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AG19 (ag19-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: AG19 (ag19-il)
Reynolds number: 100,000
Max Cl/Cd: 51.69 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag19-il-100000.txt
Download as CSV file: xf-ag19-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG19                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5287   0.10756   0.10274   0.0135   1.0000   0.0623
  -8.000  -0.5285   0.10524   0.10050   0.0086   1.0000   0.0642
  -7.750  -0.5268   0.10289   0.09823   0.0009   1.0000   0.0649
  -7.500  -0.5171   0.09692   0.09228   0.0063   1.0000   0.0677
  -7.250  -0.5076   0.09347   0.08884   0.0065   1.0000   0.0717
  -7.000  -0.4993   0.08996   0.08538   0.0018   1.0000   0.0757
  -6.750  -0.4774   0.08597   0.08132  -0.0193   1.0000   0.0784
  -6.500  -0.4753   0.08102   0.07650  -0.0099   1.0000   0.0806
  -6.250  -0.4633   0.07751   0.07301  -0.0092   1.0000   0.0845
  -6.000  -0.4305   0.07194   0.06723  -0.0290   1.0000   0.0923
  -5.750  -0.4262   0.06816   0.06362  -0.0217   1.0000   0.0948
  -5.500  -0.4070   0.06446   0.05984  -0.0246   1.0000   0.1023
  -5.250  -0.3853   0.05964   0.05495  -0.0296   1.0000   0.1088
  -5.000  -0.3577   0.05506   0.05019  -0.0362   1.0000   0.1206
  -4.750  -0.3402   0.05198   0.04715  -0.0355   1.0000   0.1282
  -4.500  -0.3125   0.04819   0.04316  -0.0398   1.0000   0.1444
  -4.250  -0.2909   0.04465   0.03960  -0.0407   1.0000   0.1554
  -4.000  -0.2648   0.04117   0.03596  -0.0433   1.0000   0.1763
  -3.750  -0.1996   0.02863   0.02161  -0.0517   1.0000   0.0625
  -3.500  -0.1702   0.02527   0.01777  -0.0521   1.0000   0.0603
  -3.250  -0.1407   0.02275   0.01471  -0.0521   1.0000   0.0623
  -3.000  -0.1114   0.02029   0.01178  -0.0518   1.0000   0.0621
  -2.750  -0.0827   0.01842   0.00949  -0.0511   1.0000   0.0644
  -2.500  -0.0559   0.01678   0.00777  -0.0507   1.0000   0.0756
  -2.250  -0.0286   0.01532   0.00628  -0.0500   1.0000   0.0923
  -2.000  -0.0019   0.01388   0.00516  -0.0497   1.0000   0.1396
  -1.750   0.0249   0.01174   0.00436  -0.0499   1.0000   0.3988
  -1.500   0.0429   0.00982   0.00399  -0.0464   1.0000   1.0000
  -1.250   0.0697   0.00985   0.00362  -0.0461   1.0000   1.0000
  -1.000   0.0960   0.00991   0.00341  -0.0459   1.0000   1.0000
  -0.750   0.1221   0.00998   0.00327  -0.0457   1.0000   1.0000
  -0.500   0.1478   0.01007   0.00320  -0.0454   1.0000   1.0000
  -0.250   0.1734   0.01020   0.00319  -0.0453   1.0000   1.0000
   0.000   0.1988   0.01035   0.00322  -0.0451   1.0000   1.0000
   0.250   0.2241   0.01054   0.00333  -0.0451   1.0000   1.0000
   0.500   0.2492   0.01077   0.00350  -0.0451   1.0000   1.0000
   0.750   0.2739   0.01105   0.00375  -0.0453   1.0000   1.0000
   1.000   0.2981   0.01140   0.00409  -0.0455   1.0000   1.0000
   1.250   0.3493   0.01166   0.00437  -0.0508   0.9845   1.0000
   1.500   0.4079   0.01173   0.00450  -0.0570   0.9616   1.0000
   1.750   0.4592   0.01167   0.00452  -0.0611   0.9356   1.0000
   2.000   0.5002   0.01157   0.00452  -0.0626   0.9043   1.0000
   2.250   0.5314   0.01153   0.00450  -0.0619   0.8675   1.0000
   2.500   0.5568   0.01156   0.00450  -0.0599   0.8262   1.0000
   2.750   0.5799   0.01166   0.00452  -0.0576   0.7807   1.0000
   3.000   0.6024   0.01186   0.00465  -0.0553   0.7298   1.0000
   3.250   0.6250   0.01214   0.00476  -0.0531   0.6733   1.0000
   3.500   0.6477   0.01253   0.00491  -0.0513   0.6120   1.0000
   3.750   0.6707   0.01303   0.00514  -0.0497   0.5476   1.0000
   4.000   0.6941   0.01365   0.00547  -0.0484   0.4856   1.0000
   4.250   0.7177   0.01434   0.00596  -0.0474   0.4286   1.0000
   4.500   0.7416   0.01511   0.00648  -0.0465   0.3774   1.0000
   4.750   0.7656   0.01591   0.00709  -0.0458   0.3306   1.0000
   5.000   0.7896   0.01678   0.00778  -0.0451   0.2883   1.0000
   5.250   0.8138   0.01769   0.00856  -0.0445   0.2495   1.0000
   5.500   0.8378   0.01871   0.00943  -0.0438   0.2165   1.0000
   5.750   0.8621   0.01975   0.01050  -0.0432   0.1861   1.0000
   6.000   0.8861   0.02092   0.01162  -0.0426   0.1607   1.0000
   6.250   0.9100   0.02220   0.01283  -0.0419   0.1386   1.0000
   6.500   0.9339   0.02358   0.01436  -0.0412   0.1180   1.0000
   6.750   0.9576   0.02520   0.01602  -0.0404   0.1012   1.0000
   7.000   0.9804   0.02706   0.01786  -0.0398   0.0858   1.0000
   7.250   1.0033   0.02918   0.02028  -0.0389   0.0734   1.0000
   7.500   1.0251   0.03146   0.02296  -0.0378   0.0629   1.0000
   7.750   1.0447   0.03520   0.02718  -0.0366   0.0568   1.0000
   8.000   1.0638   0.03726   0.02936  -0.0359   0.0489   1.0000
   8.250   1.0764   0.04251   0.03527  -0.0346   0.0469   1.0000
   8.500   1.0852   0.04763   0.04116  -0.0332   0.0460   1.0000
   8.750   1.0881   0.05336   0.04752  -0.0322   0.0459   1.0000
   9.000   1.0855   0.05920   0.05387  -0.0316   0.0458   1.0000
   9.250   1.0777   0.06506   0.06013  -0.0316   0.0459   1.0000
   9.500   1.0658   0.07082   0.06616  -0.0321   0.0463   1.0000
   9.750   1.0512   0.07629   0.07179  -0.0329   0.0468   1.0000
  10.000   1.0364   0.08187   0.07745  -0.0344   0.0473   1.0000
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