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AG45ct -02f (ag45ct02r-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: AG45ct -02f (ag45ct02r-il)
Reynolds number: 50,000
Max Cl/Cd: 30.34 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag45ct02r-il-50000.txt
Download as CSV file: xf-ag45ct02r-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG45ct -02f                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5841   0.12050   0.11399   0.0207   1.0000   0.1762
  -8.500  -0.5584   0.11376   0.10722   0.0238   1.0000   0.1857
  -8.250  -0.5766   0.11325   0.10686   0.0185   1.0000   0.1903
  -8.000  -0.5526   0.10710   0.10063   0.0215   1.0000   0.2014
  -7.750  -0.5483   0.10332   0.09693   0.0207   1.0000   0.2086
  -7.500  -0.5575   0.10161   0.09533   0.0170   1.0000   0.2181
  -7.250  -0.5431   0.09700   0.09074   0.0185   1.0000   0.2304
  -7.000  -0.5363   0.09335   0.08716   0.0184   1.0000   0.2436
  -6.750  -0.5327   0.09011   0.08398   0.0166   1.0000   0.2591
  -6.500  -0.5315   0.08700   0.08096   0.0131   1.0000   0.2755
  -6.250  -0.5138   0.08265   0.07664   0.0177   1.0000   0.2957
  -5.750  -0.4968   0.07589   0.06999   0.0181   1.0000   0.3415
  -5.500  -0.4866   0.07243   0.06659   0.0194   1.0000   0.3671
  -5.250  -0.4786   0.06941   0.06364   0.0205   1.0000   0.4003
  -5.000  -0.4676   0.06606   0.06032   0.0236   1.0000   0.4345
  -4.750  -0.4026   0.05154   0.04475  -0.0237   1.0000   0.2189
  -4.500  -0.3572   0.04159   0.03373  -0.0317   1.0000   0.1288
  -4.250  -0.3273   0.03686   0.02831  -0.0332   1.0000   0.1158
  -4.000  -0.2994   0.03324   0.02414  -0.0336   1.0000   0.1133
  -3.750  -0.2711   0.03036   0.02067  -0.0336   1.0000   0.1169
  -3.500  -0.2418   0.02765   0.01737  -0.0332   1.0000   0.1193
  -3.250  -0.2142   0.02518   0.01473  -0.0326   1.0000   0.1262
  -3.000  -0.1867   0.02329   0.01265  -0.0319   1.0000   0.1449
  -2.750  -0.1590   0.02134   0.01069  -0.0310   1.0000   0.1732
  -2.500  -0.1319   0.01926   0.00895  -0.0301   1.0000   0.2435
  -2.250  -0.0959   0.01425   0.00703  -0.0272   1.0000   1.0000
  -2.000  -0.0703   0.01418   0.00629  -0.0269   1.0000   1.0000
  -1.750  -0.0457   0.01413   0.00580  -0.0265   1.0000   1.0000
  -1.500  -0.0214   0.01412   0.00543  -0.0260   1.0000   1.0000
  -1.250   0.0024   0.01413   0.00514  -0.0256   1.0000   1.0000
  -1.000   0.0257   0.01417   0.00496  -0.0251   1.0000   1.0000
  -0.750   0.0484   0.01426   0.00486  -0.0247   1.0000   1.0000
  -0.500   0.0704   0.01440   0.00485  -0.0243   1.0000   1.0000
  -0.250   0.0912   0.01462   0.00494  -0.0239   1.0000   1.0000
   0.000   0.1111   0.01492   0.00511  -0.0236   1.0000   1.0000
   0.250   0.1308   0.01533   0.00540  -0.0235   1.0000   1.0000
   0.500   0.1505   0.01582   0.00581  -0.0237   1.0000   1.0000
   0.750   0.1700   0.01640   0.00632  -0.0242   1.0000   1.0000
   1.000   0.1893   0.01709   0.00694  -0.0249   1.0000   1.0000
   1.250   0.2488   0.01788   0.00773  -0.0329   0.9778   1.0000
   1.500   0.3233   0.01844   0.00835  -0.0426   0.9447   1.0000
   1.750   0.3942   0.01870   0.00873  -0.0505   0.9124   1.0000
   2.000   0.4418   0.01891   0.00903  -0.0534   0.8774   1.0000
   2.250   0.4799   0.01911   0.00928  -0.0537   0.8441   1.0000
   2.500   0.5078   0.01945   0.00966  -0.0522   0.8107   1.0000
   2.750   0.5319   0.01987   0.01007  -0.0500   0.7777   1.0000
   3.000   0.5551   0.02033   0.01051  -0.0475   0.7460   1.0000
   3.250   0.5772   0.02088   0.01102  -0.0449   0.7147   1.0000
   3.500   0.5988   0.02155   0.01175  -0.0428   0.6811   1.0000
   3.750   0.6208   0.02206   0.01225  -0.0404   0.6499   1.0000
   4.000   0.6430   0.02255   0.01275  -0.0383   0.6176   1.0000
   4.250   0.6655   0.02298   0.01320  -0.0362   0.5854   1.0000
   4.500   0.6884   0.02337   0.01357  -0.0341   0.5539   1.0000
   4.750   0.7115   0.02377   0.01395  -0.0319   0.5227   1.0000
   5.000   0.7345   0.02440   0.01462  -0.0303   0.4881   1.0000
   5.250   0.7577   0.02500   0.01516  -0.0284   0.4551   1.0000
   5.500   0.7809   0.02574   0.01586  -0.0268   0.4219   1.0000
   5.750   0.8039   0.02663   0.01682  -0.0253   0.3876   1.0000
   6.000   0.8271   0.02754   0.01765  -0.0238   0.3556   1.0000
   6.250   0.8499   0.02874   0.01887  -0.0225   0.3236   1.0000
   6.500   0.8722   0.03005   0.02026  -0.0213   0.2921   1.0000
   6.750   0.8944   0.03148   0.02173  -0.0201   0.2626   1.0000
   7.000   0.9163   0.03322   0.02361  -0.0189   0.2355   1.0000
   7.250   0.9371   0.03492   0.02539  -0.0178   0.2086   1.0000
   7.500   0.9591   0.03707   0.02747  -0.0167   0.1873   1.0000
   7.750   0.9766   0.03963   0.03046  -0.0156   0.1661   1.0000
   8.000   0.9937   0.04324   0.03447  -0.0148   0.1528   1.0000
   8.250   1.0092   0.04626   0.03776  -0.0139   0.1382   1.0000
   8.500   1.0211   0.05068   0.04257  -0.0133   0.1305   1.0000
   8.750   1.0228   0.05655   0.04911  -0.0134   0.1272   1.0000
   9.000   1.0354   0.06007   0.05267  -0.0126   0.1190   1.0000
   9.250   1.0251   0.06659   0.05972  -0.0137   0.1182   1.0000
   9.500   1.0116   0.07324   0.06667  -0.0155   0.1186   1.0000
   9.750   0.9971   0.07986   0.07346  -0.0178   0.1194   1.0000
  10.000   0.9835   0.08625   0.07992  -0.0201   0.1201   1.0000
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