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AG13 (ag13-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: AG13 (ag13-il)
Reynolds number: 50,000
Max Cl/Cd: 34.15 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag13-il-50000.txt
Download as CSV file: xf-ag13-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5925   0.13338   0.12658   0.0214   1.0000   0.1438
  -9.250  -0.5675   0.12561   0.11877   0.0244   1.0000   0.1511
  -9.000  -0.5722   0.12399   0.11723   0.0214   1.0000   0.1565
  -8.750  -0.5612   0.11893   0.11220   0.0216   1.0000   0.1611
  -8.500  -0.5575   0.11594   0.10926   0.0204   1.0000   0.1687
  -8.250  -0.5582   0.11293   0.10634   0.0181   1.0000   0.1727
  -8.000  -0.5475   0.10889   0.10231   0.0185   1.0000   0.1819
  -7.750  -0.5457   0.10553   0.09903   0.0168   1.0000   0.1874
  -7.500  -0.5433   0.10283   0.09640   0.0153   1.0000   0.1972
  -7.250  -0.5316   0.09845   0.09205   0.0160   1.0000   0.2073
  -7.000  -0.5267   0.09503   0.08870   0.0151   1.0000   0.2179
  -6.750  -0.5202   0.09161   0.08534   0.0138   1.0000   0.2310
  -6.500  -0.5119   0.08811   0.08190   0.0130   1.0000   0.2459
  -6.250  -0.5033   0.08470   0.07854   0.0119   1.0000   0.2623
  -6.000  -0.4985   0.08193   0.07585   0.0065   1.0000   0.2813
  -5.750  -0.4851   0.07766   0.07156   0.0089   1.0000   0.2974
  -5.500  -0.4726   0.07410   0.06803   0.0096   1.0000   0.3173
  -5.250  -0.4616   0.07057   0.06456   0.0092   1.0000   0.3402
  -5.000  -0.4500   0.06720   0.06124   0.0095   1.0000   0.3669
  -4.750  -0.4377   0.06382   0.05790   0.0109   1.0000   0.3953
  -4.500  -0.3268   0.04316   0.03527  -0.0429   1.0000   0.1295
  -4.250  -0.2944   0.03769   0.02919  -0.0456   1.0000   0.1152
  -4.000  -0.2648   0.03370   0.02473  -0.0468   1.0000   0.1134
  -3.750  -0.2336   0.03029   0.02062  -0.0478   1.0000   0.1177
  -3.500  -0.2049   0.02739   0.01743  -0.0479   1.0000   0.1223
  -3.250  -0.1738   0.02483   0.01420  -0.0477   1.0000   0.1300
  -3.000  -0.1468   0.02284   0.01221  -0.0472   1.0000   0.1550
  -2.750  -0.1193   0.02078   0.01018  -0.0464   1.0000   0.1899
  -2.500  -0.0919   0.01885   0.00852  -0.0456   1.0000   0.2750
  -2.250  -0.0687   0.01647   0.00740  -0.0437   1.0000   0.4957
  -2.000  -0.0518   0.01381   0.00625  -0.0382   1.0000   1.0000
  -1.750  -0.0209   0.01377   0.00545  -0.0391   1.0000   1.0000
  -1.500   0.0066   0.01376   0.00496  -0.0392   1.0000   1.0000
  -1.250   0.0332   0.01377   0.00456  -0.0391   1.0000   1.0000
  -1.000   0.0594   0.01380   0.00430  -0.0389   1.0000   1.0000
  -0.750   0.0851   0.01385   0.00411  -0.0387   1.0000   1.0000
  -0.500   0.1106   0.01391   0.00399  -0.0384   1.0000   1.0000
  -0.250   0.1359   0.01401   0.00393  -0.0382   1.0000   1.0000
   0.000   0.1610   0.01412   0.00391  -0.0380   1.0000   1.0000
   0.250   0.1857   0.01427   0.00398  -0.0378   1.0000   1.0000
   0.500   0.2101   0.01445   0.00411  -0.0376   1.0000   1.0000
   0.750   0.2341   0.01468   0.00432  -0.0375   1.0000   1.0000
   1.000   0.2578   0.01497   0.00461  -0.0375   1.0000   1.0000
   1.250   0.2811   0.01534   0.00499  -0.0377   1.0000   1.0000
   1.500   0.3037   0.01582   0.00551  -0.0380   1.0000   1.0000
   1.750   0.3252   0.01644   0.00618  -0.0387   1.0000   1.0000
   2.000   0.3455   0.01725   0.00706  -0.0397   1.0000   1.0000
   2.250   0.3939   0.01824   0.00825  -0.0462   0.9833   1.0000
   2.500   0.4868   0.01864   0.00900  -0.0589   0.9317   1.0000
   2.750   0.5529   0.01853   0.00919  -0.0642   0.8795   1.0000
   3.000   0.5914   0.01847   0.00934  -0.0634   0.8273   1.0000
   3.250   0.6170   0.01858   0.00944  -0.0600   0.7764   1.0000
   3.500   0.6378   0.01889   0.00970  -0.0563   0.7236   1.0000
   3.750   0.6583   0.01933   0.01004  -0.0528   0.6703   1.0000
   4.000   0.6793   0.01989   0.01046  -0.0497   0.6167   1.0000
   4.250   0.7010   0.02056   0.01106  -0.0471   0.5626   1.0000
   4.500   0.7231   0.02135   0.01169  -0.0448   0.5091   1.0000
   4.750   0.7454   0.02225   0.01241  -0.0427   0.4571   1.0000
   5.000   0.7681   0.02326   0.01323  -0.0408   0.4071   1.0000
   5.250   0.7909   0.02446   0.01434  -0.0393   0.3584   1.0000
   5.500   0.8139   0.02577   0.01561  -0.0379   0.3143   1.0000
   5.750   0.8373   0.02736   0.01717  -0.0367   0.2752   1.0000
   6.000   0.8606   0.02907   0.01878  -0.0355   0.2407   1.0000
   6.250   0.8836   0.03107   0.02094  -0.0345   0.2095   1.0000
   6.500   0.9067   0.03347   0.02348  -0.0334   0.1846   1.0000
   6.750   0.9291   0.03575   0.02569  -0.0324   0.1611   1.0000
   7.000   0.9498   0.03917   0.02971  -0.0314   0.1447   1.0000
   7.250   0.9691   0.04290   0.03385  -0.0305   0.1319   1.0000
   7.500   0.9859   0.04643   0.03785  -0.0297   0.1188   1.0000
   7.750   0.9964   0.05223   0.04446  -0.0293   0.1157   1.0000
   8.000   1.0017   0.05860   0.05147  -0.0296   0.1149   1.0000
   8.250   1.0007   0.06541   0.05877  -0.0307   0.1153   1.0000
   8.500   0.9947   0.07246   0.06616  -0.0327   0.1169   1.0000
   8.750   0.9874   0.07932   0.07321  -0.0350   0.1187   1.0000
   9.000   0.9808   0.08590   0.07989  -0.0373   0.1200   1.0000
   9.250   0.9759   0.09239   0.08645  -0.0396   0.1217   1.0000
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