GOE 370 AIRFOIL (goe370-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 370 AIRFOIL (goe370-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.46 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe370-il-1000000-n5.txt Download as CSV file: xf-goe370-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 370 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2523 0.12081 0.11928 -0.0309 1.0000 0.0034
-11.250 -0.2486 0.11801 0.11647 -0.0312 1.0000 0.0035
-11.000 -0.3496 0.12845 0.12678 -0.0239 1.0000 0.0032
-10.750 -0.3439 0.12561 0.12394 -0.0246 1.0000 0.0032
-10.500 -0.3384 0.12293 0.12128 -0.0252 1.0000 0.0033
-10.250 -0.3332 0.12006 0.11842 -0.0259 1.0000 0.0033
-10.000 -0.3281 0.11730 0.11565 -0.0264 1.0000 0.0034
-9.750 -0.3231 0.11459 0.11295 -0.0269 1.0000 0.0034
-9.500 -0.3184 0.11190 0.11028 -0.0273 1.0000 0.0036
-9.250 -0.3129 0.10901 0.10741 -0.0281 0.9999 0.0036
-9.000 -0.2980 0.10533 0.10372 -0.0316 0.9985 0.0037
-8.750 -0.2868 0.10189 0.10029 -0.0340 0.9934 0.0037
-8.500 -0.2748 0.09856 0.09696 -0.0367 0.9867 0.0040
-8.250 -0.1184 0.06817 0.06642 -0.0650 0.9056 0.0028
-7.750 -0.2133 0.08489 0.08325 -0.0535 0.9547 0.0028
-7.500 -0.1753 0.07938 0.07769 -0.0644 0.9396 0.0027
-7.250 -0.1423 0.07438 0.07255 -0.0740 0.9058 0.0026
-7.000 -0.1302 0.07139 0.06938 -0.0769 0.8656 0.0025
-6.750 -0.1217 0.06859 0.06646 -0.0786 0.8400 0.0025
-6.500 -0.1114 0.06532 0.06312 -0.0809 0.8221 0.0026
-6.250 -0.0988 0.06126 0.05900 -0.0842 0.8088 0.0029
-6.000 -0.0828 0.05746 0.05514 -0.0877 0.7976 0.0030
-5.750 -0.0644 0.05340 0.05101 -0.0918 0.7868 0.0030
-5.500 -0.0436 0.05127 0.04879 -0.0944 0.7773 0.0034
-5.000 0.0180 0.01435 0.01035 -0.1200 0.7640 0.0035
-4.750 0.0423 0.01216 0.00775 -0.1200 0.7586 0.0037
-4.500 0.0680 0.01090 0.00616 -0.1198 0.7535 0.0039
-4.250 0.0940 0.01007 0.00509 -0.1195 0.7486 0.0043
-4.000 0.1205 0.00945 0.00427 -0.1192 0.7443 0.0047
-3.750 0.1473 0.00896 0.00360 -0.1190 0.7396 0.0051
-3.500 0.1738 0.00843 0.00290 -0.1187 0.7348 0.0062
-3.250 0.2006 0.00813 0.00250 -0.1185 0.7304 0.0076
-3.000 0.2276 0.00784 0.00212 -0.1182 0.7255 0.0103
-2.750 0.2546 0.00770 0.00201 -0.1180 0.7208 0.0153
-2.500 0.2821 0.00780 0.00213 -0.1179 0.7167 0.0215
-2.250 0.3098 0.00795 0.00228 -0.1179 0.7122 0.0244
-2.000 0.3373 0.00808 0.00238 -0.1178 0.7075 0.0253
-1.750 0.3646 0.00819 0.00246 -0.1177 0.7030 0.0258
-1.500 0.3911 0.00772 0.00190 -0.1174 0.6980 0.0271
-1.250 0.4177 0.00751 0.00163 -0.1172 0.6924 0.0278
-1.000 0.4446 0.00737 0.00143 -0.1169 0.6874 0.0276
-0.750 0.4717 0.00724 0.00126 -0.1167 0.6818 0.0274
-0.500 0.4983 0.00716 0.00112 -0.1165 0.6755 0.0273
-0.250 0.5251 0.00706 0.00099 -0.1162 0.6662 0.0272
