GOE 394 AIRFOIL (goe394-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 394 AIRFOIL (goe394-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.61 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe394-il-1000000-n5.txt Download as CSV file: xf-goe394-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 394 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4031 0.12221 0.11972 -0.0026 0.7458 0.0052
-10.250 -0.3974 0.11859 0.11609 -0.0042 0.7427 0.0054
-9.750 -0.3911 0.10982 0.10730 -0.0079 0.7378 0.0061
-7.750 -0.3170 0.01748 0.01343 -0.1106 0.7217 0.0163
-7.500 -0.2893 0.01737 0.01335 -0.1105 0.7203 0.0169
-7.250 -0.2614 0.01773 0.01377 -0.1102 0.7188 0.0174
-7.000 -0.2336 0.01801 0.01409 -0.1099 0.7174 0.0180
-6.750 -0.2058 0.01710 0.01306 -0.1104 0.7160 0.0188
-6.500 -0.1780 0.01594 0.01173 -0.1109 0.7143 0.0195
-6.250 -0.1502 0.01520 0.01084 -0.1112 0.7119 0.0201
-5.750 -0.0942 0.01431 0.00973 -0.1115 0.7064 0.0210
-5.500 -0.0661 0.01400 0.00935 -0.1115 0.7039 0.0213
-5.250 -0.0379 0.01369 0.00895 -0.1116 0.7012 0.0214
-5.000 -0.0100 0.01183 0.00674 -0.1123 0.6988 0.0227
-4.750 0.0181 0.01138 0.00619 -0.1124 0.6963 0.0232
-4.500 0.0463 0.01099 0.00569 -0.1124 0.6941 0.0236
-4.250 0.0746 0.01067 0.00531 -0.1125 0.6923 0.0242
-4.000 0.1030 0.01033 0.00491 -0.1125 0.6902 0.0247
-3.750 0.1314 0.00996 0.00445 -0.1125 0.6880 0.0251
-3.500 0.1598 0.00963 0.00403 -0.1125 0.6858 0.0255
-3.250 0.1882 0.00932 0.00364 -0.1125 0.6834 0.0259
-3.000 0.2166 0.00905 0.00329 -0.1125 0.6808 0.0261
-2.750 0.2450 0.00879 0.00296 -0.1125 0.6781 0.0264
-2.500 0.2735 0.00855 0.00267 -0.1124 0.6755 0.0266
-2.250 0.3020 0.00833 0.00241 -0.1124 0.6722 0.0269
-2.000 0.3304 0.00814 0.00217 -0.1124 0.6685 0.0271
-1.750 0.3588 0.00799 0.00196 -0.1123 0.6649 0.0274
-1.500 0.3873 0.00785 0.00181 -0.1123 0.6616 0.0279
-1.250 0.4158 0.00770 0.00165 -0.1123 0.6573 0.0282
-1.000 0.4442 0.00759 0.00150 -0.1122 0.6525 0.0285
-0.750 0.4726 0.00750 0.00139 -0.1121 0.6476 0.0288
-0.500 0.5010 0.00741 0.00129 -0.1121 0.6406 0.0291
-0.250 0.5293 0.00733 0.00117 -0.1120 0.6325 0.0302
0.000 0.5576 0.00726 0.00107 -0.1120 0.6198 0.0321
0.250 0.5855 0.00727 0.00098 -0.1119 0.5914 0.0342
0.500 0.6124 0.00747 0.00097 -0.1116 0.5421 0.0367
1.000 0.6670 0.00771 0.00113 -0.1114 0.4901 0.0745
1.250 0.6945 0.00788 0.00124 -0.1113 0.4705 0.0812
1.500 0.7220 0.00802 0.00132 -0.1112 0.4527 0.0839
1.750 0.7495 0.00815 0.00141 -0.1111 0.4371 0.0869
2.000 0.7770 0.00828 0.00151 -0.1110 0.4239 0.0906
2.250 0.8046 0.00838 0.00159 -0.1109 0.4138 0.0930
2.500 0.8322 0.00848 0.00167 -0.1108 0.4028 0.0945
2.750 0.8597 0.00860 0.00177 -0.1107 0.3924 0.0960
3.000 0.8871 0.00869 0.00185 -0.1106 0.3836 0.0980
3.250 0.9146 0.00876 0.00192 -0.1105 0.3750 0.0996
3.500 0.9419 0.00888 0.00202 -0.1104 0.3643 0.1009
3.750 0.9693 0.00897 0.00212 -0.1103 0.3551 0.1023
4.000 0.9965 0.00908 0.00223 -0.1102 0.3456 0.1038
