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GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.04 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe610bm-il-1000000-n5.txt
Download as CSV file: xf-goe610bm-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610-B MOD. 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3252   0.11129   0.10965  -0.0201   0.9408   0.0033
  -9.000  -0.3201   0.10800   0.10632  -0.0211   0.9266   0.0033
  -8.750  -0.3146   0.10474   0.10302  -0.0222   0.9138   0.0033
  -8.500  -0.3084   0.10156   0.09980  -0.0235   0.9020   0.0034
  -8.250  -0.3019   0.09840   0.09661  -0.0249   0.8906   0.0035
  -8.000  -0.2956   0.09512   0.09329  -0.0265   0.8792   0.0036
  -7.750  -0.2891   0.09183   0.08996  -0.0281   0.8676   0.0037
  -7.500  -0.2828   0.08847   0.08657  -0.0299   0.8547   0.0038
  -7.250  -0.2771   0.08511   0.08317  -0.0320   0.8396   0.0039
  -7.000  -0.2658   0.08112   0.07911  -0.0359   0.8237   0.0040
  -6.750  -0.2520   0.07656   0.07450  -0.0409   0.8078   0.0043
  -6.500  -0.2352   0.07152   0.06939  -0.0469   0.7925   0.0044
  -6.250  -0.2142   0.06537   0.06315  -0.0550   0.7777   0.0045
  -6.000  -0.1858   0.05738   0.05506  -0.0664   0.7649   0.0049
  -5.750  -0.1565   0.05294   0.05053  -0.0731   0.7534   0.0051
  -5.500  -0.0690   0.01255   0.00770  -0.1129   0.7534   0.0072
  -5.250  -0.0398   0.01180   0.00680  -0.1134   0.7439   0.0084
  -5.000  -0.0106   0.01097   0.00576  -0.1139   0.7357   0.0097
  -4.750   0.0186   0.01050   0.00516  -0.1143   0.7277   0.0114
  -4.500   0.0471   0.01073   0.00542  -0.1143   0.7199   0.0132
  -4.250   0.0761   0.01052   0.00512  -0.1145   0.7121   0.0148
  -4.000   0.1047   0.01073   0.00533  -0.1146   0.7051   0.0159
  -3.750   0.1332   0.01110   0.00572  -0.1146   0.6971   0.0169
  -3.500   0.1618   0.01129   0.00588  -0.1147   0.6889   0.0182
  -3.250   0.1907   0.01117   0.00568  -0.1149   0.6800   0.0197
  -3.000   0.2195   0.01114   0.00558  -0.1150   0.6713   0.0211
  -2.750   0.2483   0.01114   0.00550  -0.1152   0.6599   0.0220
  -2.500   0.2769   0.01122   0.00551  -0.1153   0.6459   0.0225
  -2.250   0.3055   0.01130   0.00549  -0.1155   0.6266   0.0229
  -2.000   0.3352   0.01023   0.00417  -0.1161   0.6019   0.0247
  -1.750   0.3638   0.01006   0.00385  -0.1164   0.5728   0.0255
  -1.500   0.3925   0.00993   0.00358  -0.1166   0.5505   0.0260
  -1.250   0.4214   0.00977   0.00330  -0.1169   0.5342   0.0263
  -1.000   0.4503   0.00959   0.00304  -0.1172   0.5233   0.0265
  -0.750   0.4792   0.00944   0.00280  -0.1174   0.5138   0.0267
  -0.500   0.5081   0.00932   0.00264  -0.1177   0.5054   0.0271
  -0.250   0.5371   0.00920   0.00246  -0.1179   0.4977   0.0271
   0.000   0.5661   0.00908   0.00228  -0.1182   0.4911   0.0269
   0.250   0.5950   0.00900   0.00215  -0.1184   0.4846   0.0268
   0.500   0.6240   0.00893   0.00204  -0.1187   0.4788   0.0268
   0.750   0.6528   0.00890   0.00197  -0.1189   0.4726   0.0269
   1.000   0.6815   0.00888   0.00192  -0.1191   0.4675   0.0271
   1.250   0.7103   0.00886   0.00188  -0.1193   0.4622   0.0275
   1.500   0.7389   0.00888   0.00187  -0.1195   0.4564   0.0285
   1.750   0.7675   0.00890   0.00187  -0.1197   0.4499   0.0309
   2.000   0.7958   0.00896   0.00191  -0.1199   0.4401   0.0335
   2.250   0.8242   0.00901   0.00194  -0.1200   0.4306   0.0382
   2.500   0.8526   0.00903   0.00202  -0.1203   0.4222   0.0821
   2.750   0.8814   0.00890   0.00215  -0.1207   0.4147   0.2159
   3.000   0.9102   0.00867   0.00232  -0.1213   0.4081   0.4253
   3.500   0.9611   0.00777   0.00255  -0.1206   0.3908   1.0000
   3.750   0.9891   0.00792   0.00265  -0.1207   0.3816   1.0000
   4.000   1.0166   0.00813   0.00278  -0.1208   0.3641   1.0000
