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AG44ct -02f (ag44ct02r-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: AG44ct -02f (ag44ct02r-il)
Reynolds number: 100,000
Max Cl/Cd: 45.73 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag44ct02r-il-100000.txt
Download as CSV file: xf-ag44ct02r-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG44ct -02f                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5530   0.11742   0.11258   0.0148   1.0000   0.0733
  -9.000  -0.5593   0.11498   0.11022   0.0090   1.0000   0.0743
  -8.750  -0.5650   0.11213   0.10746   0.0029   1.0000   0.0746
  -8.500  -0.5384   0.10549   0.10076   0.0117   1.0000   0.0790
  -8.250  -0.5330   0.10201   0.09732   0.0105   1.0000   0.0822
  -8.000  -0.5325   0.09860   0.09397   0.0072   1.0000   0.0857
  -7.750  -0.5403   0.09526   0.09072  -0.0043   1.0000   0.0878
  -7.500  -0.5343   0.08990   0.08541  -0.0059   1.0000   0.0893
  -7.250  -0.5209   0.08671   0.08223  -0.0001   1.0000   0.0929
  -7.000  -0.5125   0.08279   0.07830  -0.0037   1.0000   0.0975
  -6.750  -0.5058   0.07644   0.07189  -0.0191   1.0000   0.1028
  -6.500  -0.4937   0.07335   0.06888  -0.0134   1.0000   0.1059
  -6.250  -0.4796   0.06816   0.06340  -0.0259   1.0000   0.1163
  -6.000  -0.4670   0.06448   0.05992  -0.0212   1.0000   0.1192
  -5.750  -0.4502   0.05996   0.05518  -0.0272   1.0000   0.1309
  -5.500  -0.4350   0.05679   0.05212  -0.0250   1.0000   0.1356
  -5.250  -0.4134   0.05375   0.04861  -0.0310   1.0000   0.1575
  -5.000  -0.3984   0.04928   0.04438  -0.0292   1.0000   0.1614
  -4.750  -0.3792   0.04603   0.04106  -0.0299   1.0000   0.1760
  -4.500  -0.3281   0.03185   0.02465  -0.0360   1.0000   0.0606
  -4.250  -0.3044   0.02825   0.02075  -0.0357   1.0000   0.0586
  -4.000  -0.2786   0.02572   0.01771  -0.0350   1.0000   0.0596
  -3.750  -0.2524   0.02332   0.01487  -0.0343   1.0000   0.0600
  -3.500  -0.2258   0.02120   0.01235  -0.0334   1.0000   0.0606
  -3.250  -0.1997   0.01899   0.00998  -0.0325   1.0000   0.0635
  -3.000  -0.1741   0.01787   0.00878  -0.0318   1.0000   0.0740
  -2.750  -0.1488   0.01630   0.00729  -0.0309   1.0000   0.0872
  -2.500  -0.1243   0.01483   0.00613  -0.0302   1.0000   0.1236
  -2.250  -0.1010   0.01242   0.00511  -0.0299   1.0000   0.3607
  -2.000  -0.0883   0.01059   0.00508  -0.0251   1.0000   0.8065
  -1.750  -0.0415   0.01030   0.00459  -0.0282   1.0000   1.0000
  -1.500  -0.0185   0.01034   0.00438  -0.0276   1.0000   1.0000
  -1.250   0.0038   0.01044   0.00425  -0.0271   1.0000   1.0000
  -1.000   0.0253   0.01061   0.00425  -0.0266   1.0000   1.0000
  -0.750   0.0458   0.01087   0.00437  -0.0263   1.0000   1.0000
  -0.500   0.0728   0.01120   0.00455  -0.0274   0.9969   1.0000
  -0.250   0.1308   0.01138   0.00456  -0.0339   0.9784   1.0000
   0.000   0.1874   0.01146   0.00452  -0.0398   0.9598   1.0000
   0.250   0.2382   0.01147   0.00445  -0.0442   0.9391   1.0000
