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AG11 (ag11-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: AG11 (ag11-il)
Reynolds number: 500,000
Max Cl/Cd: 75.71 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag11-il-500000-n5.txt
Download as CSV file: xf-ag11-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG11                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5584   0.11896   0.11666   0.0236   1.0000   0.0066
  -9.250  -0.5537   0.11523   0.11294   0.0218   1.0000   0.0066
  -8.500  -0.5414   0.10339   0.10116   0.0167   1.0000   0.0067
  -8.250  -0.5358   0.10008   0.09786   0.0165   1.0000   0.0068
  -8.000  -0.5306   0.09679   0.09459   0.0152   1.0000   0.0070
  -7.750  -0.5255   0.09349   0.09131   0.0135   1.0000   0.0071
  -7.500  -0.5205   0.09010   0.08794   0.0113   1.0000   0.0073
  -7.250  -0.5141   0.08647   0.08433   0.0083   1.0000   0.0075
  -7.000  -0.5035   0.08244   0.08031   0.0039   1.0000   0.0078
  -6.750  -0.4903   0.07828   0.07615  -0.0008   1.0000   0.0083
  -6.500  -0.4694   0.07317   0.07100  -0.0083   1.0000   0.0094
  -6.250  -0.4471   0.06803   0.06581  -0.0149   1.0000   0.0096
  -6.000  -0.4263   0.06334   0.06104  -0.0194   1.0000   0.0097
  -5.750  -0.4048   0.05888   0.05651  -0.0230   1.0000   0.0097
  -5.500  -0.3824   0.05454   0.05207  -0.0261   1.0000   0.0097
  -5.250  -0.3594   0.05032   0.04774  -0.0285   1.0000   0.0097
  -5.000  -0.3357   0.04626   0.04355  -0.0305   1.0000   0.0098
  -4.750  -0.3117   0.04237   0.03951  -0.0319   1.0000   0.0098
  -3.250  -0.1447   0.01947   0.01505  -0.0378   0.9799   0.0062
  -3.000  -0.1101   0.01659   0.01178  -0.0389   0.9668   0.0060
  -2.750  -0.0765   0.01403   0.00879  -0.0394   0.9504   0.0058
  -2.500  -0.0460   0.01215   0.00654  -0.0393   0.9296   0.0058
  -2.250  -0.0189   0.01095   0.00505  -0.0385   0.9046   0.0060
  -2.000   0.0069   0.01019   0.00407  -0.0375   0.8766   0.0064
  -1.750   0.0324   0.00955   0.00325  -0.0366   0.8466   0.0070
  -1.500   0.0583   0.00926   0.00283  -0.0360   0.8151   0.0078
  -1.250   0.0848   0.00914   0.00256  -0.0354   0.7829   0.0093
  -1.000   0.1116   0.00889   0.00214  -0.0350   0.7505   0.0104
  -0.750   0.1388   0.00870   0.00181  -0.0346   0.7186   0.0114
  -0.500   0.1662   0.00862   0.00155  -0.0343   0.6868   0.0137
  -0.250   0.1938   0.00851   0.00133  -0.0341   0.6555   0.0243
   0.000   0.2212   0.00822   0.00124  -0.0341   0.6237   0.1293
   0.250   0.2443   0.00647   0.00125  -0.0341   0.5944   0.7383
   0.500   0.2715   0.00600   0.00119  -0.0332   0.5622   1.0000
   0.750   0.2989   0.00618   0.00116  -0.0331   0.5283   1.0000
   1.000   0.3263   0.00637   0.00116  -0.0329   0.4955   1.0000
   1.250   0.3538   0.00656   0.00117  -0.0328   0.4627   1.0000
   1.500   0.3812   0.00677   0.00120  -0.0327   0.4300   1.0000
   1.750   0.4087   0.00698   0.00124  -0.0326   0.3995   1.0000
   2.000   0.4361   0.00719   0.00131  -0.0326   0.3697   1.0000
   2.250   0.4635   0.00742   0.00138  -0.0325   0.3395   1.0000
   2.500   0.4909   0.00765   0.00148  -0.0324   0.3111   1.0000
   2.750   0.5183   0.00789   0.00159  -0.0324   0.2841   1.0000
   3.000   0.5455   0.00814   0.00170  -0.0323   0.2573   1.0000
   3.250   0.5728   0.00839   0.00184  -0.0323   0.2335   1.0000
