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GOE 456 AIRFOIL (goe456-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 456 AIRFOIL (goe456-il)
Reynolds number: 100,000
Max Cl/Cd: 65.14 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe456-il-100000.txt
Download as CSV file: xf-goe456-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 456 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3382   0.09802   0.09376  -0.0268   1.0000   0.0684
  -7.000  -0.3565   0.09772   0.09358  -0.0242   1.0000   0.0690
  -6.750  -0.3699   0.09711   0.09308  -0.0246   1.0000   0.0697
  -6.500  -0.3779   0.09622   0.09225  -0.0277   1.0000   0.0701
  -6.250  -0.3801   0.09300   0.08911  -0.0279   1.0000   0.0708
  -6.000  -0.3784   0.08906   0.08520  -0.0202   1.0000   0.0730
  -5.750  -0.3790   0.08681   0.08299  -0.0185   1.0000   0.0754
  -5.500  -0.3791   0.08464   0.08086  -0.0187   1.0000   0.0783
  -5.250  -0.3644   0.08275   0.07890  -0.0315   1.0000   0.0830
  -5.000  -0.3649   0.07885   0.07508  -0.0289   1.0000   0.0842
  -4.750  -0.3560   0.07573   0.07200  -0.0259   0.9977   0.0876
  -4.500  -0.3049   0.07014   0.06621  -0.0410   0.9899   0.0977
  -4.250  -0.2572   0.06552   0.06141  -0.0517   0.9832   0.1104
  -4.000  -0.2230   0.06160   0.05739  -0.0572   0.9754   0.1241
  -3.750  -0.1810   0.05731   0.05297  -0.0639   0.9698   0.1380
  -3.500  -0.1571   0.05399   0.04967  -0.0645   0.9615   0.1453
  -3.250  -0.1088   0.04972   0.04519  -0.0722   0.9563   0.1591
  -3.000  -0.0329   0.03901   0.03317  -0.0871   0.9508   0.0965
  -2.750   0.0129   0.03149   0.02489  -0.0913   0.9474   0.0668
  -2.500   0.0606   0.02715   0.01947  -0.0948   0.9440   0.0601
  -2.250   0.0960   0.02564   0.01759  -0.0963   0.9360   0.0660
  -2.000   0.1395   0.02378   0.01522  -0.0986   0.9309   0.0685
  -1.750   0.1741   0.02247   0.01379  -0.0995   0.9230   0.0745
  -1.500   0.2161   0.02162   0.01298  -0.1020   0.9170   0.0998
  -1.250   0.2493   0.02113   0.01282  -0.1029   0.9079   0.2325
  -1.000   0.2916   0.02121   0.01290  -0.1059   0.9022   0.3082
  -0.750   0.3200   0.02111   0.01278  -0.1062   0.8920   0.3451
  -0.500   0.3607   0.02061   0.01229  -0.1085   0.8864   0.3730
  -0.250   0.3951   0.02017   0.01199  -0.1098   0.8782   0.4221
   0.000   0.4520   0.01843   0.01137  -0.1150   0.8760   1.0000
   0.250   0.4809   0.01864   0.01133  -0.1152   0.8661   1.0000
   0.500   0.5243   0.01852   0.01099  -0.1179   0.8616   1.0000
   0.750   0.5496   0.01879   0.01114  -0.1175   0.8513   1.0000
   1.000   0.5843   0.01884   0.01106  -0.1186   0.8447   1.0000
   1.250   0.6147   0.01896   0.01111  -0.1190   0.8366   1.0000
   1.500   0.6419   0.01921   0.01130  -0.1189   0.8279   1.0000
   1.750   0.6771   0.01916   0.01122  -0.1200   0.8219   1.0000
   2.000   0.7012   0.01948   0.01153  -0.1194   0.8123   1.0000
   2.250   0.7413   0.01907   0.01109  -0.1207   0.8066   1.0000
   2.500   0.7677   0.01903   0.01106  -0.1199   0.7949   1.0000
   2.750   0.7973   0.01874   0.01082  -0.1193   0.7826   1.0000
   3.000   0.8270   0.01839   0.01049  -0.1186   0.7701   1.0000
   3.250   0.8555   0.01821   0.01033  -0.1180   0.7584   1.0000
   3.500   0.8850   0.01810   0.01028  -0.1177   0.7488   1.0000
   3.750   0.9141   0.01803   0.01034  -0.1173   0.7391   1.0000
   4.000   0.9386   0.01817   0.01059  -0.1164   0.7276   1.0000
   4.250   0.9643   0.01826   0.01079  -0.1156   0.7161   1.0000
   4.500   0.9926   0.01793   0.01054  -0.1145   0.7005   1.0000
   4.750   1.0208   0.01697   0.00952  -0.1123   0.6701   1.0000
   5.000   1.0410   0.01661   0.00922  -0.1095   0.6345   1.0000
   5.250   1.0597   0.01639   0.00889  -0.1063   0.5891   1.0000
   5.500   1.0742   0.01649   0.00887  -0.1028   0.5318   1.0000
   5.750   1.0842   0.01695   0.00902  -0.0988   0.4379   1.0000
   6.000   1.0814   0.01884   0.00971  -0.0935   0.2707   1.0000
   6.250   1.0827   0.02106   0.01099  -0.0895   0.1365   1.0000
   6.500   1.0841   0.02338   0.01260  -0.0856   0.0546   1.0000
   6.750   1.0983   0.02458   0.01399  -0.0831   0.0491   1.0000
   7.000   1.1115   0.02582   0.01543  -0.0805   0.0460   1.0000
   7.250   1.1221   0.02719   0.01698  -0.0777   0.0443   1.0000
   7.500   1.1273   0.02878   0.01870  -0.0742   0.0427   1.0000
   7.750   1.1290   0.03083   0.02079  -0.0704   0.0409   1.0000
   8.000   1.1419   0.03230   0.02237  -0.0681   0.0393   1.0000
   8.250   1.1638   0.03433   0.02442  -0.0669   0.0389   1.0000
   8.500   1.2127   0.03755   0.02762  -0.0693   0.0397   1.0000
   8.750   1.2669   0.04189   0.03209  -0.0723   0.0415   1.0000
   9.000   1.2886   0.04309   0.03386  -0.0698   0.0449   1.0000
   9.250   1.3182   0.04778   0.03906  -0.0690   0.0503   1.0000
   9.500   1.3401   0.05071   0.04251  -0.0668   0.0551   1.0000
   9.750   1.3470   0.05533   0.04783  -0.0634   0.0608   1.0000
  10.000   1.3496   0.05943   0.05271  -0.0593   0.0697   1.0000
  10.250   1.3434   0.06554   0.05957  -0.0551   0.0830   1.0000
  10.500   1.3309   0.07684   0.07163  -0.0524   0.1114   1.0000
  10.750   1.2932   0.07885   0.07397  -0.0472   0.1100   1.0000
  11.000   1.2001   0.07199   0.06725  -0.0369   0.0906   1.0000
  11.250   1.1680   0.07671   0.07218  -0.0350   0.0907   1.0000
  11.500   1.1383   0.08197   0.07760  -0.0343   0.0904   1.0000
  11.750   1.1068   0.08774   0.08353  -0.0348   0.0902   1.0000
  12.000   1.0781   0.09391   0.08982  -0.0362   0.0897   1.0000
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