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AG11 (ag11-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AG11 (ag11-il)
Reynolds number: 500,000
Max Cl/Cd: 77.82 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag11-il-500000.txt
Download as CSV file: xf-ag11-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5258   0.09818   0.09599   0.0111   1.0000   0.0098
  -7.750  -0.5205   0.09439   0.09223   0.0083   1.0000   0.0098
  -7.500  -0.5189   0.08917   0.08703   0.0055   1.0000   0.0100
  -7.250  -0.5116   0.08557   0.08344   0.0045   1.0000   0.0102
  -7.000  -0.5014   0.08189   0.07977   0.0018   1.0000   0.0104
  -6.750  -0.4892   0.07809   0.07596  -0.0018   1.0000   0.0107
  -6.500  -0.4748   0.07411   0.07197  -0.0059   1.0000   0.0112
  -6.250  -0.4579   0.06986   0.06770  -0.0105   1.0000   0.0117
  -6.000  -0.4388   0.06543   0.06322  -0.0152   1.0000   0.0121
  -5.750  -0.4177   0.06094   0.05867  -0.0196   1.0000   0.0125
  -5.500  -0.3943   0.05646   0.05411  -0.0236   1.0000   0.0130
  -5.250  -0.3663   0.05198   0.04950  -0.0275   1.0000   0.0136
  -5.000  -0.3361   0.04808   0.04542  -0.0302   1.0000   0.0140
  -4.750  -0.3101   0.04450   0.04168  -0.0317   1.0000   0.0141
  -4.500  -0.2850   0.04096   0.03796  -0.0327   1.0000   0.0142
  -4.250  -0.2659   0.03500   0.03179  -0.0344   1.0000   0.0147
  -4.000  -0.2446   0.03243   0.02912  -0.0348   1.0000   0.0152
  -3.750  -0.2217   0.03010   0.02668  -0.0350   1.0000   0.0159
  -3.500  -0.1976   0.02777   0.02419  -0.0348   1.0000   0.0168
  -3.250  -0.1728   0.02549   0.02172  -0.0342   1.0000   0.0182
  -3.000  -0.1456   0.02483   0.02080  -0.0326   1.0000   0.0203
  -2.750  -0.1227   0.02085   0.01640  -0.0321   1.0000   0.0213
  -2.500  -0.0926   0.01872   0.01418  -0.0334   0.9979   0.0229
  -2.250  -0.0534   0.01714   0.01242  -0.0357   0.9939   0.0256
  -2.000  -0.0138   0.01551   0.01039  -0.0375   0.9882   0.0311
  -1.750   0.0267   0.01191   0.00629  -0.0379   0.9828   0.0147
  -1.500   0.0630   0.01074   0.00502  -0.0391   0.9720   0.0140
  -1.250   0.0969   0.00930   0.00347  -0.0400   0.9578   0.0151
  -1.000   0.1268   0.00895   0.00314  -0.0401   0.9366   0.0186
  -0.750   0.1533   0.00846   0.00257  -0.0393   0.9114   0.0195
  -0.500   0.1787   0.00805   0.00202  -0.0382   0.8830   0.0214
  -0.250   0.2045   0.00738   0.00153  -0.0373   0.8530   0.1238
   0.000   0.2264   0.00492   0.00147  -0.0362   0.8228   1.0000
   0.250   0.2524   0.00505   0.00137  -0.0354   0.7891   1.0000
   0.500   0.2787   0.00521   0.00130  -0.0348   0.7551   1.0000
   0.750   0.3053   0.00537   0.00126  -0.0343   0.7197   1.0000
   1.000   0.3321   0.00555   0.00123  -0.0339   0.6852   1.0000
   1.250   0.3591   0.00573   0.00123  -0.0336   0.6497   1.0000
   1.500   0.3861   0.00593   0.00124  -0.0333   0.6135   1.0000
   1.750   0.4133   0.00613   0.00127  -0.0331   0.5767   1.0000
   2.000   0.4404   0.00635   0.00131  -0.0329   0.5389   1.0000
   2.250   0.4675   0.00659   0.00137  -0.0327   0.4994   1.0000
   2.500   0.4946   0.00685   0.00146  -0.0326   0.4599   1.0000
   2.750   0.5217   0.00711   0.00155  -0.0325   0.4214   1.0000
   3.000   0.5487   0.00740   0.00166  -0.0324   0.3837   1.0000
   3.250   0.5758   0.00768   0.00179  -0.0323   0.3492   1.0000
   3.500   0.6029   0.00797   0.00194  -0.0322   0.3171   1.0000
   3.750   0.6300   0.00826   0.00211  -0.0321   0.2859   1.0000
