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AG19 (ag19-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: AG19 (ag19-il)
Reynolds number: 1,000,000
Max Cl/Cd: 90.93 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag19-il-1000000-n5.txt
Download as CSV file: xf-ag19-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5721   0.12191   0.12028   0.0273   1.0000   0.0055
  -9.500  -0.5669   0.11817   0.11654   0.0256   1.0000   0.0055
  -7.000  -0.5134   0.07577   0.07425  -0.0010   1.0000   0.0029
  -6.750  -0.4974   0.06987   0.06835  -0.0084   1.0000   0.0028
  -6.500  -0.4770   0.06328   0.06173  -0.0170   1.0000   0.0028
  -6.250  -0.4517   0.05549   0.05387  -0.0269   1.0000   0.0027
  -6.000  -0.4210   0.04521   0.04342  -0.0382   1.0000   0.0027
  -5.750  -0.3849   0.01718   0.01376  -0.0527   1.0000   0.0030
  -5.500  -0.3582   0.01346   0.00940  -0.0534   1.0000   0.0035
  -5.250  -0.3315   0.01271   0.00852  -0.0533   1.0000   0.0037
  -5.000  -0.3047   0.01197   0.00766  -0.0532   1.0000   0.0039
  -4.750  -0.2780   0.01126   0.00682  -0.0530   1.0000   0.0041
  -4.500  -0.2512   0.01048   0.00591  -0.0528   1.0000   0.0043
  -4.250  -0.2223   0.00980   0.00511  -0.0530   0.9983   0.0045
  -4.000  -0.1888   0.00935   0.00458  -0.0542   0.9918   0.0050
  -3.750  -0.1547   0.00878   0.00391  -0.0556   0.9815   0.0053
  -3.500  -0.1212   0.00814   0.00315  -0.0566   0.9648   0.0054
  -3.250  -0.0909   0.00770   0.00257  -0.0569   0.9375   0.0055
  -3.000  -0.0649   0.00745   0.00216  -0.0562   0.9045   0.0057
  -2.750  -0.0389   0.00715   0.00166  -0.0554   0.8721   0.0069
  -2.500  -0.0124   0.00704   0.00142  -0.0549   0.8408   0.0090
  -2.250   0.0145   0.00696   0.00122  -0.0545   0.8101   0.0127
  -2.000   0.0417   0.00690   0.00107  -0.0542   0.7808   0.0201
  -1.750   0.0691   0.00681   0.00094  -0.0540   0.7532   0.0365
  -1.500   0.0966   0.00672   0.00083  -0.0538   0.7260   0.0607
  -1.250   0.1242   0.00665   0.00074  -0.0537   0.6987   0.0914
  -1.000   0.1519   0.00657   0.00067  -0.0536   0.6704   0.1305
  -0.750   0.1795   0.00650   0.00063  -0.0536   0.6399   0.1775
  -0.500   0.2071   0.00647   0.00060  -0.0535   0.6066   0.2215
  -0.250   0.2347   0.00643   0.00058  -0.0535   0.5719   0.2789
   0.000   0.2622   0.00638   0.00058  -0.0535   0.5351   0.3469
   0.250   0.2897   0.00635   0.00061  -0.0535   0.4984   0.4186
   0.500   0.3172   0.00634   0.00065  -0.0535   0.4616   0.4912
   0.750   0.3445   0.00632   0.00070  -0.0535   0.4239   0.5730
   1.000   0.3716   0.00621   0.00077  -0.0534   0.3906   0.6808
   1.500   0.4226   0.00580   0.00087  -0.0521   0.3325   1.0000
   1.750   0.4503   0.00599   0.00094  -0.0520   0.3053   1.0000
   2.000   0.4779   0.00618   0.00102  -0.0520   0.2800   1.0000
   2.250   0.5054   0.00637   0.00110  -0.0519   0.2565   1.0000
   2.500   0.5330   0.00656   0.00120  -0.0518   0.2351   1.0000
   2.750   0.5605   0.00676   0.00130  -0.0517   0.2132   1.0000
