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AG14 (ag14-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: AG14 (ag14-il)
Reynolds number: 50,000
Max Cl/Cd: 34.82 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag14-il-50000.txt
Download as CSV file: xf-ag14-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG14                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5471   0.10787   0.10137   0.0153   1.0000   0.1712
  -7.500  -0.5334   0.10277   0.09629   0.0164   1.0000   0.1777
  -7.250  -0.5383   0.10140   0.09503   0.0107   1.0000   0.1854
  -7.000  -0.5228   0.09617   0.08981   0.0138   1.0000   0.1947
  -6.500  -0.5081   0.08910   0.08287   0.0099   1.0000   0.2170
  -6.250  -0.4982   0.08552   0.07934   0.0091   1.0000   0.2321
  -6.000  -0.4882   0.08212   0.07592   0.0079   1.0000   0.2501
  -5.750  -0.4791   0.07885   0.07271   0.0040   1.0000   0.2694
  -5.500  -0.4661   0.07495   0.06886   0.0065   1.0000   0.2880
  -5.250  -0.4549   0.07159   0.06553   0.0047   1.0000   0.3118
  -5.000  -0.4427   0.06824   0.06223   0.0045   1.0000   0.3387
  -4.750  -0.4304   0.06478   0.05883   0.0064   1.0000   0.3672
  -4.500  -0.4182   0.06145   0.05556   0.0091   1.0000   0.3990
  -4.000  -0.2706   0.03995   0.03206  -0.0437   1.0000   0.1347
  -3.750  -0.2321   0.03477   0.02597  -0.0470   1.0000   0.1159
  -3.500  -0.2003   0.03135   0.02190  -0.0482   1.0000   0.1168
  -3.250  -0.1719   0.02836   0.01866  -0.0484   1.0000   0.1217
  -3.000  -0.1410   0.02561   0.01542  -0.0484   1.0000   0.1243
  -2.750  -0.1116   0.02338   0.01278  -0.0481   1.0000   0.1365
  -2.500  -0.0832   0.02148   0.01067  -0.0475   1.0000   0.1607
  -2.250  -0.0561   0.01968   0.00899  -0.0466   1.0000   0.2086
  -2.000  -0.0278   0.01735   0.00733  -0.0459   1.0000   0.3467
  -1.750  -0.0101   0.01371   0.00587  -0.0411   1.0000   1.0000
  -1.500   0.0182   0.01370   0.00516  -0.0410   1.0000   1.0000
  -1.250   0.0450   0.01370   0.00467  -0.0408   1.0000   1.0000
  -1.000   0.0712   0.01373   0.00434  -0.0405   1.0000   1.0000
  -0.750   0.0971   0.01377   0.00411  -0.0402   1.0000   1.0000
  -0.500   0.1227   0.01383   0.00395  -0.0399   1.0000   1.0000
  -0.250   0.1481   0.01391   0.00386  -0.0396   1.0000   1.0000
   0.000   0.1733   0.01401   0.00380  -0.0393   1.0000   1.0000
   0.250   0.1983   0.01414   0.00383  -0.0390   1.0000   1.0000
   0.500   0.2230   0.01430   0.00393  -0.0388   1.0000   1.0000
   0.750   0.2474   0.01450   0.00410  -0.0387   1.0000   1.0000
   1.000   0.2715   0.01474   0.00434  -0.0386   1.0000   1.0000
   1.250   0.2952   0.01505   0.00467  -0.0386   1.0000   1.0000
   1.500   0.3185   0.01545   0.00511  -0.0388   1.0000   1.0000
   1.750   0.3409   0.01598   0.00569  -0.0393   1.0000   1.0000
   2.000   0.3620   0.01668   0.00648  -0.0401   1.0000   1.0000
   2.250   0.3814   0.01766   0.00756  -0.0415   1.0000   1.0000
   2.500   0.4836   0.01826   0.00857  -0.0566   0.9439   1.0000
   2.750   0.5603   0.01809   0.00874  -0.0639   0.8852   1.0000
   3.000   0.5990   0.01804   0.00889  -0.0631   0.8253   1.0000
   3.250   0.6235   0.01821   0.00902  -0.0596   0.7678   1.0000
   3.500   0.6442   0.01858   0.00927  -0.0557   0.7112   1.0000
   3.750   0.6647   0.01909   0.00962  -0.0523   0.6551   1.0000
   4.000   0.6858   0.01973   0.01008  -0.0493   0.5996   1.0000
   4.250   0.7077   0.02050   0.01075  -0.0469   0.5447   1.0000
   4.500   0.7301   0.02139   0.01146  -0.0448   0.4907   1.0000
   4.750   0.7528   0.02241   0.01234  -0.0430   0.4384   1.0000
   5.000   0.7758   0.02354   0.01332  -0.0413   0.3898   1.0000
   5.250   0.7990   0.02481   0.01451  -0.0399   0.3443   1.0000
   5.500   0.8224   0.02620   0.01582  -0.0387   0.3031   1.0000
   5.750   0.8460   0.02780   0.01744  -0.0375   0.2676   1.0000
   6.000   0.8698   0.02966   0.01942  -0.0365   0.2361   1.0000
   6.250   0.8929   0.03154   0.02138  -0.0354   0.2072   1.0000
   6.500   0.9161   0.03411   0.02418  -0.0345   0.1850   1.0000
   6.750   0.9385   0.03632   0.02632  -0.0335   0.1623   1.0000
   7.000   0.9591   0.03981   0.03039  -0.0325   0.1467   1.0000
   7.250   0.9783   0.04357   0.03455  -0.0316   0.1339   1.0000
   7.500   0.9948   0.04716   0.03852  -0.0308   0.1207   1.0000
   7.750   1.0041   0.05329   0.04553  -0.0306   0.1179   1.0000
   8.000   1.0083   0.05996   0.05292  -0.0312   0.1175   1.0000
   8.250   1.0072   0.06690   0.06032  -0.0325   0.1181   1.0000
   8.500   1.0025   0.07387   0.06759  -0.0345   0.1193   1.0000
   8.750   0.9966   0.08065   0.07445  -0.0368   0.1206   1.0000
   9.000   0.9912   0.08723   0.08112  -0.0390   0.1216   1.0000
   9.250   0.9879   0.09366   0.08772  -0.0409   0.1225   1.0000
   9.500   0.8843   0.12445   0.11801  -0.0853   0.3004   1.0000
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