0.000 0.5515 0.00702 0.00088 -0.1159 0.6530 0.0273
0.250 0.5774 0.00701 0.00078 -0.1155 0.6346 0.0276
0.500 0.6032 0.00703 0.00070 -0.1150 0.6122 0.0286
0.750 0.6284 0.00710 0.00067 -0.1145 0.5864 0.0323
1.000 0.6538 0.00718 0.00069 -0.1140 0.5648 0.0414
1.250 0.6794 0.00720 0.00074 -0.1136 0.5496 0.0741
1.500 0.7056 0.00723 0.00080 -0.1134 0.5392 0.0926
1.750 0.7318 0.00726 0.00088 -0.1131 0.5311 0.1175
2.000 0.7582 0.00732 0.00095 -0.1129 0.5229 0.1293
2.250 0.7845 0.00738 0.00103 -0.1126 0.5147 0.1366
2.500 0.8107 0.00746 0.00112 -0.1123 0.5069 0.1420
2.750 0.8372 0.00751 0.00120 -0.1121 0.5005 0.1479
3.000 0.8635 0.00757 0.00131 -0.1119 0.4937 0.1623
3.250 0.8883 0.00756 0.00151 -0.1114 0.4776 0.2762
3.500 0.9115 0.00763 0.00172 -0.1107 0.4407 0.4195
4.000 0.9616 0.00818 0.00255 -0.1110 0.2632 1.0000
4.500 0.9893 0.01065 0.00389 -0.1064 0.0195 1.0000
4.750 1.0127 0.01098 0.00419 -0.1056 0.0104 1.0000
5.000 1.0365 0.01126 0.00450 -0.1049 0.0082 1.0000
5.250 1.0594 0.01163 0.00488 -0.1040 0.0061 1.0000
5.500 1.0824 0.01197 0.00527 -0.1032 0.0051 1.0000
5.750 1.1051 0.01234 0.00567 -0.1023 0.0044 1.0000
6.000 1.1270 0.01279 0.00615 -0.1013 0.0038 1.0000
6.250 1.1473 0.01340 0.00684 -0.1000 0.0034 1.0000
6.500 1.1679 0.01396 0.00748 -0.0987 0.0031 1.0000
6.750 1.1877 0.01457 0.00816 -0.0973 0.0028 1.0000
7.000 1.2083 0.01507 0.00873 -0.0962 0.0025 1.0000
7.250 1.2293 0.01550 0.00918 -0.0952 0.0022 1.0000
7.500 1.2459 0.01633 0.01009 -0.0933 0.0021 1.0000
7.750 1.2586 0.01748 0.01137 -0.0908 0.0019 1.0000
8.000 1.2758 0.01820 0.01218 -0.0891 0.0018 1.0000
8.250 1.2904 0.01917 0.01326 -0.0870 0.0017 1.0000
8.500 1.3024 0.02040 0.01462 -0.0844 0.0016 1.0000
8.750 1.3144 0.02173 0.01610 -0.0819 0.0014 1.0000
9.000 1.3250 0.02341 0.01795 -0.0791 0.0013 1.0000
9.250 1.3375 0.02548 0.02023 -0.0768 0.0012 1.0000
9.500 1.3538 0.02960 0.02471 -0.0751 0.0012 1.0000
9.750 1.3577 0.04083 0.03675 -0.0707 0.0012 1.0000
10.000 1.3545 0.04565 0.04192 -0.0665 0.0013 1.0000
10.250 1.3470 0.04998 0.04655 -0.0621 0.0013 1.0000
10.500 1.3345 0.05311 0.04988 -0.0572 0.0014 1.0000
10.750 1.3165 0.05644 0.05341 -0.0523 0.0014 1.0000
11.000 1.3001 0.05971 0.05685 -0.0487 0.0014 1.0000
11.250 1.2834 0.06316 0.06047 -0.0460 0.0014 1.0000
11.500 1.2644 0.06720 0.06467 -0.0442 0.0014 1.0000
11.750 1.2457 0.07154 0.06916 -0.0434 0.0014 1.0000
12.000 1.2258 0.07645 0.07421 -0.0436 0.0014 1.0000
12.250 1.2052 0.08192 0.07982 -0.0447 0.0014 1.0000
12.500 1.1858 0.08780 0.08583 -0.0467 0.0014 1.0000
12.750 1.1643 0.09464 0.09279 -0.0499 0.0015 1.0000
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Polar data table (+)
Polar graphs
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