   3.000   0.5881   0.00694   0.00143  -0.0516   0.1961   1.0000
   3.250   0.6154   0.00717   0.00157  -0.0515   0.1749   1.0000
   3.500   0.6428   0.00738   0.00170  -0.0514   0.1575   1.0000
   3.750   0.6701   0.00760   0.00186  -0.0513   0.1410   1.0000
   4.000   0.6973   0.00786   0.00203  -0.0512   0.1226   1.0000
   4.250   0.7245   0.00809   0.00223  -0.0511   0.1096   1.0000
   4.500   0.7516   0.00834   0.00243  -0.0509   0.0949   1.0000
   4.750   0.7787   0.00860   0.00265  -0.0508   0.0822   1.0000
   5.000   0.8056   0.00887   0.00288  -0.0507   0.0713   1.0000
   5.250   0.8325   0.00917   0.00313  -0.0505   0.0595   1.0000
   5.500   0.8593   0.00945   0.00341  -0.0503   0.0510   1.0000
   5.750   0.8860   0.00975   0.00369  -0.0502   0.0423   1.0000
   6.000   0.9125   0.01009   0.00400  -0.0500   0.0340   1.0000
   6.250   0.9388   0.01047   0.00435  -0.0498   0.0255   1.0000
   6.500   0.9651   0.01085   0.00471  -0.0496   0.0197   1.0000
   6.750   0.9913   0.01122   0.00509  -0.0493   0.0150   1.0000
   7.000   1.0172   0.01167   0.00555  -0.0491   0.0109   1.0000
   7.250   1.0431   0.01208   0.00599  -0.0488   0.0082   1.0000
   7.500   1.0685   0.01262   0.00654  -0.0485   0.0054   1.0000
   7.750   1.0942   0.01304   0.00701  -0.0482   0.0045   1.0000
   8.000   1.1194   0.01357   0.00757  -0.0479   0.0036   1.0000
   8.250   1.1441   0.01425   0.00833  -0.0475   0.0028   1.0000
   8.500   1.1692   0.01476   0.00893  -0.0472   0.0026   1.0000
   8.750   1.1939   0.01534   0.00962  -0.0468   0.0024   1.0000
   9.000   1.2182   0.01597   0.01034  -0.0464   0.0021   1.0000
   9.250   1.2422   0.01664   0.01110  -0.0459   0.0019   1.0000
   9.500   1.2658   0.01738   0.01193  -0.0455   0.0017   1.0000
   9.750   1.2885   0.01826   0.01292  -0.0449   0.0015   1.0000
  10.000   1.3080   0.01983   0.01472  -0.0440   0.0013   1.0000
  10.250   1.3290   0.02093   0.01597  -0.0433   0.0012   1.0000
  10.500   1.3497   0.02201   0.01720  -0.0426   0.0012   1.0000
  10.750   1.3692   0.02325   0.01860  -0.0418   0.0011   1.0000
  11.000   1.3872   0.02466   0.02020  -0.0409   0.0011   1.0000
  11.250   1.4036   0.02625   0.02202  -0.0399   0.0011   1.0000
  11.500   1.4177   0.02806   0.02404  -0.0388   0.0010   1.0000
  11.750   1.4292   0.03009   0.02630  -0.0375   0.0010   1.0000
  12.000   1.4371   0.03241   0.02886  -0.0361   0.0010   1.0000
  12.250   1.4412   0.03495   0.03164  -0.0345   0.0010   1.0000
  12.500   1.4389   0.03777   0.03469  -0.0326   0.0010   1.0000
  12.750   1.4278   0.04076   0.03788  -0.0304   0.0010   1.0000
  13.000   1.4124   0.04499   0.04232  -0.0307   0.0010   1.0000
  13.250   1.3953   0.05113   0.04866  -0.0343   0.0010   1.0000
  13.500   1.3753   0.06000   0.05774  -0.0416   0.0010   1.0000
  13.750   1.3480   0.07215   0.07009  -0.0509   0.0010   1.0000
  14.000   1.3151   0.08466   0.08273  -0.0583   0.0010   1.0000
  14.250   1.2810   0.09643   0.09459  -0.0643   0.0010   1.0000
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