   4.000   0.6570   0.00855   0.00229  -0.0321   0.2588   1.0000
   4.250   0.6840   0.00885   0.00248  -0.0320   0.2336   1.0000
   4.500   0.7109   0.00916   0.00268  -0.0319   0.2087   1.0000
   4.750   0.7377   0.00948   0.00294  -0.0318   0.1846   1.0000
   5.000   0.7644   0.00984   0.00319  -0.0317   0.1631   1.0000
   5.250   0.7911   0.01017   0.00346  -0.0316   0.1434   1.0000
   5.500   0.8175   0.01057   0.00377  -0.0315   0.1247   1.0000
   5.750   0.8438   0.01096   0.00413  -0.0314   0.1083   1.0000
   6.000   0.8701   0.01138   0.00450  -0.0312   0.0947   1.0000
   6.250   0.8960   0.01187   0.00494  -0.0310   0.0838   1.0000
   6.500   0.9223   0.01224   0.00536  -0.0308   0.0767   1.0000
   6.750   0.9479   0.01275   0.00588  -0.0306   0.0699   1.0000
   7.000   0.9740   0.01314   0.00631  -0.0304   0.0647   1.0000
   7.250   0.9984   0.01390   0.00708  -0.0300   0.0593   1.0000
   7.500   1.0243   0.01427   0.00754  -0.0297   0.0565   1.0000
   7.750   1.0498   0.01473   0.00807  -0.0295   0.0530   1.0000
   8.000   1.0724   0.01576   0.00914  -0.0289   0.0483   1.0000
   8.250   1.0978   0.01619   0.00967  -0.0286   0.0465   1.0000
   8.500   1.1226   0.01670   0.01029  -0.0282   0.0440   1.0000
   8.750   1.1473   0.01721   0.01087  -0.0279   0.0413   1.0000
   9.000   1.1674   0.01863   0.01237  -0.0271   0.0378   1.0000
   9.250   1.1913   0.01924   0.01310  -0.0267   0.0365   1.0000
   9.500   1.2156   0.01972   0.01371  -0.0263   0.0344   1.0000
   9.750   1.2391   0.02030   0.01439  -0.0259   0.0323   1.0000
  10.000   1.2611   0.02109   0.01523  -0.0254   0.0301   1.0000
  10.250   1.2785   0.02277   0.01707  -0.0244   0.0278   1.0000
  10.500   1.3031   0.02297   0.01743  -0.0241   0.0261   1.0000
  10.750   1.3272   0.02320   0.01771  -0.0239   0.0238   1.0000
  11.000   1.3469   0.02411   0.01867  -0.0233   0.0214   1.0000
  11.250   1.3653   0.02525   0.01997  -0.0224   0.0198   1.0000
  11.500   1.3881   0.02561   0.02044  -0.0221   0.0178   1.0000
  11.750   1.4093   0.02615   0.02100  -0.0217   0.0158   1.0000
  12.000   1.4222   0.02780   0.02282  -0.0204   0.0140   1.0000
  12.250   1.4413   0.02857   0.02375  -0.0198   0.0124   1.0000
  12.500   1.4550   0.02988   0.02514  -0.0188   0.0107   1.0000
  12.750   1.4605   0.03200   0.02747  -0.0171   0.0095   1.0000
  13.000   1.4688   0.03360   0.02924  -0.0156   0.0084   1.0000
  13.250   1.4697   0.03542   0.03119  -0.0136   0.0077   1.0000
  13.500   1.4602   0.03837   0.03430  -0.0119   0.0072   1.0000
  13.750   1.4439   0.04281   0.03894  -0.0123   0.0070   1.0000
  14.000   1.4252   0.04883   0.04519  -0.0153   0.0068   1.0000
  14.250   1.4087   0.05568   0.05225  -0.0198   0.0067   1.0000
  14.500   1.3901   0.06358   0.06034  -0.0252   0.0067   1.0000
  14.750   1.3703   0.07189   0.06883  -0.0305   0.0068   1.0000
  15.000   1.3503   0.08024   0.07733  -0.0353   0.0069   1.0000
  15.250   1.3312   0.08826   0.08549  -0.0396   0.0071   1.0000
  15.500   1.3083   0.09694   0.09431  -0.0440   0.0073   1.0000
  15.750   1.2825   0.10609   0.10361  -0.0485   0.0076   1.0000
  16.000   1.2519   0.11626   0.11392  -0.0534   0.0080   1.0000
  16.250   1.2214   0.12704   0.12483  -0.0589   0.0084   1.0000
  16.500   1.1922   0.13803   0.13593  -0.0646   0.0089   1.0000
  16.750   1.1648   0.14925   0.14723  -0.0705   0.0094   1.0000
  17.000   1.1377   0.16100   0.15906  -0.0768   0.0098   1.0000
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