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AG455ct -02f rot. (ag455ct02r-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: AG455ct -02f rot. (ag455ct02r-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.6 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag455ct02r-il-1000000-n5.txt
Download as CSV file: xf-ag455ct02r-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4781   0.11369   0.11217   0.0179   1.0000   0.0058
 -10.000  -0.4770   0.10971   0.10820   0.0169   1.0000   0.0058
  -9.500  -0.6016   0.11350   0.11191   0.0301   1.0000   0.0058
  -9.250  -0.5978   0.10950   0.10792   0.0283   1.0000   0.0058
  -9.000  -0.5940   0.10549   0.10392   0.0265   1.0000   0.0058
  -8.500  -0.5871   0.09736   0.09582   0.0225   1.0000   0.0058
  -6.500  -0.5360   0.01904   0.01554  -0.0322   1.0000   0.0033
  -6.250  -0.5120   0.01615   0.01217  -0.0321   1.0000   0.0034
  -6.000  -0.4863   0.01464   0.01039  -0.0319   1.0000   0.0035
  -5.750  -0.4613   0.01243   0.00777  -0.0317   1.0000   0.0038
  -5.500  -0.4348   0.01167   0.00691  -0.0315   1.0000   0.0040
  -5.250  -0.4080   0.01117   0.00634  -0.0312   1.0000   0.0043
  -5.000  -0.3812   0.01068   0.00578  -0.0310   1.0000   0.0045
  -4.750  -0.3470   0.01011   0.00512  -0.0324   0.9822   0.0048
  -4.500  -0.3111   0.00961   0.00449  -0.0340   0.9358   0.0051
  -4.250  -0.2884   0.00946   0.00398  -0.0325   0.8367   0.0053
  -4.000  -0.2636   0.00936   0.00352  -0.0317   0.7561   0.0055
  -3.750  -0.2365   0.00917   0.00317  -0.0315   0.7297   0.0057
  -3.500  -0.2089   0.00891   0.00279  -0.0313   0.7154   0.0061
  -3.250  -0.1813   0.00857   0.00234  -0.0312   0.7060   0.0067
  -3.000  -0.1533   0.00833   0.00204  -0.0310   0.6967   0.0073
  -2.750  -0.1253   0.00814   0.00180  -0.0309   0.6856   0.0083
  -2.500  -0.0973   0.00796   0.00157  -0.0308   0.6724   0.0103
  -2.250  -0.0693   0.00782   0.00138  -0.0307   0.6573   0.0141
  -2.000  -0.0413   0.00769   0.00123  -0.0306   0.6405   0.0215
  -1.750  -0.0135   0.00755   0.00109  -0.0305   0.6226   0.0380
  -1.500   0.0144   0.00737   0.00098  -0.0305   0.6032   0.0712
  -1.250   0.0422   0.00724   0.00087  -0.0305   0.5829   0.1060
  -1.000   0.0700   0.00708   0.00080  -0.0305   0.5625   0.1577
  -0.750   0.0978   0.00695   0.00074  -0.0305   0.5412   0.2082
  -0.500   0.1256   0.00679   0.00070  -0.0305   0.5201   0.2747
  -0.250   0.1533   0.00664   0.00067  -0.0305   0.4980   0.3462
   0.000   0.1810   0.00647   0.00066  -0.0305   0.4767   0.4305
   0.250   0.2084   0.00624   0.00066  -0.0306   0.4545   0.5415
   0.500   0.2355   0.00599   0.00068  -0.0305   0.4329   0.6588
   0.750   0.2618   0.00577   0.00072  -0.0301   0.4108   0.7717
   1.000   0.2858   0.00557   0.00077  -0.0290   0.3896   0.8751
   1.250   0.3134   0.00548   0.00079  -0.0286   0.3684   0.9795
   1.500   0.3436   0.00562   0.00082  -0.0291   0.3458   1.0000
   1.750   0.3715   0.00577   0.00087  -0.0290   0.3254   1.0000
   2.000   0.3993   0.00592   0.00093  -0.0290   0.3051   1.0000
   2.250   0.4271   0.00608   0.00100  -0.0289   0.2854   1.0000
   2.500   0.4549   0.00624   0.00109  -0.0289   0.2662   1.0000
   2.750   0.4827   0.00642   0.00117  -0.0288   0.2467   1.0000
   3.000   0.5104   0.00660   0.00127  -0.0288   0.2285   1.0000
