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AG17 (ag17-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: AG17 (ag17-il)
Reynolds number: 200,000
Max Cl/Cd: 60.36 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag17-il-200000-n5.txt
Download as CSV file: xf-ag17-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG17                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4448   0.10014   0.09678   0.0040   1.0000   0.0136
  -9.000  -0.4444   0.09580   0.09246   0.0028   1.0000   0.0129
  -8.750  -0.5515   0.10356   0.10009   0.0134   1.0000   0.0142
  -8.250  -0.5456   0.09518   0.09173   0.0094   1.0000   0.0124
  -8.000  -0.5441   0.09042   0.08704   0.0067   1.0000   0.0116
  -7.750  -0.5477   0.08304   0.07974   0.0013   1.0000   0.0103
  -7.500  -0.5396   0.07758   0.07432  -0.0038   1.0000   0.0099
  -7.000  -0.5159   0.06602   0.06274  -0.0169   1.0000   0.0095
  -6.750  -0.4995   0.05809   0.05475  -0.0262   1.0000   0.0094
  -6.500  -0.4792   0.04837   0.04482  -0.0358   1.0000   0.0093
  -6.250  -0.4583   0.03874   0.03474  -0.0429   1.0000   0.0092
  -6.000  -0.4352   0.03165   0.02698  -0.0469   1.0000   0.0093
  -5.750  -0.4111   0.02659   0.02123  -0.0490   1.0000   0.0103
  -5.500  -0.3866   0.02527   0.01972  -0.0496   1.0000   0.0116
  -5.250  -0.3606   0.02280   0.01682  -0.0499   1.0000   0.0124
  -5.000  -0.3339   0.02013   0.01365  -0.0500   1.0000   0.0126
  -4.750  -0.3072   0.01811   0.01127  -0.0498   1.0000   0.0130
  -4.500  -0.2806   0.01651   0.00939  -0.0495   1.0000   0.0136
  -4.250  -0.2541   0.01520   0.00789  -0.0491   1.0000   0.0145
  -4.000  -0.2276   0.01417   0.00671  -0.0488   1.0000   0.0156
  -3.750  -0.2013   0.01311   0.00553  -0.0486   1.0000   0.0187
  -3.500  -0.1749   0.01255   0.00492  -0.0483   1.0000   0.0235
  -3.250  -0.1481   0.01181   0.00409  -0.0480   1.0000   0.0302
  -3.000  -0.1216   0.01128   0.00358  -0.0478   1.0000   0.0493
  -2.750  -0.0952   0.01074   0.00322  -0.0476   1.0000   0.0880
  -2.500  -0.0689   0.01027   0.00297  -0.0476   1.0000   0.1431
  -2.250  -0.0426   0.00987   0.00277  -0.0476   1.0000   0.2077
  -2.000  -0.0076   0.00950   0.00263  -0.0493   0.9935   0.2820
  -1.750   0.0294   0.00919   0.00251  -0.0514   0.9824   0.3509
  -1.500   0.0655   0.00889   0.00241  -0.0532   0.9692   0.4202
  -1.250   0.1005   0.00861   0.00231  -0.0546   0.9535   0.4902
  -1.000   0.1337   0.00832   0.00223  -0.0555   0.9344   0.5629
  -0.750   0.1646   0.00799   0.00216  -0.0558   0.9129   0.6487
  -0.500   0.1894   0.00757   0.00208  -0.0544   0.8879   0.7705
  -0.250   0.2212   0.00720   0.00192  -0.0541   0.8607   1.0000
   0.000   0.2483   0.00728   0.00184  -0.0535   0.8312   1.0000
   0.250   0.2747   0.00739   0.00178  -0.0528   0.8006   1.0000
   0.500   0.3009   0.00752   0.00175  -0.0521   0.7692   1.0000
   0.750   0.3272   0.00768   0.00173  -0.0514   0.7377   1.0000
   1.000   0.3535   0.00786   0.00173  -0.0508   0.7060   1.0000
