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AG44ct -02f (ag44ct02r-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: AG44ct -02f (ag44ct02r-il)
Reynolds number: 200,000
Max Cl/Cd: 60.6 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag44ct02r-il-200000-n5.txt
Download as CSV file: xf-ag44ct02r-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5428   0.09318   0.08977   0.0077   1.0000   0.0167
  -8.000  -0.5404   0.08921   0.08584   0.0060   1.0000   0.0154
  -7.500  -0.5385   0.07547   0.07217  -0.0066   1.0000   0.0119
  -7.250  -0.5301   0.06976   0.06645  -0.0127   1.0000   0.0117
  -7.000  -0.5189   0.06350   0.06014  -0.0190   1.0000   0.0115
  -6.750  -0.5057   0.05679   0.05331  -0.0248   1.0000   0.0113
  -6.500  -0.4909   0.04986   0.04618  -0.0295   1.0000   0.0112
  -6.250  -0.4742   0.04215   0.03811  -0.0329   1.0000   0.0116
  -5.750  -0.4381   0.03057   0.02545  -0.0354   1.0000   0.0126
  -5.500  -0.4163   0.02691   0.02125  -0.0353   1.0000   0.0125
  -5.250  -0.3935   0.02403   0.01790  -0.0349   1.0000   0.0124
  -5.000  -0.3700   0.02157   0.01501  -0.0344   1.0000   0.0125
  -4.750  -0.3459   0.01952   0.01261  -0.0338   1.0000   0.0127
  -4.500  -0.3213   0.01790   0.01076  -0.0332   1.0000   0.0130
  -4.250  -0.2965   0.01662   0.00932  -0.0326   1.0000   0.0135
  -4.000  -0.2716   0.01555   0.00812  -0.0319   1.0000   0.0142
  -3.750  -0.2466   0.01459   0.00708  -0.0313   1.0000   0.0153
  -3.500  -0.2215   0.01382   0.00621  -0.0306   1.0000   0.0169
  -3.250  -0.1966   0.01307   0.00542  -0.0301   1.0000   0.0200
  -3.000  -0.1672   0.01245   0.00475  -0.0304   0.9966   0.0236
  -2.750  -0.1288   0.01176   0.00400  -0.0327   0.9833   0.0323
  -2.500  -0.0923   0.01113   0.00346  -0.0345   0.9647   0.0588
  -2.250  -0.0560   0.01050   0.00309  -0.0364   0.9408   0.1278
  -2.000  -0.0211   0.00991   0.00284  -0.0381   0.9086   0.2266
  -1.750   0.0107   0.00932   0.00262  -0.0389   0.8702   0.3537
  -1.500   0.0372   0.00879   0.00246  -0.0384   0.8311   0.4964
  -1.250   0.0601   0.00834   0.00236  -0.0369   0.7982   0.6366
  -0.750   0.1164   0.00774   0.00221  -0.0350   0.7499   0.9442
  -0.500   0.1538   0.00782   0.00206  -0.0368   0.7303   1.0000
  -0.250   0.1801   0.00796   0.00200  -0.0363   0.7138   1.0000
   0.000   0.2067   0.00809   0.00197  -0.0359   0.6985   1.0000
   0.250   0.2336   0.00818   0.00195  -0.0356   0.6811   1.0000
   0.500   0.2603   0.00829   0.00193  -0.0352   0.6634   1.0000
   0.750   0.2872   0.00838   0.00192  -0.0348   0.6442   1.0000
   1.000   0.3139   0.00849   0.00191  -0.0344   0.6238   1.0000
   1.250   0.3406   0.00861   0.00192  -0.0341   0.6022   1.0000
   1.500   0.3671   0.00875   0.00193  -0.0337   0.5791   1.0000
   1.750   0.3937   0.00890   0.00196  -0.0333   0.5541   1.0000
   2.000   0.4203   0.00907   0.00201  -0.0329   0.5285   1.0000
   2.250   0.4467   0.00926   0.00210  -0.0325   0.5022   1.0000
   2.500   0.4731   0.00947   0.00218  -0.0322   0.4756   1.0000
   2.750   0.4996   0.00970   0.00230  -0.0319   0.4496   1.0000
   3.250   0.5524   0.01019   0.00259  -0.0313   0.3986   1.0000
