.7113 0.01006 0.00196 -0.1043 0.1621 0.0991
2.250 0.7386 0.01017 0.00206 -0.1041 0.1580 0.1019
2.500 0.7659 0.01026 0.00215 -0.1040 0.1541 0.1073
2.750 0.7931 0.01036 0.00226 -0.1038 0.1499 0.1099
3.000 0.8205 0.01043 0.00235 -0.1036 0.1478 0.1116
3.250 0.8478 0.01051 0.00245 -0.1035 0.1452 0.1134
3.500 0.8749 0.01062 0.00257 -0.1033 0.1415 0.1153
3.750 0.9018 0.01077 0.00270 -0.1031 0.1358 0.1197
4.000 0.9262 0.01127 0.00299 -0.1026 0.0859 0.1280
4.250 0.9527 0.01139 0.00327 -0.1024 0.0788 0.2250
4.500 0.9795 0.01149 0.00348 -0.1023 0.0760 0.2728
4.750 1.0063 0.01157 0.00370 -0.1021 0.0738 0.3314
5.000 1.0282 0.01060 0.00403 -0.1012 0.0700 1.0000
5.250 1.0543 0.01087 0.00428 -0.1008 0.0652 1.0000
5.500 1.0807 0.01106 0.00447 -0.1006 0.0589 1.0000
5.750 1.1042 0.01169 0.00491 -0.0999 0.0255 1.0000
6.000 1.1294 0.01204 0.00524 -0.0994 0.0198 1.0000
6.250 1.1550 0.01234 0.00555 -0.0990 0.0171 1.0000
6.500 1.1800 0.01270 0.00589 -0.0986 0.0144 1.0000
6.750 1.2049 0.01305 0.00626 -0.0981 0.0126 1.0000
7.000 1.2300 0.01337 0.00660 -0.0976 0.0117 1.0000
7.250 1.2546 0.01373 0.00698 -0.0971 0.0107 1.0000
7.500 1.2788 0.01415 0.00739 -0.0965 0.0097 1.0000
7.750 1.3025 0.01461 0.00788 -0.0959 0.0088 1.0000
8.000 1.3267 0.01498 0.00830 -0.0953 0.0083 1.0000
8.250 1.3504 0.01540 0.00874 -0.0947 0.0078 1.0000
8.500 1.3737 0.01584 0.00921 -0.0940 0.0073 1.0000
8.750 1.3964 0.01632 0.00972 -0.0933 0.0069 1.0000
9.000 1.4182 0.01691 0.01034 -0.0924 0.0064 1.0000
9.250 1.4394 0.01754 0.01104 -0.0914 0.0061 1.0000
9.500 1.4610 0.01808 0.01163 -0.0905 0.0059 1.0000
9.750 1.4820 0.01865 0.01226 -0.0895 0.0057 1.0000
10.000 1.5026 0.01922 0.01289 -0.0885 0.0054 1.0000
10.250 1.5228 0.01981 0.01352 -0.0874 0.0051 1.0000
10.500 1.5424 0.02041 0.01417 -0.0863 0.0049 1.0000
10.750 1.5611 0.02106 0.01487 -0.0850 0.0047 1.0000
11.000 1.5782 0.02181 0.01568 -0.0836 0.0045 1.0000
11.250 1.5927 0.02274 0.01668 -0.0818 0.0043 1.0000
11.500 1.6042 0.02382 0.01786 -0.0795 0.0041 1.0000
11.750 1.6162 0.02466 0.01878 -0.0773 0.0041 1.0000
12.000 1.6252 0.02557 0.01977 -0.0746 0.0040 1.0000
12.250 1.6327 0.02660 0.02089 -0.0719 0.0039 1.0000
12.500 1.6392 0.02774 0.02214 -0.0693 0.0038 1.0000
12.750 1.6447 0.02904 0.02354 -0.0669 0.0038 1.0000
13.000 1.6492 0.03052 0.02511 -0.0646 0.0037 1.0000
13.250 1.6525 0.03220 0.02692 -0.0626 0.0036 1.0000
13.500 1.6549 0.03408 0.02891 -0.0608 0.0036 1.0000
13.750 1.6567 0.03614 0.03107 -0.0593 0.0035 1.0000
14.000 1.6572 0.03847 0.03352 -0.0581 0.0034 1.0000
14.250 1.6565 0.04107 0.03623 -0.0572 0.0034 1.0000
14.500 1.6550 0.04395 0.03922 -0.0566 0.0033 1.0000
14.750 1.6519 0.04718 0.04257 -0.0563 0.0033 1.0000
15.000 1.6466 0.05080 0.04631 -0.0563 0.0032 1.0000
15.250 1.6403 0.05474 0.05037 -0.0567 0.0032 1.0000
15.500 1.6325 0.05907 0.05482 -0.0575 0.0032 1.0000
15.750 1.6225 0.06395 0.05984 -0.0587 0.0031 1.0000
16.000 1.6122 0.06916 0.06517 -0.0602 0.0031 1.0000
16.250 1.5997 0.07485 0.07099 -0.0621 0.0031 1.0000
16.500 1.5856 0.08089 0.07716 -0.0642 0.0031 1.0000
16.750 1.5699 0.08731 0.08371 -0.0666 0.0031 1.0000
17.000 1.5527 0.09408 0.09062 -0.0691 0.0031 1.0000
17.250 1.5366 0.10077 0.09742 -0.0717 0.0031 1.0000
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