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GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il)
Reynolds number: 1,000,000
Max Cl/Cd: 130.41 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe300-il-1000000.txt
Download as CSV file: xf-goe300-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2790   0.01649   0.01262  -0.0997   0.8928   0.0207
  -7.250  -0.2553   0.01403   0.00991  -0.0997   0.8842   0.0216
  -7.000  -0.2296   0.01296   0.00864  -0.0994   0.8749   0.0226
  -6.750  -0.2030   0.01216   0.00766  -0.0992   0.8643   0.0233
  -6.500  -0.1765   0.01146   0.00684  -0.0989   0.8530   0.0248
  -6.250  -0.1495   0.01108   0.00636  -0.0986   0.8406   0.0261
  -6.000  -0.1222   0.01071   0.00585  -0.0983   0.8275   0.0274
  -5.750  -0.0948   0.01037   0.00545  -0.0980   0.8135   0.0293
  -5.500  -0.0671   0.01026   0.00526  -0.0977   0.7976   0.0309
  -5.250  -0.0395   0.01008   0.00494  -0.0974   0.7809   0.0322
  -5.000  -0.0118   0.00997   0.00479  -0.0971   0.7642   0.0342
  -4.750   0.0162   0.01007   0.00484  -0.0969   0.7476   0.0358
  -4.500   0.0442   0.01011   0.00477  -0.0966   0.7310   0.0373
  -4.250   0.0719   0.00998   0.00457  -0.0964   0.7145   0.0390
  -3.750   0.1281   0.01033   0.00481  -0.0960   0.6796   0.0417
  -3.500   0.1561   0.01042   0.00480  -0.0958   0.6637   0.0431
  -3.250   0.1838   0.01009   0.00435  -0.0956   0.6504   0.0447
  -3.000   0.2120   0.01013   0.00436  -0.0955   0.6380   0.0459
  -2.750   0.2402   0.01029   0.00450  -0.0954   0.6265   0.0471
  -2.500   0.2683   0.01031   0.00445  -0.0952   0.6153   0.0485
  -2.250   0.2965   0.01025   0.00433  -0.0951   0.6051   0.0499
  -2.000   0.3247   0.01031   0.00432  -0.0949   0.5957   0.0508
  -1.750   0.3521   0.00969   0.00358  -0.0948   0.5864   0.0527
  -1.500   0.3803   0.00966   0.00353  -0.0947   0.5777   0.0539
  -1.250   0.4082   0.00960   0.00342  -0.0946   0.5684   0.0551
  -1.000   0.4364   0.00955   0.00333  -0.0945   0.5592   0.0565
  -0.750   0.4642   0.00945   0.00316  -0.0944   0.5505   0.0577
  -0.500   0.4924   0.00931   0.00299  -0.0943   0.5432   0.0586
   0.000   0.5480   0.00895   0.00253  -0.0940   0.5278   0.0609
   0.500   0.6036   0.00871   0.00224  -0.0938   0.5107   0.0637
   1.000   0.6594   0.00866   0.00214  -0.0936   0.4952   0.0666
   1.500   0.7152   0.00864   0.00208  -0.0934   0.4778   0.0693
   1.750   0.7429   0.00867   0.00207  -0.0933   0.4676   0.0701
   2.000   0.7702   0.00860   0.00194  -0.0931   0.4548   0.0733
   2.250   0.7978   0.00864   0.00196  -0.0930   0.4400   0.0759
   2.500   0.8251   0.00874   0.00200  -0.0929   0.4241   0.0787
   2.750   0.8522   0.00886   0.00207  -0.0927   0.4073   0.0815
   3.000   0.8791   0.00897   0.00211  -0.0926   0.3898   0.0859
   3.250   0.9060   0.00911   0.00221  -0.0924   0.3746   0.0916
   3.750   0.9601   0.00935   0.00241  -0.0921   0.3539   0.1062
   4.000   0.9869   0.00950   0.00254  -0.0919   0.3454   0.1161
   4.250   1.0142   0.00958   0.00265  -0.0918   0.3386   0.1291
   4.500   1.0409   0.00972   0.00280  -0.0917   0.3315   0.1511
   4.750   1.0658   0.00839   0.00311  -0.0915   0.3268   1.0000
   5.000   1.0927   0.00854   0.00323  -0.0913   0.3216   1.0000
   5.250   1.1190   0.00875   0.00339  -0.0911   0.3147   1.0000
   5.500   1.1461   0.00888   0.00353  -0.0910   0.3097   1.0000
   5.750   1.1726   0.00906   0.00368  -0.0908   0.3036   1.0000
   6.000   1.1989   0.00926   0.00385  -0.0906   0.2976   1.0000