   1.250   0.3800   0.00804   0.00175  -0.0503   0.6731   1.0000
   1.500   0.4064   0.00825   0.00179  -0.0498   0.6397   1.0000
   1.750   0.4330   0.00847   0.00187  -0.0493   0.6053   1.0000
   2.000   0.4595   0.00871   0.00194  -0.0489   0.5704   1.0000
   2.250   0.4861   0.00896   0.00204  -0.0485   0.5347   1.0000
   2.500   0.5126   0.00923   0.00217  -0.0482   0.4993   1.0000
   2.750   0.5391   0.00952   0.00234  -0.0479   0.4635   1.0000
   3.000   0.5657   0.00983   0.00252  -0.0476   0.4284   1.0000
   3.250   0.5922   0.01015   0.00271  -0.0473   0.3940   1.0000
   3.500   0.6187   0.01048   0.00293  -0.0471   0.3603   1.0000
   3.750   0.6451   0.01084   0.00317  -0.0468   0.3273   1.0000
   4.250   0.6979   0.01160   0.00378  -0.0464   0.2653   1.0000
   4.500   0.7241   0.01200   0.00411  -0.0462   0.2362   1.0000
   4.750   0.7503   0.01243   0.00447  -0.0460   0.2085   1.0000
   5.000   0.7763   0.01288   0.00486  -0.0458   0.1816   1.0000
   5.250   0.8022   0.01336   0.00533  -0.0455   0.1564   1.0000
   5.500   0.8279   0.01389   0.00580  -0.0453   0.1319   1.0000
   5.750   0.8535   0.01443   0.00632  -0.0450   0.1104   1.0000
   6.000   0.8788   0.01503   0.00688  -0.0447   0.0894   1.0000
   6.250   0.9039   0.01568   0.00751  -0.0444   0.0717   1.0000
   6.500   0.9285   0.01642   0.00826  -0.0441   0.0558   1.0000
   6.750   0.9530   0.01720   0.00907  -0.0437   0.0439   1.0000
   7.000   0.9769   0.01807   0.00996  -0.0432   0.0330   1.0000
   7.250   1.0010   0.01890   0.01092  -0.0427   0.0257   1.0000
   7.500   1.0240   0.01995   0.01207  -0.0421   0.0199   1.0000
   7.750   1.0464   0.02112   0.01336  -0.0414   0.0162   1.0000
   8.000   1.0671   0.02258   0.01499  -0.0406   0.0133   1.0000
   8.250   1.0893   0.02365   0.01623  -0.0400   0.0111   1.0000
   8.500   1.1095   0.02508   0.01789  -0.0392   0.0098   1.0000
   8.750   1.1261   0.02720   0.02021  -0.0381   0.0089   1.0000
   9.000   1.1412   0.02969   0.02297  -0.0368   0.0084   1.0000
   9.250   1.1570   0.03194   0.02554  -0.0356   0.0080   1.0000
   9.500   1.1702   0.03458   0.02853  -0.0343   0.0077   1.0000
   9.750   1.1800   0.03761   0.03195  -0.0329   0.0075   1.0000
  10.000   1.1856   0.04100   0.03574  -0.0314   0.0073   1.0000
  10.250   1.1865   0.04456   0.03970  -0.0300   0.0071   1.0000
  10.500   1.1828   0.04814   0.04361  -0.0288   0.0069   1.0000
  10.750   1.1719   0.05170   0.04745  -0.0275   0.0067   1.0000
  11.000   1.1570   0.05621   0.05222  -0.0282   0.0067   1.0000
  11.250   1.1410   0.06193   0.05819  -0.0315   0.0067   1.0000
  11.500   1.1208   0.06992   0.06642  -0.0376   0.0069   1.0000
  11.750   1.0998   0.07954   0.07623  -0.0454   0.0071   1.0000
  12.000   1.0772   0.09037   0.08721  -0.0533   0.0073   1.0000
  12.250   1.0540   0.10158   0.09851  -0.0604   0.0075   1.0000
  12.500   1.0295   0.11312   0.11010  -0.0668   0.0078   1.0000
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