   3.500   0.6001   0.00863   0.00198  -0.0322   0.2120   1.0000
   3.750   0.6272   0.00890   0.00216  -0.0321   0.1902   1.0000
   4.000   0.6545   0.00914   0.00233  -0.0321   0.1727   1.0000
   4.250   0.6816   0.00940   0.00252  -0.0320   0.1570   1.0000
   4.500   0.7086   0.00967   0.00272  -0.0319   0.1408   1.0000
   4.750   0.7355   0.00998   0.00297  -0.0319   0.1242   1.0000
   5.000   0.7624   0.01027   0.00321  -0.0318   0.1108   1.0000
   5.250   0.7892   0.01056   0.00347  -0.0317   0.0995   1.0000
   5.500   0.8160   0.01085   0.00374  -0.0316   0.0897   1.0000
   5.750   0.8426   0.01118   0.00405  -0.0315   0.0801   1.0000
   6.000   0.8690   0.01153   0.00438  -0.0313   0.0712   1.0000
   6.250   0.8956   0.01183   0.00470  -0.0312   0.0657   1.0000
   6.500   0.9218   0.01222   0.00510  -0.0310   0.0597   1.0000
   6.750   0.9482   0.01253   0.00545  -0.0309   0.0559   1.0000
   7.000   0.9742   0.01292   0.00585  -0.0307   0.0513   1.0000
   7.250   1.0000   0.01335   0.00631  -0.0305   0.0476   1.0000
   7.500   1.0260   0.01369   0.00674  -0.0303   0.0454   1.0000
   7.750   1.0517   0.01410   0.00721  -0.0301   0.0426   1.0000
   8.000   1.0769   0.01459   0.00772  -0.0298   0.0393   1.0000
   8.250   1.1019   0.01510   0.00830  -0.0295   0.0369   1.0000
   8.500   1.1271   0.01552   0.00882  -0.0293   0.0353   1.0000
   8.750   1.1521   0.01598   0.00938  -0.0290   0.0330   1.0000
   9.000   1.1765   0.01651   0.00995  -0.0287   0.0305   1.0000
   9.250   1.1998   0.01726   0.01077  -0.0282   0.0281   1.0000
   9.500   1.2243   0.01773   0.01135  -0.0279   0.0269   1.0000
   9.750   1.2483   0.01826   0.01199  -0.0276   0.0252   1.0000
  10.000   1.2718   0.01885   0.01266  -0.0272   0.0234   1.0000
  10.250   1.2941   0.01961   0.01349  -0.0267   0.0212   1.0000
  10.500   1.3170   0.02024   0.01424  -0.0263   0.0196   1.0000
  10.750   1.3398   0.02082   0.01491  -0.0259   0.0176   1.0000
  11.000   1.3614   0.02157   0.01571  -0.0254   0.0154   1.0000
  11.250   1.3823   0.02241   0.01666  -0.0248   0.0139   1.0000
  11.500   1.4030   0.02320   0.01757  -0.0242   0.0122   1.0000
  11.750   1.4220   0.02420   0.01864  -0.0235   0.0103   1.0000
  12.000   1.4405   0.02521   0.01981  -0.0227   0.0091   1.0000
  12.250   1.4576   0.02634   0.02107  -0.0218   0.0078   1.0000
  12.500   1.4720   0.02773   0.02258  -0.0208   0.0067   1.0000
  12.750   1.4861   0.02905   0.02408  -0.0197   0.0059   1.0000
  13.000   1.4970   0.03062   0.02580  -0.0184   0.0051   1.0000
  13.250   1.5033   0.03253   0.02788  -0.0168   0.0045   1.0000
  13.500   1.5062   0.03435   0.02989  -0.0148   0.0041   1.0000
  13.750   1.5041   0.03644   0.03216  -0.0128   0.0038   1.0000
  14.000   1.4991   0.03912   0.03502  -0.0117   0.0036   1.0000
  14.250   1.4912   0.04261   0.03871  -0.0119   0.0034   1.0000
  14.500   1.4804   0.04722   0.04352  -0.0138   0.0033   1.0000
  14.750   1.4656   0.05335   0.04986  -0.0176   0.0033   1.0000
  15.000   1.4454   0.06130   0.05803  -0.0231   0.0033   1.0000
  15.250   1.4184   0.07107   0.06801  -0.0295   0.0034   1.0000
  15.500   1.3829   0.08257   0.07970  -0.0363   0.0036   1.0000
  15.750   1.3402   0.09530   0.09259  -0.0431   0.0040   1.0000
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