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AG09 (ag09-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: AG09 (ag09-il)
Reynolds number: 500,000
Max Cl/Cd: 70.68 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag09-il-500000-n5.txt
Download as CSV file: xf-ag09-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG09                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6018   0.09842   0.09622   0.0251   1.0000   0.0092
  -8.000  -0.5986   0.09441   0.09223   0.0228   1.0000   0.0092
  -7.750  -0.5952   0.09052   0.08836   0.0204   1.0000   0.0089
  -7.500  -0.5900   0.08614   0.08400   0.0166   1.0000   0.0085
  -7.250  -0.5805   0.08088   0.07875   0.0110   1.0000   0.0081
  -7.000  -0.5682   0.07467   0.07252   0.0040   1.0000   0.0077
  -6.750  -0.5525   0.06622   0.06401  -0.0054   1.0000   0.0073
  -6.500  -0.5323   0.05651   0.05418  -0.0151   1.0000   0.0070
  -6.250  -0.5086   0.04773   0.04520  -0.0226   1.0000   0.0071
  -6.000  -0.4861   0.02075   0.01659  -0.0339   1.0000   0.0075
  -5.750  -0.4604   0.01818   0.01357  -0.0341   1.0000   0.0079
  -5.500  -0.4340   0.01629   0.01132  -0.0342   1.0000   0.0082
  -5.250  -0.4072   0.01495   0.00969  -0.0341   1.0000   0.0087
  -5.000  -0.3801   0.01403   0.00857  -0.0340   1.0000   0.0094
  -4.750  -0.3530   0.01313   0.00747  -0.0339   1.0000   0.0098
  -4.500  -0.3259   0.01192   0.00605  -0.0337   1.0000   0.0103
  -4.250  -0.2988   0.01105   0.00505  -0.0335   1.0000   0.0110
  -4.000  -0.2715   0.01053   0.00447  -0.0334   1.0000   0.0120
  -3.750  -0.2441   0.01007   0.00394  -0.0332   1.0000   0.0131
  -3.500  -0.2168   0.00965   0.00346  -0.0330   1.0000   0.0143
  -3.250  -0.1895   0.00920   0.00296  -0.0328   1.0000   0.0166
  -3.000  -0.1622   0.00891   0.00267  -0.0326   1.0000   0.0196
  -2.750  -0.1350   0.00861   0.00234  -0.0324   1.0000   0.0226
  -2.500  -0.1079   0.00833   0.00209  -0.0321   1.0000   0.0286
  -2.250  -0.0807   0.00810   0.00187  -0.0319   0.9997   0.0364
  -2.000  -0.0451   0.00789   0.00168  -0.0336   0.9829   0.0465
  -1.750  -0.0103   0.00770   0.00153  -0.0350   0.9596   0.0597
  -1.500   0.0216   0.00756   0.00140  -0.0357   0.9267   0.0737
  -1.250   0.0475   0.00750   0.00128  -0.0348   0.8849   0.0882
  -1.000   0.0723   0.00750   0.00118  -0.0338   0.8413   0.1053
  -0.750   0.0979   0.00752   0.00110  -0.0331   0.7977   0.1249
  -0.250   0.1507   0.00753   0.00098  -0.0322   0.7095   0.1944
   0.000   0.1776   0.00748   0.00095  -0.0320   0.6661   0.2576
   0.250   0.2044   0.00717   0.00094  -0.0320   0.6222   0.4200
   0.500   0.2268   0.00573   0.00094  -0.0306   0.5808   1.0000
   0.750   0.2541   0.00594   0.00093  -0.0304   0.5376   1.0000
   1.000   0.2815   0.00616   0.00095  -0.0303   0.4956   1.0000
   1.250   0.3089   0.00638   0.00098  -0.0301   0.4561   1.0000
   1.500   0.3364   0.00660   0.00103  -0.0300   0.4203   1.0000
