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GOE 400 AIRFOIL (goe400-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 400 AIRFOIL (goe400-il)
Reynolds number: 500,000
Max Cl/Cd: 88.77 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe400-il-500000-n5.txt
Download as CSV file: xf-goe400-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 400 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4329   0.10339   0.10119   0.0024   1.0000   0.0103
  -8.750  -0.4308   0.09877   0.09659   0.0000   1.0000   0.0108
  -8.500  -0.4320   0.09326   0.09110  -0.0030   1.0000   0.0113
  -8.250  -0.4222   0.09105   0.08891  -0.0044   1.0000   0.0116
  -8.000  -0.4122   0.08884   0.08671  -0.0059   1.0000   0.0120
  -7.750  -0.4023   0.08635   0.08425  -0.0077   1.0000   0.0124
  -7.500  -0.3912   0.08292   0.08083  -0.0111   1.0000   0.0130
  -7.250  -0.3797   0.07822   0.07613  -0.0162   1.0000   0.0138
  -7.000  -0.3590   0.06895   0.06682  -0.0289   0.9682   0.0153
  -6.750  -0.3326   0.06677   0.06458  -0.0329   0.9368   0.0158
  -6.500  -0.3125   0.06469   0.06240  -0.0352   0.8984   0.0164
  -6.250  -0.2922   0.06133   0.05888  -0.0390   0.8599   0.0174
  -6.000  -0.2576   0.04897   0.04621  -0.0548   0.8316   0.0204
  -5.750  -0.2336   0.04744   0.04451  -0.0566   0.8023   0.0209
  -5.500  -0.2081   0.04569   0.04261  -0.0586   0.7786   0.0215
  -5.250  -0.1803   0.04300   0.03975  -0.0617   0.7593   0.0223
  -4.750  -0.1035   0.01883   0.01396  -0.0801   0.7368   0.0269
  -4.250  -0.0496   0.01437   0.00854  -0.0812   0.7117   0.0283
  -4.000  -0.0223   0.01349   0.00743  -0.0812   0.7006   0.0287
  -3.750   0.0052   0.01283   0.00657  -0.0811   0.6901   0.0291
  -3.500   0.0327   0.01227   0.00583  -0.0810   0.6799   0.0295
  -3.250   0.0605   0.01178   0.00519  -0.0808   0.6702   0.0299
  -3.000   0.0881   0.01142   0.00470  -0.0807   0.6610   0.0305
  -2.750   0.1159   0.01108   0.00426  -0.0805   0.6516   0.0312
  -2.500   0.1437   0.01073   0.00379  -0.0804   0.6428   0.0317
  -2.250   0.1715   0.01043   0.00338  -0.0802   0.6338   0.0322
  -2.000   0.1994   0.01016   0.00303  -0.0800   0.6253   0.0328
  -1.750   0.2272   0.00994   0.00273  -0.0798   0.6170   0.0336
  -1.500   0.2552   0.00975   0.00248  -0.0797   0.6087   0.0343
  -1.250   0.2830   0.00961   0.00226  -0.0795   0.6007   0.0351
  -1.000   0.3110   0.00948   0.00208  -0.0793   0.5924   0.0357
  -0.750   0.3388   0.00938   0.00193  -0.0791   0.5846   0.0363
  -0.500   0.3668   0.00929   0.00180  -0.0790   0.5762   0.0369
  -0.250   0.3947   0.00920   0.00165  -0.0788   0.5682   0.0388
   0.000   0.4225   0.00911   0.00155  -0.0786   0.5597   0.0420
   0.250   0.4504   0.00903   0.00147  -0.0785   0.5515   0.0480
   0.500   0.4780   0.00900   0.00155  -0.0783   0.5428   0.0822
   0.750   0.5060   0.00907   0.00160  -0.0782   0.5337   0.0912
   1.000   0.5337   0.00914   0.00163  -0.0780   0.5224   0.0958
   1.250   0.5612   0.00919   0.00165  -0.0778   0.5072   0.0995
   1.500   0.5887   0.00927   0.00168  -0.0776   0.4907   0.1031
   1.750   0.6162   0.00935   0.00172  -0.0775   0.4774   0.1059
   2.000   0.6437   0.00943   0.00176  -0.0773   0.4654   0.1073
   2.250   0.6711   0.00945   0.00176  -0.0771   0.4510   0.1114
