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GOE 265 AIRFOIL (goe265-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 265 AIRFOIL (goe265-il)
Reynolds number: 50,000
Max Cl/Cd: 23.03 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe265-il-50000.txt
Download as CSV file: xf-goe265-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 265 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2633   0.12280   0.11611  -0.0167   1.0000   0.0981
  -9.000  -0.2633   0.12298   0.11639  -0.0191   1.0000   0.0993
  -8.750  -0.2672   0.12402   0.11757  -0.0216   1.0000   0.0999
  -8.500  -0.2532   0.11762   0.11122  -0.0215   1.0000   0.1010
  -8.250  -0.2363   0.11132   0.10492  -0.0205   1.0000   0.1036
  -8.000  -0.2284   0.10828   0.10195  -0.0208   1.0000   0.1062
  -7.750  -0.2235   0.10600   0.09977  -0.0213   1.0000   0.1089
  -7.500  -0.2231   0.10463   0.09853  -0.0217   1.0000   0.1117
  -7.250  -0.2279   0.10479   0.09887  -0.0230   1.0000   0.1137
  -7.000  -0.2366   0.10616   0.10043  -0.0248   1.0000   0.1145
  -6.750  -0.2490   0.10777   0.10221  -0.0257   1.0000   0.1148
  -6.500  -0.2469   0.10049   0.09504  -0.0189   1.0000   0.1167
  -6.250  -0.2569   0.09888   0.09355  -0.0153   1.0000   0.1182
  -6.000  -0.2686   0.09801   0.09279  -0.0125   1.0000   0.1196
  -5.750  -0.2784   0.09717   0.09204  -0.0107   1.0000   0.1213
  -5.500  -0.2855   0.09624   0.09119  -0.0098   1.0000   0.1233
  -5.250  -0.2894   0.09531   0.09033  -0.0101   1.0000   0.1257
  -5.000  -0.2862   0.09534   0.09038  -0.0142   1.0000   0.1286
  -4.750  -0.2631   0.09223   0.08725  -0.0207   0.9951   0.1308
  -4.500  -0.2362   0.08696   0.08196  -0.0229   0.9860   0.1361
  -4.250  -0.1818   0.08384   0.07870  -0.0373   0.9735   0.1458
  -4.000  -0.1547   0.07943   0.07428  -0.0398   0.9632   0.1533
  -3.750  -0.1066   0.07593   0.07064  -0.0503   0.9516   0.1621
  -3.500  -0.0518   0.07244   0.06700  -0.0611   0.9408   0.1757
  -3.250  -0.0119   0.06966   0.06410  -0.0679   0.9281   0.1901
  -3.000   0.0282   0.06674   0.06107  -0.0740   0.9160   0.2051
  -2.750   0.0686   0.06313   0.05737  -0.0792   0.9053   0.2213
  -2.500   0.1095   0.05969   0.05388  -0.0837   0.8946   0.2453
  -2.250   0.1430   0.05715   0.05128  -0.0873   0.8818   0.2711
  -1.250   0.2482   0.04624   0.04044  -0.0890   0.8366   0.5075
  -1.000   0.2808   0.04318   0.03740  -0.0890   0.8275   0.5714
  -0.750   0.3123   0.04134   0.03551  -0.0904   0.8150   0.6100
  -0.500   0.3433   0.03970   0.03384  -0.0918   0.8021   0.6381
  -0.250   0.4006   0.03844   0.03233  -0.0993   0.7894   0.6374
   0.000   0.5407   0.04049   0.03286  -0.1252   0.7730   0.3747
   0.250   0.6009   0.04008   0.03163  -0.1297   0.7618   0.2792
   0.500   0.6385   0.03917   0.03037  -0.1306   0.7499   0.2670
   0.750   0.6671   0.03890   0.02986  -0.1306   0.7361   0.2612
   1.000   0.6961   0.03878   0.02946  -0.1306   0.7233   0.2636
   1.250   0.7281   0.03828   0.02872  -0.1304   0.7121   0.2687
   1.500   0.7607   0.03797   0.02807  -0.1301   0.7008   0.2795
   1.750   0.7842   0.03838   0.02834  -0.1296   0.6873   0.2884
   2.000   0.8085   0.03887   0.02866  -0.1290   0.6748   0.2988
   2.250   0.8436   0.03811   0.02773  -0.1281   0.6668   0.3176
   2.500   0.8616   0.03923   0.02883  -0.1274   0.6534   0.3283
   2.750   0.8793   0.04034   0.03001  -0.1267   0.6415   0.3479
   3.000   0.9125   0.03963   0.02935  -0.1256   0.6346   0.3802
   3.250   0.9255   0.04139   0.03134  -0.1253   0.6220   0.4112
   3.500   0.9382   0.04237   0.03322  -0.1245   0.6116   1.0000
   3.750   0.9675   0.04303   0.03350  -0.1235   0.6043   1.0000
   4.000   0.9722   0.04633   0.03670  -0.1233   0.5931   1.0000
   4.250   1.0060   0.04627   0.03637  -0.1221   0.5872   1.0000
   4.500   0.9958   0.05133   0.04149  -0.1224   0.5762   1.0000
   4.750   1.0294   0.05138   0.04139  -0.1213   0.5711   1.0000
   5.000   0.9974   0.05885   0.04898  -0.1223   0.5609   1.0000
   5.250   1.0347   0.05858   0.04861  -0.1211   0.5555   1.0000
   5.500   0.9879   0.06723   0.05736  -0.1219   0.5499   1.0000
   5.750   0.9730   0.07232   0.06247  -0.1220   0.5464   1.0000
   6.000   0.9857   0.07493   0.06506  -0.1217   0.5416   1.0000
   6.250   0.9980   0.07777   0.06791  -0.1215   0.5374   1.0000
   6.500   0.9869   0.08284   0.07301  -0.1219   0.5373   1.0000
   6.750   0.9798   0.08750   0.07771  -0.1223   0.5373   1.0000
   7.000   0.9752   0.09194   0.08218  -0.1227   0.5374   1.0000
   7.250   0.9675   0.09635   0.08663  -0.1229   0.5369   1.0000
   7.500   0.9567   0.10058   0.09091  -0.1229   0.5348   1.0000
   7.750   0.9513   0.10444   0.09481  -0.1228   0.5317   1.0000
   8.000   0.9525   0.10817   0.09858  -0.1230   0.5288   1.0000
   8.250   1.0205   0.10241   0.09276  -0.1165   0.4696   1.0000
   8.500   1.0394   0.10390   0.09430  -0.1151   0.4561   1.0000
   8.750   1.0604   0.10504   0.09549  -0.1135   0.4418   1.0000
   9.250   1.0496   0.11291   0.10348  -0.1130   0.4192   1.0000
   9.500   1.0571   0.11596   0.10662  -0.1124   0.4079   1.0000
   9.750   1.0804   0.11745   0.10818  -0.1110   0.3958   1.0000
  10.000   1.0506   0.12525   0.11603  -0.1133   0.3926   1.0000
  10.250   1.0377   0.13148   0.12232  -0.1149   0.3916   1.0000
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