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AG455ct -02f rot. (ag455ct02r-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: AG455ct -02f rot. (ag455ct02r-il)
Reynolds number: 1,000,000
Max Cl/Cd: 92.94 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag455ct02r-il-1000000.txt
Download as CSV file: xf-ag455ct02r-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG455ct -02f rot.                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5889   0.10375   0.10220   0.0261   1.0000   0.0078
  -8.500  -0.5851   0.09978   0.09824   0.0240   1.0000   0.0082
  -8.250  -0.5813   0.09553   0.09401   0.0214   1.0000   0.0086
  -8.000  -0.5769   0.09118   0.08967   0.0182   1.0000   0.0089
  -7.750  -0.5720   0.08713   0.08564   0.0153   1.0000   0.0090
  -7.500  -0.5657   0.08264   0.08116   0.0109   1.0000   0.0091
  -7.250  -0.5543   0.07734   0.07586   0.0045   1.0000   0.0091
  -7.000  -0.5400   0.07157   0.07008  -0.0025   1.0000   0.0091
  -6.750  -0.5232   0.06545   0.06392  -0.0095   1.0000   0.0091
  -6.500  -0.5043   0.05908   0.05748  -0.0158   1.0000   0.0092
  -6.250  -0.4839   0.05254   0.05083  -0.0211   1.0000   0.0092
  -6.000  -0.4625   0.04587   0.04400  -0.0253   1.0000   0.0092
  -5.750  -0.4475   0.03318   0.03081  -0.0306   1.0000   0.0096
  -5.500  -0.4263   0.02909   0.02645  -0.0318   1.0000   0.0099
  -5.250  -0.4029   0.02657   0.02374  -0.0323   1.0000   0.0103
  -5.000  -0.3786   0.02399   0.02093  -0.0325   1.0000   0.0107
  -4.750  -0.3531   0.01681   0.01293  -0.0319   1.0000   0.0080
  -4.500  -0.3270   0.01256   0.00802  -0.0312   1.0000   0.0073
  -4.250  -0.3004   0.01153   0.00685  -0.0308   1.0000   0.0080
  -4.000  -0.2737   0.01077   0.00598  -0.0303   1.0000   0.0085
  -3.750  -0.2471   0.01012   0.00525  -0.0299   1.0000   0.0089
  -3.500  -0.2205   0.00957   0.00463  -0.0295   1.0000   0.0091
  -3.250  -0.1901   0.00856   0.00351  -0.0300   0.9970   0.0096
  -3.000  -0.1520   0.00783   0.00270  -0.0322   0.9824   0.0107
  -2.750  -0.1145   0.00740   0.00219  -0.0340   0.9432   0.0117
  -2.500  -0.0911   0.00739   0.00184  -0.0324   0.8426   0.0135
  -2.250  -0.0659   0.00732   0.00146  -0.0315   0.7713   0.0209
  -2.000  -0.0388   0.00712   0.00124  -0.0313   0.7414   0.0496
  -1.750  -0.0114   0.00693   0.00112  -0.0312   0.7235   0.0942
  -1.500   0.0161   0.00666   0.00103  -0.0311   0.7102   0.1664
  -1.250   0.0437   0.00640   0.00096  -0.0311   0.6987   0.2442
  -1.000   0.0713   0.00603   0.00091  -0.0312   0.6856   0.3566
  -0.750   0.0987   0.00558   0.00086  -0.0312   0.6708   0.5010
  -0.500   0.1247   0.00499   0.00083  -0.0310   0.6541   0.7033
  -0.250   0.1480   0.00456   0.00083  -0.0297   0.6360   0.8575
   0.000   0.1734   0.00436   0.00080  -0.0286   0.6160   0.9719
   0.250   0.2067   0.00444   0.00076  -0.0297   0.5932   1.0000
   0.500   0.2346   0.00454   0.00074  -0.0296   0.5702   1.0000
   0.750   0.2625   0.00465   0.00074  -0.0295   0.5466   1.0000
   1.000   0.2903   0.00478   0.00075  -0.0294   0.5223   1.0000
   1.250   0.3181   0.00490   0.00077  -0.0293   0.4977   1.0000
   1.500   0.3460   0.00504   0.00080  -0.0292   0.4727   1.0000
   1.750   0.3738   0.00518   0.00084  -0.0291   0.4481   1.0000
   2.000   0.4016   0.00534   0.00088  -0.0290   0.4234   1.0000
   2.250   0.4294   0.00551   0.00094  -0.0290   0.3983   1.0000
   2.500   0.4572   0.00567   0.00102  -0.0289   0.3738   1.0000
   2.750   0.4849   0.00585   0.00110  -0.0289   0.3493   1.0000