   3.500   0.5788   0.01046   0.00279  -0.0310   0.3745   1.0000
   3.750   0.6051   0.01074   0.00299  -0.0307   0.3515   1.0000
   4.000   0.6315   0.01102   0.00321  -0.0305   0.3292   1.0000
   4.250   0.6578   0.01133   0.00345  -0.0302   0.3082   1.0000
   4.500   0.6840   0.01163   0.00375  -0.0299   0.2876   1.0000
   4.750   0.7102   0.01197   0.00403  -0.0297   0.2677   1.0000
   5.000   0.7363   0.01229   0.00434  -0.0294   0.2482   1.0000
   5.250   0.7623   0.01266   0.00467  -0.0292   0.2289   1.0000
   5.500   0.7882   0.01303   0.00506  -0.0289   0.2104   1.0000
   5.750   0.8139   0.01343   0.00544  -0.0287   0.1917   1.0000
   6.000   0.8394   0.01386   0.00586  -0.0284   0.1733   1.0000
   6.250   0.8649   0.01431   0.00630  -0.0281   0.1552   1.0000
   6.500   0.8901   0.01479   0.00681  -0.0278   0.1367   1.0000
   6.750   0.9149   0.01535   0.00733  -0.0275   0.1189   1.0000
   7.000   0.9396   0.01590   0.00790  -0.0272   0.1014   1.0000
   7.250   0.9639   0.01654   0.00852  -0.0268   0.0840   1.0000
   7.500   0.9876   0.01726   0.00922  -0.0264   0.0683   1.0000
   7.750   1.0109   0.01804   0.01004  -0.0260   0.0542   1.0000
   8.000   1.0338   0.01890   0.01092  -0.0255   0.0430   1.0000
   8.250   1.0559   0.01988   0.01193  -0.0250   0.0339   1.0000
   8.500   1.0782   0.02078   0.01298  -0.0244   0.0285   1.0000
   8.750   1.0983   0.02203   0.01429  -0.0236   0.0239   1.0000
   9.000   1.1197   0.02300   0.01543  -0.0230   0.0205   1.0000
   9.250   1.1388   0.02428   0.01687  -0.0222   0.0181   1.0000
   9.500   1.1546   0.02601   0.01875  -0.0211   0.0165   1.0000
   9.750   1.1724   0.02739   0.02034  -0.0202   0.0152   1.0000
  10.000   1.1895   0.02873   0.02186  -0.0193   0.0137   1.0000
  10.250   1.2053   0.03012   0.02339  -0.0185   0.0124   1.0000
  10.500   1.2153   0.03222   0.02564  -0.0172   0.0116   1.0000
  10.750   1.2231   0.03453   0.02815  -0.0158   0.0111   1.0000
  11.000   1.2311   0.03666   0.03053  -0.0144   0.0107   1.0000
  11.250   1.2344   0.03900   0.03312  -0.0129   0.0103   1.0000
  11.500   1.2333   0.04158   0.03594  -0.0113   0.0100   1.0000
  11.750   1.2293   0.04460   0.03919  -0.0106   0.0098   1.0000
  12.000   1.2232   0.04822   0.04305  -0.0111   0.0096   1.0000
  12.250   1.2157   0.05245   0.04752  -0.0127   0.0094   1.0000
  12.500   1.2066   0.05730   0.05263  -0.0152   0.0093   1.0000
  12.750   1.1955   0.06280   0.05834  -0.0183   0.0092   1.0000
  13.000   1.1819   0.06909   0.06484  -0.0221   0.0091   1.0000
  13.250   1.1663   0.07611   0.07205  -0.0265   0.0091   1.0000
  13.500   1.1481   0.08391   0.07999  -0.0314   0.0092   1.0000
  13.750   1.1281   0.09237   0.08862  -0.0365   0.0093   1.0000
  14.000   1.1056   0.10160   0.09800  -0.0419   0.0095   1.0000
  14.250   1.0824   0.11133   0.10787  -0.0474   0.0097   1.0000
  14.500   1.0577   0.12207   0.11872  -0.0535   0.0099   1.0000
  14.750   1.0312   0.13394   0.13068  -0.0599   0.0102   1.0000
  15.000   1.0021   0.14743   0.14422  -0.0669   0.0106   1.0000
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