   0.500   0.2808   0.01146   0.00436  -0.0467   0.9149   1.0000
   0.750   0.3159   0.01147   0.00430  -0.0474   0.8882   1.0000
   1.000   0.3455   0.01153   0.00427  -0.0470   0.8608   1.0000
   1.250   0.3719   0.01164   0.00428  -0.0458   0.8333   1.0000
   1.500   0.3966   0.01180   0.00433  -0.0443   0.8058   1.0000
   1.750   0.4208   0.01201   0.00443  -0.0428   0.7786   1.0000
   2.000   0.4448   0.01227   0.00456  -0.0414   0.7516   1.0000
   2.250   0.4689   0.01257   0.00476  -0.0400   0.7249   1.0000
   2.500   0.4931   0.01291   0.00498  -0.0387   0.6978   1.0000
   2.750   0.5175   0.01318   0.00519  -0.0375   0.6687   1.0000
   3.000   0.5421   0.01339   0.00533  -0.0364   0.6401   1.0000
   3.250   0.5668   0.01358   0.00545  -0.0353   0.6110   1.0000
   3.500   0.5916   0.01380   0.00561  -0.0342   0.5811   1.0000
   3.750   0.6163   0.01407   0.00576  -0.0332   0.5508   1.0000
   4.000   0.6412   0.01439   0.00598  -0.0323   0.5193   1.0000
   4.250   0.6660   0.01476   0.00626  -0.0315   0.4878   1.0000
   4.500   0.6908   0.01519   0.00663  -0.0307   0.4573   1.0000
   4.750   0.7157   0.01567   0.00702  -0.0299   0.4279   1.0000
   5.000   0.7404   0.01619   0.00746  -0.0292   0.3994   1.0000
   5.250   0.7651   0.01675   0.00797  -0.0286   0.3718   1.0000
   5.500   0.7897   0.01734   0.00855  -0.0279   0.3449   1.0000
   5.750   0.8142   0.01798   0.00915  -0.0273   0.3191   1.0000
   6.000   0.8384   0.01865   0.00977  -0.0266   0.2941   1.0000
   6.250   0.8624   0.01935   0.01042  -0.0260   0.2694   1.0000
   6.500   0.8861   0.02006   0.01122  -0.0253   0.2442   1.0000
   6.750   0.9094   0.02083   0.01203  -0.0247   0.2192   1.0000
   7.000   0.9322   0.02169   0.01289  -0.0240   0.1946   1.0000
   7.250   0.9543   0.02265   0.01380  -0.0232   0.1703   1.0000
   7.500   0.9755   0.02370   0.01480  -0.0225   0.1455   1.0000
   7.750   0.9965   0.02495   0.01615  -0.0216   0.1216   1.0000
   8.000   1.0167   0.02663   0.01789  -0.0206   0.1021   1.0000
   8.250   1.0366   0.02829   0.01967  -0.0196   0.0857   1.0000
   8.500   1.0566   0.03055   0.02204  -0.0186   0.0747   1.0000
   8.750   1.0755   0.03282   0.02436  -0.0177   0.0656   1.0000
   9.000   1.0942   0.03518   0.02707  -0.0165   0.0592   1.0000
   9.250   1.1107   0.03900   0.03099  -0.0157   0.0551   1.0000
   9.500   1.1225   0.04184   0.03451  -0.0141   0.0515   1.0000
   9.750   1.1339   0.04487   0.03790  -0.0129   0.0482   1.0000
  10.000   1.1412   0.04865   0.04210  -0.0117   0.0468   1.0000
  10.250   1.1434   0.05290   0.04673  -0.0106   0.0460   1.0000
  10.500   1.1385   0.05758   0.05181  -0.0096   0.0458   1.0000
  10.750   1.1238   0.06253   0.05719  -0.0088   0.0461   1.0000
  11.000   1.0888   0.06817   0.06327  -0.0092   0.0473   1.0000
  11.250   1.0500   0.07615   0.07151  -0.0148   0.0489   1.0000
  11.500   1.0137   0.08650   0.08202  -0.0236   0.0508   1.0000
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