   2.500   0.6984   0.00954   0.00183  -0.0770   0.4349   0.1155
   2.750   0.7256   0.00963   0.00189  -0.0768   0.4193   0.1175
   3.000   0.7529   0.00973   0.00196  -0.0766   0.4054   0.1185
   3.250   0.7801   0.00984   0.00205  -0.0765   0.3915   0.1196
   3.750   0.8345   0.01008   0.00225  -0.0761   0.3659   0.1218
   4.000   0.8616   0.01020   0.00238  -0.0759   0.3533   0.1241
   4.250   0.8885   0.01035   0.00253  -0.0758   0.3398   0.1268
   4.500   0.9153   0.01054   0.00270  -0.0756   0.3236   0.1303
   4.750   0.9419   0.01074   0.00288  -0.0754   0.3072   0.1352
   5.000   0.9685   0.01091   0.00311  -0.0752   0.2933   0.1547
   6.500   1.1150   0.01265   0.00543  -0.0730   0.1011   1.0000
   6.750   1.1393   0.01318   0.00590  -0.0726   0.0870   1.0000
   7.000   1.1640   0.01364   0.00634  -0.0722   0.0783   1.0000
   7.250   1.1891   0.01400   0.00673  -0.0718   0.0711   1.0000
   7.500   1.2132   0.01451   0.00719  -0.0714   0.0554   1.0000
   7.750   1.2329   0.01566   0.00807  -0.0706   0.0217   1.0000
   8.000   1.2560   0.01627   0.00871  -0.0700   0.0171   1.0000
   8.250   1.2787   0.01691   0.00939  -0.0693   0.0144   1.0000
   8.500   1.3015   0.01751   0.01006  -0.0687   0.0130   1.0000
   8.750   1.3240   0.01809   0.01071  -0.0680   0.0119   1.0000
   9.000   1.3457   0.01876   0.01144  -0.0673   0.0108   1.0000
   9.250   1.3657   0.01962   0.01237  -0.0664   0.0099   1.0000
   9.500   1.3851   0.02049   0.01333  -0.0655   0.0093   1.0000
   9.750   1.4049   0.02126   0.01420  -0.0645   0.0089   1.0000
  10.000   1.4234   0.02212   0.01514  -0.0635   0.0084   1.0000
  10.250   1.4411   0.02300   0.01611  -0.0624   0.0079   1.0000
  10.500   1.4579   0.02391   0.01709  -0.0612   0.0075   1.0000
  10.750   1.4727   0.02494   0.01818  -0.0599   0.0071   1.0000
  11.000   1.4820   0.02638   0.01974  -0.0580   0.0067   1.0000
  11.250   1.4900   0.02764   0.02110  -0.0559   0.0065   1.0000
  11.500   1.4969   0.02896   0.02253  -0.0539   0.0064   1.0000
  11.750   1.5017   0.03054   0.02424  -0.0521   0.0062   1.0000
  12.000   1.5054   0.03239   0.02621  -0.0507   0.0061   1.0000
  12.250   1.5083   0.03450   0.02845  -0.0497   0.0059   1.0000
  12.500   1.5106   0.03688   0.03095  -0.0491   0.0058   1.0000
  12.750   1.5118   0.03954   0.03374  -0.0488   0.0056   1.0000
  13.000   1.5122   0.04242   0.03674  -0.0488   0.0055   1.0000
  13.250   1.5116   0.04552   0.03996  -0.0490   0.0054   1.0000
  13.500   1.5099   0.04881   0.04337  -0.0493   0.0053   1.0000
  13.750   1.5069   0.05233   0.04703  -0.0497   0.0052   1.0000
  14.000   1.5028   0.05605   0.05087  -0.0503   0.0051   1.0000
  14.250   1.4972   0.06003   0.05497  -0.0510   0.0051   1.0000
  14.500   1.4908   0.06421   0.05927  -0.0519   0.0050   1.0000
  14.750   1.4830   0.06863   0.06380  -0.0529   0.0049   1.0000
  15.000   1.4742   0.07331   0.06860  -0.0541   0.0049   1.0000
  15.250   1.4650   0.07822   0.07363  -0.0555   0.0048   1.0000
  15.500   1.4549   0.08343   0.07896  -0.0572   0.0048   1.0000
  15.750   1.4443   0.08887   0.08452  -0.0590   0.0047   1.0000
  16.000   1.4330   0.09455   0.09032  -0.0610   0.0047   1.0000
  16.250   1.4206   0.10050   0.09640  -0.0632   0.0046   1.0000
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