   3.000   0.5125   0.00604   0.00120  -0.0288   0.3255   1.0000
   3.250   0.5402   0.00624   0.00130  -0.0287   0.3013   1.0000
   3.500   0.5678   0.00644   0.00143  -0.0287   0.2779   1.0000
   3.750   0.5953   0.00665   0.00156  -0.0286   0.2562   1.0000
   4.000   0.6228   0.00689   0.00170  -0.0286   0.2324   1.0000
   4.250   0.6502   0.00711   0.00185  -0.0285   0.2124   1.0000
   4.750   0.7049   0.00762   0.00222  -0.0284   0.1715   1.0000
   5.000   0.7320   0.00791   0.00242  -0.0283   0.1510   1.0000
   5.250   0.7592   0.00818   0.00264  -0.0282   0.1343   1.0000
   5.500   0.7863   0.00846   0.00288  -0.0281   0.1177   1.0000
   5.750   0.8133   0.00876   0.00313  -0.0280   0.1029   1.0000
   6.000   0.8401   0.00909   0.00340  -0.0279   0.0883   1.0000
   6.250   0.8668   0.00943   0.00368  -0.0278   0.0751   1.0000
   6.500   0.8935   0.00978   0.00400  -0.0277   0.0628   1.0000
   6.750   0.9200   0.01014   0.00434  -0.0276   0.0523   1.0000
   7.000   0.9464   0.01053   0.00470  -0.0274   0.0425   1.0000
   7.250   0.9726   0.01096   0.00511  -0.0272   0.0340   1.0000
   7.500   0.9983   0.01150   0.00562  -0.0270   0.0258   1.0000
   7.750   1.0245   0.01187   0.00601  -0.0268   0.0219   1.0000
   8.000   1.0500   0.01246   0.00664  -0.0265   0.0172   1.0000
   8.250   1.0757   0.01292   0.00712  -0.0263   0.0147   1.0000
   8.500   1.0998   0.01382   0.00812  -0.0259   0.0116   1.0000
   8.750   1.1254   0.01425   0.00861  -0.0256   0.0107   1.0000
   9.000   1.1504   0.01477   0.00918  -0.0254   0.0095   1.0000
   9.250   1.1736   0.01571   0.01019  -0.0249   0.0080   1.0000
   9.500   1.1963   0.01671   0.01134  -0.0244   0.0073   1.0000
   9.750   1.2204   0.01734   0.01207  -0.0240   0.0068   1.0000
  10.000   1.2437   0.01809   0.01292  -0.0236   0.0063   1.0000
  10.250   1.2665   0.01888   0.01379  -0.0232   0.0058   1.0000
  10.500   1.2882   0.01984   0.01484  -0.0227   0.0054   1.0000
  10.750   1.3044   0.02174   0.01695  -0.0217   0.0049   1.0000
  11.000   1.3173   0.02406   0.01953  -0.0205   0.0046   1.0000
  11.250   1.3375   0.02499   0.02057  -0.0200   0.0044   1.0000
  11.500   1.3563   0.02608   0.02179  -0.0193   0.0042   1.0000
  11.750   1.3735   0.02730   0.02315  -0.0186   0.0040   1.0000
  12.000   1.3898   0.02854   0.02453  -0.0179   0.0037   1.0000
  12.250   1.4042   0.02991   0.02601  -0.0171   0.0035   1.0000
  12.500   1.4166   0.03139   0.02761  -0.0163   0.0033   1.0000
  12.750   1.4243   0.03326   0.02962  -0.0153   0.0032   1.0000
  13.000   1.4227   0.03551   0.03202  -0.0138   0.0031   1.0000
  13.250   1.4144   0.03878   0.03546  -0.0138   0.0031   1.0000
  13.500   1.4043   0.04379   0.04067  -0.0171   0.0030   1.0000
  13.750   1.3914   0.05013   0.04719  -0.0218   0.0030   1.0000
  14.000   1.3748   0.05759   0.05483  -0.0272   0.0030   1.0000
  14.250   1.3545   0.06587   0.06328  -0.0326   0.0031   1.0000
  14.500   1.3306   0.07479   0.07235  -0.0379   0.0031   1.0000
  14.750   1.3038   0.08415   0.08185  -0.0429   0.0031   1.0000
  15.000   1.2735   0.09415   0.09198  -0.0480   0.0032   1.0000
  15.250   1.2374   0.10538   0.10336  -0.0536   0.0033   1.0000
  15.500   1.2063   0.11610   0.11420  -0.0589   0.0034   1.0000
  15.750   1.1717   0.12810   0.12632  -0.0648   0.0035   1.0000
  16.000   1.1385   0.14057   0.13889  -0.0711   0.0037   1.0000
  16.250   1.0998   0.15541   0.15387  -0.0786   0.0039   1.0000
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