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GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 57 AIRFOIL (goe57-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.28 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe57-il-1000000.txt
Download as CSV file: xf-goe57-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 57 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3137   0.09869   0.09711  -0.0245   1.0000   0.0138
  -8.250  -0.3118   0.09599   0.09444  -0.0252   1.0000   0.0154
  -8.000  -0.3157   0.09371   0.09219  -0.0248   1.0000   0.0155
  -5.750  -0.0973   0.05289   0.05109  -0.0840   0.9301   0.0206
  -5.500  -0.0778   0.05137   0.04950  -0.0844   0.9156   0.0210
  -5.250  -0.0551   0.04965   0.04770  -0.0861   0.9016   0.0218
  -5.000  -0.0284   0.04719   0.04513  -0.0892   0.8874   0.0233
  -4.750   0.0157   0.04328   0.04101  -0.0965   0.8739   0.0255
  -4.500   0.0523   0.02236   0.02002  -0.0943   0.8397   0.0257
  -4.250   0.0770   0.01644   0.01393  -0.0993   0.8325   0.0266
  -4.000   0.1009   0.01499   0.01240  -0.1002   0.8247   0.0271
  -3.750   0.1260   0.01361   0.01094  -0.1012   0.8160   0.0278
  -3.500   0.1527   0.01212   0.00934  -0.1025   0.8079   0.0289
  -3.250   0.1856   0.01118   0.00822  -0.1036   0.7990   0.0326
  -3.000   0.2215   0.02489   0.02159  -0.1105   0.8083   0.0329
  -2.750   0.2509   0.02244   0.01890  -0.1113   0.7974   0.0330
  -2.500   0.2798   0.02020   0.01642  -0.1120   0.7857   0.0331
  -2.000   0.3373   0.01327   0.00866  -0.1137   0.7615   0.0337
  -1.750   0.3650   0.01193   0.00711  -0.1137   0.7454   0.0323
  -1.500   0.3922   0.01145   0.00643  -0.1134   0.7239   0.0328
  -0.750   0.4724   0.00967   0.00392  -0.1125   0.6394   0.0333
  -0.500   0.4990   0.00914   0.00319  -0.1122   0.6131   0.0334
  -0.250   0.5257   0.00854   0.00242  -0.1120   0.5883   0.0346
   0.000   0.5523   0.00837   0.00212  -0.1117   0.5600   0.0355
   0.250   0.5787   0.00838   0.00199  -0.1113   0.5233   0.0367
   0.500   0.6043   0.00854   0.00194  -0.1109   0.4741   0.0382
   0.750   0.6297   0.00875   0.00192  -0.1104   0.4230   0.0395
   1.000   0.6557   0.00891   0.00190  -0.1101   0.3854   0.0407
   1.250   0.6818   0.00907   0.00191  -0.1097   0.3512   0.0418
   1.500   0.7078   0.00929   0.00197  -0.1094   0.3165   0.0427
   1.750   0.7337   0.00942   0.00191  -0.1091   0.2767   0.0482
   2.000   0.7580   0.00986   0.00207  -0.1085   0.2166   0.0532
   2.250   0.7840   0.01008   0.00218  -0.1082   0.1924   0.0621
   2.500   0.8107   0.01019   0.00229  -0.1079   0.1840   0.0823
   2.750   0.8378   0.01016   0.00245  -0.1079   0.1805   0.1816
   3.000   0.8606   0.00882   0.00275  -0.1073   0.1771   1.0000
   3.250   0.8870   0.00904   0.00290  -0.1070   0.1706   1.0000
   3.500   0.9140   0.00917   0.00300  -0.1068   0.1669   1.0000
   3.750   0.9408   0.00934   0.00313  -0.1066   0.1643   1.0000
   4.000   0.9673   0.00952   0.00328  -0.1063   0.1612   1.0000
   4.250   0.9934   0.00976   0.00348  -0.1060   0.1563   1.0000
