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AG13 (ag13-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: AG13 (ag13-il)
Reynolds number: 200,000
Max Cl/Cd: 58.95 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag13-il-200000-n5.txt
Download as CSV file: xf-ag13-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG13                                            
  
 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  -0.5693   0.11590   0.11242   0.0187   1.0000   0.0163
  -9.000  -0.5686   0.11080   0.10734   0.0170   1.0000   0.0166
  -8.750  -0.5652   0.10653   0.10305   0.0153   1.0000   0.0167
  -7.750  -0.5456   0.09171   0.08830   0.0110   1.0000   0.0143
  -7.500  -0.5420   0.08767   0.08429   0.0087   1.0000   0.0133
  -7.250  -0.5364   0.08297   0.07964   0.0047   1.0000   0.0124
  -7.000  -0.5270   0.07688   0.07356  -0.0019   1.0000   0.0114
  -6.250  -0.4677   0.05404   0.05053  -0.0278   1.0000   0.0097
  -6.000  -0.4443   0.04577   0.04202  -0.0350   1.0000   0.0096
  -5.500  -0.3962   0.03299   0.02846  -0.0438   1.0000   0.0111
  -5.250  -0.3712   0.03080   0.02604  -0.0449   1.0000   0.0125
  -5.000  -0.3438   0.02592   0.02055  -0.0464   1.0000   0.0127
  -4.750  -0.3159   0.02208   0.01608  -0.0470   1.0000   0.0126
  -4.500  -0.2883   0.01939   0.01286  -0.0471   1.0000   0.0127
  -4.250  -0.2609   0.01738   0.01047  -0.0469   1.0000   0.0130
  -4.000  -0.2337   0.01580   0.00862  -0.0466   1.0000   0.0137
  -3.750  -0.2067   0.01452   0.00711  -0.0463   1.0000   0.0146
  -3.500  -0.1798   0.01354   0.00598  -0.0459   1.0000   0.0159
  -3.250  -0.1532   0.01265   0.00506  -0.0458   1.0000   0.0202
  -3.000  -0.1262   0.01200   0.00430  -0.0455   1.0000   0.0244
  -2.750  -0.0991   0.01132   0.00357  -0.0452   1.0000   0.0333
  -2.500  -0.0723   0.01077   0.00307  -0.0450   1.0000   0.0563
  -2.250  -0.0457   0.01029   0.00277  -0.0449   1.0000   0.1027
  -2.000  -0.0192   0.00982   0.00256  -0.0448   1.0000   0.1679
  -1.750   0.0073   0.00941   0.00242  -0.0448   1.0000   0.2467
  -1.500   0.0337   0.00904   0.00234  -0.0447   1.0000   0.3302
  -1.250   0.0696   0.00865   0.00224  -0.0466   0.9892   0.4310
  -1.000   0.1057   0.00824   0.00218  -0.0484   0.9735   0.5392
  -0.500   0.1736   0.00700   0.00197  -0.0496   0.9286   1.0000
  -0.250   0.2074   0.00703   0.00184  -0.0504   0.8958   1.0000
   0.000   0.2374   0.00709   0.00174  -0.0504   0.8579   1.0000
   0.250   0.2642   0.00721   0.00166  -0.0496   0.8174   1.0000
   0.500   0.2899   0.00737   0.00162  -0.0487   0.7766   1.0000
   0.750   0.3156   0.00756   0.00160  -0.0478   0.7360   1.0000
   1.000   0.3415   0.00777   0.00160  -0.0471   0.6961   1.0000
   1.250   0.3676   0.00800   0.00162  -0.0465   0.6570   1.0000
   1.500   0.3939   0.00823   0.00167  -0.0459   0.6187   1.0000
   1.750   0.4203   0.00848   0.00176  -0.0455   0.5810   1.0000
   2.000   0.4467   0.00875   0.00184  -0.0450   0.5436   1.0000
   2.250   0.4733   0.00901   0.00195  -0.0447   0.5070   1.0000
   2.500   0.4999   0.00929   0.00208  -0.0443   0.4712   1.0000
   2.750   0.5265   0.00958   0.00223  -0.0441   0.4356   1.0000
   3.000   0.5531   0.00989   0.00243  -0.0438   0.4003   1.0000
   3.250   0.5796   0.01021   0.00263  -0.0435   0.3654   1.0000
   3.500   0.6062   0.01055   0.00285  -0.0433   0.3312   1.0000
   3.750   0.6327   0.01090   0.00310  -0.0431   0.2986   1.0000
   4.000   0.6592   0.01128   0.00337  -0.0429   0.2669   1.0000
   4.250   0.6856   0.01167   0.00372  -0.0427   0.2367   1.0000
   4.500   0.7119   0.01208   0.00406  -0.0425   0.2084   1.0000
   4.750   0.7381   0.01252   0.00443  -0.0422   0.1808   1.0000
   5.000   0.7642   0.01297   0.00484  -0.0420   0.1569   1.0000
   5.250   0.7901   0.01348   0.00532  -0.0418   0.1329   1.0000
   5.500   0.8160   0.01398   0.00582  -0.0415   0.1123   1.0000
   5.750   0.8416   0.01455   0.00636  -0.0413   0.0933   1.0000
   6.000   0.8672   0.01513   0.00695  -0.0410   0.0767   1.0000
   6.250   0.8924   0.01577   0.00760  -0.0407   0.0619   1.0000
   6.500   0.9175   0.01646   0.00832  -0.0403   0.0493   1.0000
   6.750   0.9422   0.01722   0.00917  -0.0399   0.0385   1.0000
   7.000   0.9664   0.01811   0.01013  -0.0395   0.0298   1.0000
   7.250   0.9898   0.01915   0.01122  -0.0390   0.0226   1.0000
   7.500   1.0135   0.02011   0.01235  -0.0384   0.0182   1.0000
   7.750   1.0339   0.02189   0.01426  -0.0376   0.0149   1.0000
   8.000   1.0568   0.02297   0.01556  -0.0369   0.0129   1.0000
   8.250   1.0792   0.02404   0.01678  -0.0364   0.0108   1.0000
   8.500   1.0990   0.02567   0.01861  -0.0356   0.0097   1.0000
   8.750   1.1138   0.02852   0.02171  -0.0344   0.0088   1.0000
   9.000   1.1314   0.03066   0.02424  -0.0334   0.0085   1.0000
   9.250   1.1464   0.03326   0.02721  -0.0322   0.0081   1.0000
   9.500   1.1582   0.03632   0.03068  -0.0310   0.0078   1.0000
   9.750   1.1658   0.03984   0.03464  -0.0298   0.0076   1.0000
  10.000   1.1680   0.04377   0.03902  -0.0287   0.0074   1.0000
  10.250   1.1640   0.04805   0.04372  -0.0277   0.0074   1.0000
  10.500   1.1522   0.05239   0.04839  -0.0270   0.0073   1.0000
  10.750   1.1356   0.05716   0.05342  -0.0280   0.0073   1.0000
  11.000   1.1181   0.06361   0.06011  -0.0327   0.0074   1.0000
  11.250   1.1006   0.07214   0.06884  -0.0404   0.0075   1.0000
  11.500   1.0813   0.08243   0.07929  -0.0490   0.0076   1.0000
  11.750   1.0589   0.09374   0.09070  -0.0568   0.0078   1.0000
  12.000   1.0344   0.10536   0.10236  -0.0635   0.0080   1.0000
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