4.250 1.0234 0.00924 0.00237 -0.1101 0.3323 0.1053
4.500 1.0502 0.00942 0.00251 -0.1099 0.3179 0.1069
4.750 1.0769 0.00959 0.00267 -0.1097 0.3054 0.1085
5.000 1.1033 0.00980 0.00285 -0.1095 0.2893 0.1103
5.250 1.1295 0.01003 0.00304 -0.1093 0.2714 0.1139
5.500 1.1538 0.01053 0.00336 -0.1089 0.2313 0.1176
6.000 1.1972 0.01225 0.00448 -0.1075 0.1114 0.1425
6.500 1.2458 0.01175 0.00531 -0.1068 0.0906 1.0000
6.750 1.2707 0.01211 0.00562 -0.1064 0.0799 1.0000
7.000 1.2946 0.01257 0.00600 -0.1060 0.0636 1.0000
7.250 1.3165 0.01330 0.00655 -0.1052 0.0373 1.0000
7.500 1.3389 0.01392 0.00709 -0.1045 0.0232 1.0000
7.750 1.3617 0.01447 0.00759 -0.1038 0.0160 1.0000
8.000 1.3849 0.01494 0.00807 -0.1032 0.0127 1.0000
8.250 1.4081 0.01537 0.00853 -0.1026 0.0112 1.0000
8.500 1.4305 0.01588 0.00904 -0.1019 0.0098 1.0000
8.750 1.4528 0.01638 0.00957 -0.1011 0.0089 1.0000
9.000 1.4750 0.01684 0.01008 -0.1004 0.0083 1.0000
9.250 1.4966 0.01735 0.01062 -0.0996 0.0076 1.0000
9.500 1.5172 0.01793 0.01123 -0.0987 0.0070 1.0000
9.750 1.5366 0.01861 0.01195 -0.0976 0.0063 1.0000
10.000 1.5567 0.01915 0.01254 -0.0966 0.0060 1.0000
10.250 1.5758 0.01976 0.01320 -0.0955 0.0057 1.0000
10.500 1.5940 0.02041 0.01390 -0.0942 0.0054 1.0000
10.750 1.6110 0.02110 0.01464 -0.0929 0.0051 1.0000
11.000 1.6264 0.02185 0.01545 -0.0913 0.0049 1.0000
11.250 1.6377 0.02268 0.01634 -0.0891 0.0046 1.0000
11.500 1.6460 0.02374 0.01747 -0.0866 0.0044 1.0000
11.750 1.6552 0.02480 0.01861 -0.0845 0.0043 1.0000
12.000 1.6649 0.02586 0.01975 -0.0826 0.0042 1.0000
12.250 1.6739 0.02705 0.02102 -0.0808 0.0041 1.0000
12.500 1.6821 0.02836 0.02242 -0.0791 0.0040 1.0000
12.750 1.6900 0.02977 0.02391 -0.0776 0.0038 1.0000
13.000 1.6971 0.03132 0.02554 -0.0762 0.0037 1.0000
13.250 1.7035 0.03300 0.02732 -0.0750 0.0036 1.0000
13.500 1.7096 0.03477 0.02917 -0.0738 0.0035 1.0000
13.750 1.7147 0.03668 0.03116 -0.0728 0.0034 1.0000
14.000 1.7188 0.03875 0.03332 -0.0718 0.0033 1.0000
14.250 1.7208 0.04106 0.03572 -0.0708 0.0032 1.0000
14.500 1.7213 0.04359 0.03834 -0.0699 0.0031 1.0000
14.750 1.7199 0.04637 0.04122 -0.0691 0.0030 1.0000
15.000 1.7158 0.04951 0.04446 -0.0684 0.0030 1.0000
15.250 1.7093 0.05302 0.04809 -0.0678 0.0029 1.0000
15.500 1.7001 0.05700 0.05220 -0.0675 0.0028 1.0000
15.750 1.6915 0.06113 0.05646 -0.0675 0.0028 1.0000
16.000 1.6851 0.06518 0.06063 -0.0678 0.0028 1.0000
16.250 1.6782 0.06951 0.06507 -0.0684 0.0028 1.0000
16.500 1.6695 0.07427 0.06996 -0.0693 0.0027 1.0000
16.750 1.6604 0.07926 0.07508 -0.0705 0.0027 1.0000
17.000 1.6498 0.08463 0.08057 -0.0720 0.0027 1.0000
17.250 1.6382 0.09020 0.08627 -0.0736 0.0027 1.0000
17.500 1.6252 0.09609 0.09229 -0.0754 0.0027 1.0000
17.750 1.6115 0.10219 0.09852 -0.0775 0.0027 1.0000
18.000 1.5969 0.10853 0.10498 -0.0797 0.0026 1.0000
18.250 1.5818 0.11500 0.11159 -0.0822 0.0026 1.0000
18.500 1.5670 0.12159 0.11830 -0.0848 0.0026 1.0000
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