   4.500   1.0205   0.00985   0.00358  -0.1059   0.1543   1.0000
   4.750   1.0472   0.00999   0.00371  -0.1057   0.1506   1.0000
   5.000   1.0731   0.01023   0.00388  -0.1054   0.1419   1.0000
   5.250   1.0991   0.01044   0.00398  -0.1051   0.1249   1.0000
   5.500   1.1150   0.01198   0.00494  -0.1033   0.0199   1.0000
   5.750   1.1402   0.01230   0.00527  -0.1028   0.0158   1.0000
   6.000   1.1653   0.01262   0.00563  -0.1023   0.0148   1.0000
   6.250   1.1899   0.01299   0.00606  -0.1017   0.0137   1.0000
   6.500   1.2136   0.01348   0.00660  -0.1010   0.0124   1.0000
   6.750   1.2361   0.01412   0.00732  -0.1001   0.0114   1.0000
   7.000   1.2600   0.01455   0.00778  -0.0994   0.0110   1.0000
   7.250   1.2832   0.01505   0.00833  -0.0986   0.0106   1.0000
   7.500   1.3058   0.01560   0.00894  -0.0978   0.0101   1.0000
   7.750   1.3278   0.01621   0.00960  -0.0968   0.0096   1.0000
   8.000   1.3489   0.01689   0.01033  -0.0958   0.0092   1.0000
   8.250   1.3685   0.01768   0.01117  -0.0945   0.0087   1.0000
   8.500   1.3791   0.01936   0.01297  -0.0919   0.0082   1.0000
   8.750   1.3968   0.02021   0.01389  -0.0904   0.0079   1.0000
   9.000   1.4153   0.02093   0.01467  -0.0890   0.0077   1.0000
   9.250   1.4315   0.02182   0.01562  -0.0873   0.0075   1.0000
   9.500   1.4460   0.02281   0.01668  -0.0853   0.0073   1.0000
   9.750   1.4589   0.02387   0.01781  -0.0832   0.0071   1.0000
  10.000   1.4692   0.02496   0.01899  -0.0806   0.0070   1.0000
  10.250   1.4768   0.02611   0.02021  -0.0776   0.0068   1.0000
  10.500   1.4840   0.02731   0.02147  -0.0747   0.0067   1.0000
  10.750   1.4907   0.02860   0.02284  -0.0720   0.0065   1.0000
  11.000   1.4968   0.02999   0.02430  -0.0694   0.0064   1.0000
  11.250   1.5028   0.03143   0.02580  -0.0671   0.0062   1.0000
  11.500   1.5081   0.03300   0.02744  -0.0649   0.0061   1.0000
  11.750   1.5124   0.03473   0.02924  -0.0628   0.0059   1.0000
  12.000   1.5156   0.03669   0.03129  -0.0608   0.0058   1.0000
  12.250   1.5177   0.03896   0.03363  -0.0588   0.0057   1.0000
  12.500   1.5200   0.04157   0.03632  -0.0567   0.0056   1.0000
  12.750   1.5267   0.04542   0.04027  -0.0543   0.0055   1.0000
  13.000   1.5197   0.04823   0.04329  -0.0524   0.0054   1.0000
  13.250   1.5153   0.05057   0.04578  -0.0513   0.0053   1.0000
  13.500   1.5117   0.05337   0.04873  -0.0504   0.0052   1.0000
  13.750   1.5067   0.05662   0.05213  -0.0496   0.0052   1.0000
  14.000   1.5001   0.06036   0.05602  -0.0489   0.0052   1.0000
  14.250   1.4917   0.06438   0.06020  -0.0487   0.0052   1.0000
  14.500   1.4811   0.06886   0.06484  -0.0488   0.0052   1.0000
  14.750   1.4696   0.07361   0.06975  -0.0494   0.0052   1.0000
  15.000   1.4556   0.07894   0.07524  -0.0502   0.0052   1.0000
  15.250   1.4536   0.08288   0.07936  -0.0506   0.0059   1.0000
  15.500   1.4456   0.08750   0.08409  -0.0520   0.0059   1.0000
  15.750   1.4364   0.09247   0.08914  -0.0539   0.0058   1.0000
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