   3.250   0.5381   0.00678   0.00138  -0.0287   0.2105   1.0000
   3.500   0.5657   0.00699   0.00152  -0.0287   0.1918   1.0000
   4.000   0.6208   0.00740   0.00180  -0.0286   0.1589   1.0000
   4.250   0.6483   0.00761   0.00195  -0.0285   0.1450   1.0000
   4.500   0.6757   0.00785   0.00214  -0.0284   0.1286   1.0000
   4.750   0.7030   0.00808   0.00232  -0.0284   0.1163   1.0000
   5.000   0.7303   0.00834   0.00253  -0.0283   0.1021   1.0000
   5.250   0.7575   0.00859   0.00274  -0.0282   0.0911   1.0000
   5.500   0.7846   0.00887   0.00298  -0.0281   0.0788   1.0000
   5.750   0.8116   0.00916   0.00323  -0.0280   0.0683   1.0000
   6.000   0.8385   0.00947   0.00351  -0.0279   0.0573   1.0000
   6.250   0.8652   0.00980   0.00380  -0.0278   0.0477   1.0000
   6.500   0.8920   0.01012   0.00410  -0.0277   0.0398   1.0000
   6.750   0.9186   0.01046   0.00444  -0.0276   0.0333   1.0000
   7.000   0.9449   0.01085   0.00481  -0.0274   0.0259   1.0000
   7.250   0.9714   0.01120   0.00517  -0.0273   0.0221   1.0000
   7.500   0.9975   0.01161   0.00557  -0.0271   0.0176   1.0000
   7.750   1.0237   0.01199   0.00598  -0.0269   0.0151   1.0000
   8.000   1.0494   0.01246   0.00647  -0.0267   0.0117   1.0000
   8.250   1.0753   0.01286   0.00691  -0.0265   0.0104   1.0000
   8.500   1.1008   0.01334   0.00742  -0.0263   0.0089   1.0000
   8.750   1.1259   0.01389   0.00802  -0.0260   0.0075   1.0000
   9.000   1.1513   0.01434   0.00853  -0.0258   0.0069   1.0000
   9.250   1.1763   0.01485   0.00910  -0.0255   0.0061   1.0000
   9.500   1.2008   0.01545   0.00974  -0.0252   0.0053   1.0000
   9.750   1.2246   0.01617   0.01056  -0.0248   0.0046   1.0000
  10.000   1.2489   0.01674   0.01121  -0.0245   0.0044   1.0000
  10.250   1.2727   0.01737   0.01193  -0.0242   0.0041   1.0000
  10.500   1.2961   0.01805   0.01270  -0.0238   0.0038   1.0000
  10.750   1.3190   0.01878   0.01351  -0.0234   0.0035   1.0000
  11.000   1.3412   0.01959   0.01440  -0.0229   0.0032   1.0000
  11.250   1.3622   0.02056   0.01548  -0.0224   0.0029   1.0000
  11.500   1.3808   0.02191   0.01698  -0.0217   0.0027   1.0000
  11.750   1.4012   0.02283   0.01804  -0.0211   0.0026   1.0000
  12.000   1.4210   0.02378   0.01911  -0.0205   0.0025   1.0000
  12.250   1.4397   0.02482   0.02027  -0.0199   0.0024   1.0000
  12.500   1.4575   0.02593   0.02150  -0.0192   0.0023   1.0000
  12.750   1.4739   0.02711   0.02280  -0.0184   0.0021   1.0000
  13.000   1.4889   0.02838   0.02419  -0.0176   0.0020   1.0000
  13.250   1.5020   0.02977   0.02571  -0.0167   0.0019   1.0000
  13.500   1.5124   0.03132   0.02739  -0.0157   0.0018   1.0000
  13.750   1.5176   0.03311   0.02931  -0.0144   0.0017   1.0000
  14.000   1.5155   0.03527   0.03162  -0.0129   0.0017   1.0000
  14.250   1.5092   0.03842   0.03493  -0.0131   0.0017   1.0000
  14.500   1.5008   0.04308   0.03978  -0.0160   0.0016   1.0000
  14.750   1.4886   0.04903   0.04591  -0.0202   0.0016   1.0000
  15.000   1.4704   0.05650   0.05356  -0.0254   0.0016   1.0000
  15.250   1.4433   0.06586   0.06309  -0.0315   0.0016   1.0000
  15.500   1.4080   0.07678   0.07419  -0.0378   0.0017   1.0000
  15.750   1.3641   0.08925   0.08683  -0.0444   0.0017   1.0000
  16.000   1.3155   0.10268   0.10042  -0.0511   0.0018   1.0000
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