GOE 780 AIRFOIL (goe780-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 780 AIRFOIL (goe780-il) Reynolds number: 50,000 Max Cl/Cd: 12.37 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe780-il-50000.txt Download as CSV file: xf-goe780-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 780 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4674 0.11866 0.11190 -0.0313 1.0000 0.2698
-10.500 -0.4684 0.11568 0.10893 -0.0309 1.0000 0.2841
-10.250 -0.4774 0.11319 0.10653 -0.0305 1.0000 0.2989
-10.000 -0.4517 0.10828 0.10158 -0.0286 1.0000 0.3194
-9.750 -0.4657 0.10658 0.10000 -0.0274 1.0000 0.3399
-9.500 -0.4568 0.10342 0.09687 -0.0252 1.0000 0.3673
-9.250 -0.4339 0.09972 0.09316 -0.0224 1.0000 0.4056
-9.000 -0.4389 0.09776 0.09128 -0.0196 1.0000 0.4367
-7.500 -0.4523 0.07964 0.07368 -0.0096 1.0000 0.4956
-7.250 -0.5052 0.07759 0.07191 -0.0071 1.0000 0.4554
-7.000 -0.5506 0.07595 0.07047 -0.0025 1.0000 0.4418
-6.750 -0.5924 0.07444 0.06913 0.0032 1.0000 0.4410
-6.500 -0.6321 0.07310 0.06792 0.0095 1.0000 0.4408
-6.250 -0.6762 0.07120 0.06613 0.0154 1.0000 0.4393
-6.000 -0.7245 0.06751 0.06243 0.0170 1.0000 0.3997
-5.750 -0.7683 0.06373 0.05834 0.0181 1.0000 0.3554
-5.500 -0.7675 0.05661 0.04986 0.0135 1.0000 0.2076
-5.250 -0.7555 0.05227 0.04444 0.0167 1.0000 0.1514
-5.000 -0.7411 0.04893 0.04047 0.0201 1.0000 0.1291
-4.750 -0.7289 0.04642 0.03721 0.0239 1.0000 0.1188
-4.500 -0.7148 0.04375 0.03408 0.0267 1.0000 0.1174
-4.250 -0.1857 0.03142 0.02262 -0.0431 1.0000 1.0000
-4.000 -0.1845 0.03129 0.02221 -0.0400 1.0000 1.0000
-3.750 -0.1824 0.03115 0.02182 -0.0371 1.0000 1.0000
-3.500 -0.1794 0.03103 0.02138 -0.0342 1.0000 1.0000
-3.250 -0.1757 0.03093 0.02106 -0.0313 1.0000 1.0000
-3.000 -0.1713 0.03084 0.02075 -0.0285 1.0000 1.0000
-2.750 -0.1662 0.03076 0.02047 -0.0258 1.0000 1.0000
-2.500 -0.1606 0.03071 0.02023 -0.0231 1.0000 1.0000
-2.250 -0.1544 0.03068 0.02001 -0.0205 1.0000 1.0000
-2.000 -0.1475 0.03067 0.01983 -0.0180 1.0000 1.0000
-1.750 -0.1402 0.03069 0.01968 -0.0155 1.0000 1.0000
-1.500 -0.1324 0.03073 0.01957 -0.0130 1.0000 1.0000
-1.250 -0.1240 0.03079 0.01943 -0.0106 1.0000 1.0000
-1.000 -0.1153 0.03087 0.01938 -0.0083 1.0000 1.0000
-0.750 -0.1062 0.03097 0.01936 -0.0060 1.0000 1.0000
-0.500 -0.0968 0.03109 0.01936 -0.0037 1.0000 1.0000
-0.250 -0.0871 0.03124 0.01941 -0.0015 1.0000 1.0000
0.000 -0.0771 0.03140 0.01948 0.0007 1.0000 1.0000
0.250 -0.0668 0.03158 0.01959 0.0028 1.0000 1.0000
0.500 -0.0562 0.03179 0.01970 0.0049 1.0000 1.0000
0.750 -0.0455 0.03201 0.01986 0.0070 1.0000 1.0000
1.000 -0.0346 0.03225 0.02005 0.0090 1.0000 1.0000
1.250 -0.0234 0.03251 0.02028 0.0109 1.0000 1.0000
1.500 -0.0120 0.03280 0.02054 0.0128 1.0000 1.0000
1.750 -0.0004 0.03311 0.02083 0.0147 1.0000 1.0000
2.000 0.0114 0.03344 0.02116 0.0165 1.0000 1.0000
2.250 0.0233 0.03379 0.02152 0.0182 1.0000 1.0000
2.500 0.0354 0.03417 0.02192 0.0199 1.0000 1.0000
2.750 0.0478 0.03457 0.02235 0.0215 1.0000 1.0000
3.000 0.0603 0.03500 0.02283 0.0231 1.0000 1.0000
3.250 0.0729 0.03546 0.02334 0.0246 1.0000 1.0000
3.500 0.0857 0.03595 0.02394 0.0261 1.0000 1.0000
3.750 0.0986 0.03647 0.02455 0.0275 1.0000 1.0000
4.000 0.1115 0.03702 0.02520 0.0289 1.0000 1.0000
4.250 0.1246 0.03761 0.02590 0.0302 1.0000 1.0000
4.500 0.1378 0.03823 0.02666 0.0314 1.0000 1.0000
4.750 0.1509 0.03888 0.02746 0.0326 1.0000 1.0000
5.000 0.1641 0.03958 0.02839 0.0337 1.0000 1.0000
5.250 0.1773 0.04032 0.02933 0.0348 1.0000 1.0000
5.500 0.1905 0.04111 0.03035 0.0359 1.0000 1.0000
5.750 0.2036 0.04195 0.03144 0.0368 1.0000 1.0000
6.000 0.2166 0.04284 0.03261 0.0378 1.0000 1.0000
7.750 0.8435 0.06820 0.06218 0.0000 0.3179 1.0000
8.000 0.8031 0.07137 0.06536 0.0050 0.3198 1.0000
8.250 0.7637 0.07459 0.06852 0.0099 0.3204 1.0000
8.500 0.7225 0.07827 0.07208 0.0137 0.3203 1.0000
8.750 0.6813 0.08332 0.07696 0.0144 0.3211 1.0000
9.000 0.6410 0.08987 0.08333 0.0120 0.3348 1.0000
9.250 0.5894 0.09907 0.09224 0.0046 0.3997 1.0000
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Polar data table (+)
Polar graphs
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