   6.250   1.2257   0.00940   0.00400  -0.0904   0.2912   1.0000
   6.500   1.2515   0.00964   0.00419  -0.0902   0.2828   1.0000
   6.750   1.2780   0.00980   0.00435  -0.0900   0.2740   1.0000
   7.000   1.3035   0.01005   0.00455  -0.0897   0.2612   1.0000
   7.250   1.3279   0.01041   0.00481  -0.0893   0.2394   1.0000
   7.500   1.3480   0.01117   0.00529  -0.0883   0.1930   1.0000
   7.750   1.3695   0.01178   0.00576  -0.0875   0.1734   1.0000
   8.000   1.3929   0.01218   0.00613  -0.0869   0.1647   1.0000
   8.250   1.4164   0.01256   0.00649  -0.0864   0.1589   1.0000
   8.500   1.4393   0.01297   0.00688  -0.0857   0.1527   1.0000
   8.750   1.4639   0.01321   0.00716  -0.0854   0.1496   1.0000
   9.000   1.4873   0.01354   0.00750  -0.0848   0.1453   1.0000
   9.250   1.5095   0.01397   0.00792  -0.0841   0.1400   1.0000
   9.500   1.5332   0.01424   0.00822  -0.0836   0.1364   1.0000
   9.750   1.5564   0.01453   0.00855  -0.0831   0.1325   1.0000
  10.000   1.5780   0.01495   0.00895  -0.0823   0.1271   1.0000
  10.250   1.6002   0.01529   0.00931  -0.0816   0.1222   1.0000
  10.500   1.6209   0.01572   0.00972  -0.0808   0.1143   1.0000
  10.750   1.6412   0.01616   0.01015  -0.0798   0.1069   1.0000
  11.000   1.6588   0.01676   0.01069  -0.0786   0.0960   1.0000
  11.250   1.6721   0.01755   0.01139  -0.0766   0.0816   1.0000
  11.500   1.6779   0.01862   0.01234  -0.0736   0.0652   1.0000
  11.750   1.6775   0.02010   0.01370  -0.0699   0.0450   1.0000
  12.000   1.6754   0.02181   0.01531  -0.0664   0.0303   1.0000
  12.250   1.6805   0.02316   0.01667  -0.0641   0.0254   1.0000
  12.500   1.6853   0.02461   0.01816  -0.0619   0.0224   1.0000
  12.750   1.6940   0.02585   0.01946  -0.0603   0.0210   1.0000
  13.000   1.6995   0.02739   0.02106  -0.0587   0.0195   1.0000
  13.250   1.7025   0.02925   0.02299  -0.0571   0.0181   1.0000
  13.500   1.7102   0.03077   0.02458  -0.0559   0.0174   1.0000
  13.750   1.7156   0.03257   0.02645  -0.0549   0.0166   1.0000
  14.000   1.7183   0.03471   0.02865  -0.0539   0.0158   1.0000
  14.250   1.7171   0.03734   0.03137  -0.0529   0.0151   1.0000
  14.500   1.7161   0.04006   0.03419  -0.0522   0.0145   1.0000
  14.750   1.7184   0.04249   0.03671  -0.0518   0.0142   1.0000
  15.000   1.7188   0.04521   0.03952  -0.0514   0.0138   1.0000
  15.250   1.7177   0.04816   0.04256  -0.0512   0.0134   1.0000
  15.500   1.7148   0.05140   0.04589  -0.0511   0.0130   1.0000
  15.750   1.7099   0.05497   0.04955  -0.0512   0.0127   1.0000
  16.000   1.7025   0.05897   0.05365  -0.0514   0.0124   1.0000
  16.250   1.6917   0.06350   0.05829  -0.0519   0.0121   1.0000
  16.500   1.6760   0.06882   0.06373  -0.0526   0.0117   1.0000
  16.750   1.6652   0.07357   0.06859  -0.0534   0.0116   1.0000
  17.000   1.6587   0.07776   0.07289  -0.0542   0.0114   1.0000
  17.250   1.6503   0.08228   0.07751  -0.0551   0.0112   1.0000
  17.500   1.6407   0.08708   0.08241  -0.0562   0.0111   1.0000
  17.750   1.6303   0.09208   0.08753  -0.0574   0.0109   1.0000
  18.000   1.6187   0.09731   0.09286  -0.0588   0.0107   1.0000
  18.250   1.6067   0.10267   0.09833  -0.0603   0.0106   1.0000
  18.500   1.5944   0.10820   0.10395  -0.0620   0.0104   1.0000
  18.750   1.5823   0.11373   0.10958  -0.0639   0.0103   1.0000
  19.000   1.5694   0.11942   0.11538  -0.0659   0.0102   1.0000
  19.250   1.5570   0.12513   0.12119  -0.0680   0.0101   1.0000
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