   1.750   0.3640   0.00680   0.00110  -0.0299   0.3882   1.0000
   2.000   0.3915   0.00701   0.00117  -0.0298   0.3577   1.0000
   2.250   0.4190   0.00721   0.00126  -0.0298   0.3299   1.0000
   2.500   0.4466   0.00742   0.00136  -0.0297   0.3039   1.0000
   2.750   0.4741   0.00764   0.00148  -0.0296   0.2792   1.0000
   3.000   0.5016   0.00785   0.00161  -0.0295   0.2558   1.0000
   3.250   0.5290   0.00808   0.00175  -0.0294   0.2332   1.0000
   3.500   0.5564   0.00833   0.00191  -0.0293   0.2111   1.0000
   3.750   0.5837   0.00856   0.00211  -0.0292   0.1900   1.0000
   4.000   0.6110   0.00884   0.00230  -0.0291   0.1687   1.0000
   4.250   0.6381   0.00912   0.00251  -0.0290   0.1473   1.0000
   4.500   0.6652   0.00943   0.00275  -0.0289   0.1261   1.0000
   4.750   0.6920   0.00979   0.00304  -0.0288   0.1029   1.0000
   5.000   0.7188   0.01018   0.00334  -0.0287   0.0799   1.0000
   5.250   0.7453   0.01061   0.00368  -0.0286   0.0580   1.0000
   5.500   0.7717   0.01110   0.00408  -0.0284   0.0392   1.0000
   5.750   0.7981   0.01156   0.00451  -0.0283   0.0270   1.0000
   6.000   0.8243   0.01205   0.00500  -0.0281   0.0184   1.0000
   6.250   0.8505   0.01257   0.00553  -0.0278   0.0133   1.0000
   6.500   0.8766   0.01309   0.00609  -0.0276   0.0107   1.0000
   6.750   0.9023   0.01374   0.00682  -0.0273   0.0091   1.0000
   7.000   0.9281   0.01432   0.00750  -0.0270   0.0082   1.0000
   7.250   0.9535   0.01497   0.00828  -0.0266   0.0075   1.0000
   7.500   0.9784   0.01572   0.00912  -0.0263   0.0069   1.0000
   7.750   1.0020   0.01680   0.01032  -0.0258   0.0064   1.0000
   8.000   1.0248   0.01808   0.01177  -0.0252   0.0061   1.0000
   8.250   1.0486   0.01897   0.01280  -0.0248   0.0058   1.0000
   8.500   1.0720   0.01990   0.01390  -0.0243   0.0055   1.0000
   8.750   1.0948   0.02093   0.01509  -0.0238   0.0052   1.0000
   9.000   1.1164   0.02221   0.01655  -0.0232   0.0050   1.0000
   9.250   1.1372   0.02362   0.01815  -0.0226   0.0048   1.0000
   9.500   1.1572   0.02510   0.01984  -0.0219   0.0046   1.0000
   9.750   1.1762   0.02669   0.02164  -0.0212   0.0045   1.0000
  10.000   1.1940   0.02838   0.02354  -0.0205   0.0043   1.0000
  10.250   1.2101   0.03022   0.02560  -0.0198   0.0042   1.0000
  10.500   1.2238   0.03235   0.02800  -0.0190   0.0041   1.0000
  10.750   1.2328   0.03506   0.03099  -0.0181   0.0040   1.0000
  11.000   1.2344   0.03862   0.03488  -0.0171   0.0039   1.0000
  11.250   1.2264   0.04301   0.03963  -0.0163   0.0038   1.0000
  11.500   1.2092   0.04744   0.04434  -0.0160   0.0038   1.0000
  11.750   1.1943   0.05319   0.05032  -0.0201   0.0038   1.0000
  12.000   1.1817   0.06146   0.05879  -0.0284   0.0038   1.0000
  12.250   1.1687   0.07088   0.06839  -0.0366   0.0038   1.0000
  12.500   1.1511   0.08057   0.07820  -0.0432   0.0039   1.0000
  12.750   1.1253   0.09154   0.08929  -0.0496   0.0040   1.0000
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