   4.250   1.0432   0.00849   0.00296  -0.1208   0.3273   1.0000
   4.500   1.0691   0.00897   0.00322  -0.1208   0.2848   1.0000
   4.750   1.0912   0.01011   0.00381  -0.1203   0.1855   1.0000
   5.000   1.1150   0.01091   0.00430  -0.1200   0.1296   1.0000
   5.250   1.1396   0.01153   0.00470  -0.1198   0.0926   1.0000
   5.500   1.1606   0.01271   0.00547  -0.1190   0.0201   1.0000
   5.750   1.1869   0.01298   0.00576  -0.1189   0.0133   1.0000
   6.000   1.2128   0.01329   0.00610  -0.1187   0.0112   1.0000
   6.250   1.2381   0.01368   0.00653  -0.1184   0.0089   1.0000
   6.500   1.2637   0.01399   0.00688  -0.1182   0.0079   1.0000
   6.750   1.2888   0.01434   0.00725  -0.1179   0.0069   1.0000
   7.000   1.3130   0.01480   0.00774  -0.1175   0.0059   1.0000
   7.250   1.3373   0.01523   0.00820  -0.1171   0.0055   1.0000
   7.500   1.3613   0.01566   0.00868  -0.1166   0.0050   1.0000
   7.750   1.3849   0.01610   0.00916  -0.1161   0.0045   1.0000
   8.000   1.4079   0.01658   0.00966  -0.1156   0.0041   1.0000
   8.250   1.4293   0.01724   0.01037  -0.1147   0.0037   1.0000
   8.500   1.4511   0.01779   0.01098  -0.1139   0.0035   1.0000
   8.750   1.4720   0.01840   0.01165  -0.1130   0.0033   1.0000
   9.000   1.4920   0.01906   0.01238  -0.1119   0.0031   1.0000
   9.250   1.5112   0.01973   0.01314  -0.1108   0.0029   1.0000
   9.500   1.5298   0.02042   0.01388  -0.1096   0.0027   1.0000
   9.750   1.5470   0.02116   0.01468  -0.1081   0.0026   1.0000
  10.000   1.5622   0.02198   0.01556  -0.1064   0.0025   1.0000
  10.250   1.5714   0.02314   0.01681  -0.1037   0.0023   1.0000
  10.500   1.5764   0.02436   0.01815  -0.1003   0.0023   1.0000
  10.750   1.5827   0.02542   0.01930  -0.0973   0.0022   1.0000
  11.000   1.5892   0.02659   0.02057  -0.0945   0.0021   1.0000
  11.250   1.5946   0.02796   0.02204  -0.0920   0.0021   1.0000
  11.500   1.5994   0.02949   0.02367  -0.0896   0.0020   1.0000
  11.750   1.6036   0.03116   0.02545  -0.0875   0.0019   1.0000
  12.000   1.6067   0.03305   0.02744  -0.0855   0.0018   1.0000
  12.250   1.6077   0.03524   0.02978  -0.0837   0.0018   1.0000
  12.500   1.6083   0.03759   0.03223  -0.0821   0.0017   1.0000
  12.750   1.6081   0.04016   0.03493  -0.0807   0.0017   1.0000
  13.000   1.6075   0.04288   0.03776  -0.0796   0.0016   1.0000
  13.250   1.6063   0.04577   0.04076  -0.0787   0.0016   1.0000
  13.500   1.6037   0.04895   0.04406  -0.0780   0.0016   1.0000
  13.750   1.6009   0.05220   0.04743  -0.0775   0.0015   1.0000
  14.000   1.5966   0.05575   0.05109  -0.0771   0.0015   1.0000
  14.250   1.5917   0.05948   0.05494  -0.0770   0.0015   1.0000
  14.500   1.5872   0.06331   0.05889  -0.0772   0.0015   1.0000
  14.750   1.5816   0.06744   0.06313  -0.0775   0.0014   1.0000
  15.000   1.5744   0.07193   0.06775  -0.0781   0.0014   1.0000
  15.250   1.5674   0.07655   0.07248  -0.0789   0.0014   1.0000
  15.500   1.5592   0.08139   0.07744  -0.0799   0.0014   1.0000
  15.750   1.5502   0.08645   0.08262  -0.0810   0.0014   1.0000
  16.000   1.5405   0.09174   0.08804  -0.0824   0.0014   1.0000
  16.250   1.5300   0.09723   0.09366  -0.0839   0.0014   1.0000
  16.500   1.5186   0.10293   0.09948  -0.0856   0.0013   1.0000
  16.750   1.5058   0.10898   0.10565  -0.0875   0.0013   1.0000
  17.000   1.4936   0.11509   0.11189  -0.0896   0.0013   1.0000
  17.250   1.4804   0.12149   0.11843  -0.0920   0.0013   1.0000
  17.500   1.4670   0.12808   0.12514  -0.0946   0.0013   1.0000
  17.750   1.4530   0.13495   0.13215  -0.0976   0.0013   1.0000
  18.000   1.4392   0.14200   0.13934  -0.1009   0.0013   1.0000
  18.250   1.4243   0.14957   0.14706  -0.1047   0.0013   1.0000
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