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Coanda 1 (coanda1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: Coanda 1 (coanda1-il)
Reynolds number: 1,000,000
Max Cl/Cd: 60.53 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-coanda1-il-1000000.txt
Download as CSV file: xf-coanda1-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Coanda 1                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4446   0.08542   0.08390  -0.0142   1.0000   0.0077
  -7.750  -0.4565   0.08260   0.08112  -0.0130   1.0000   0.0077
  -7.500  -0.4593   0.07938   0.07792  -0.0131   1.0000   0.0077
  -7.250  -0.4611   0.07575   0.07429  -0.0138   1.0000   0.0078
  -7.000  -0.4613   0.07227   0.07082  -0.0144   1.0000   0.0078
  -6.750  -0.4746   0.06439   0.06294  -0.0170   0.9998   0.0082
  -6.500  -0.4492   0.05837   0.05682  -0.0241   0.9975   0.0087
  -6.250  -0.4211   0.05410   0.05247  -0.0292   0.9954   0.0092
  -6.000  -0.3938   0.04997   0.04825  -0.0334   0.9934   0.0098
  -5.750  -0.3682   0.04678   0.04498  -0.0361   0.9907   0.0113
  -5.500  -0.3410   0.04168   0.03973  -0.0392   0.9875   0.0125
  -4.750  -0.2905   0.01556   0.01160  -0.0373   0.9744   0.0082
  -4.500  -0.2618   0.01395   0.00976  -0.0373   0.9725   0.0075
  -4.250  -0.2325   0.01219   0.00768  -0.0374   0.9710   0.0074
  -4.000  -0.2004   0.01117   0.00647  -0.0381   0.9699   0.0076
  -3.750  -0.1754   0.00985   0.00491  -0.0371   0.9666   0.0085
  -3.500  -0.1480   0.00905   0.00395  -0.0368   0.9629   0.0102
  -3.250  -0.1157   0.00859   0.00343  -0.0376   0.9605   0.0112
  -3.000  -0.0805   0.00814   0.00290  -0.0390   0.9583   0.0130
  -2.750  -0.0424   0.00775   0.00241  -0.0411   0.9561   0.0149
  -2.500  -0.0155   0.00739   0.00199  -0.0406   0.9477   0.0219
  -2.250   0.0257   0.00775   0.00262  -0.0433   0.9410   0.0653
  -2.000   0.0618   0.00782   0.00267  -0.0451   0.9299   0.0678
  -1.750   0.0975   0.00807   0.00291  -0.0467   0.9159   0.0708
  -1.500   0.1289   0.00802   0.00281  -0.0474   0.8973   0.0722
  -1.250   0.1576   0.00844   0.00315  -0.0474   0.8728   0.0759
  -1.000   0.1834   0.00829   0.00288  -0.0467   0.8412   0.0765
  -0.750   0.2067   0.00820   0.00263  -0.0456   0.7989   0.0770
  -0.500   0.2288   0.00827   0.00253  -0.0441   0.7580   0.0777
  -0.250   0.2513   0.00834   0.00245  -0.0428   0.7239   0.0783
   0.000   0.2745   0.00836   0.00236  -0.0417   0.6947   0.0787
   0.250   0.2970   0.00799   0.00190  -0.0406   0.6658   0.0811
   0.500   0.3201   0.00796   0.00178  -0.0396   0.6350   0.0820
   0.750   0.3430   0.00800   0.00171  -0.0385   0.6015   0.0831
   1.000   0.3665   0.00805   0.00169  -0.0375   0.5732   0.0841
   1.250   0.3903   0.00809   0.00165  -0.0367   0.5471   0.0849
   1.500   0.4143   0.00814   0.00163  -0.0358   0.5231   0.0856
   1.750   0.4343   0.00843   0.00163  -0.0342   0.4472   0.0861
   2.000   0.4536   0.00885   0.00168  -0.0326   0.3530   0.0866
   2.250   0.4748   0.00916   0.00177  -0.0314   0.2938   0.0871
   2.500   0.4976   0.00937   0.00182  -0.0304   0.2517   0.0876
   2.750   0.5189   0.00972   0.00192  -0.0292   0.1926   0.0883
   3.000   0.5403   0.01007   0.00204  -0.0281   0.1441   0.0888
   3.250   0.5582   0.01075   0.00231  -0.0263   0.0531   0.0896
   3.500   0.5806   0.01107   0.00249  -0.0252   0.0158   0.0906
   3.750   0.6051   0.01122   0.00274  -0.0245   0.0141   0.0916
   4.000   0.6289   0.01131   0.00290  -0.0237   0.0130   0.0951
   4.250   0.6521   0.01157   0.00326  -0.0227   0.0111   0.0974
   4.500   0.6731   0.01208   0.00389  -0.0212   0.0096   0.1004
   4.750   0.6941   0.01258   0.00448  -0.0198   0.0094   0.1023
   5.000   0.7136   0.01325   0.00525  -0.0181   0.0093   0.1040
   5.250   0.7350   0.01367   0.00574  -0.0168   0.0088   0.1072
   5.500   0.7562   0.01409   0.00624  -0.0155   0.0085   0.1129
   5.750   0.8832   0.01459   0.00870  -0.0389   0.0065   0.9887
  17.000   0.6538   0.17984   0.17832  -0.0351   0.0048   1.0000
  17.250   0.6545   0.18322   0.18170  -0.0362   0.0048   1.0000
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