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Coanda 2 (coanda2-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Coanda 2 (coanda2-il)
Reynolds number: 200,000
Max Cl/Cd: 49.48 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-coanda2-il-200000-n5.txt
Download as CSV file: xf-coanda2-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Coanda 2                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4273   0.09803   0.09454  -0.0165   1.0000   0.0116
  -9.000  -0.4268   0.09480   0.09136  -0.0168   1.0000   0.0112
  -8.750  -0.4270   0.09167   0.08827  -0.0173   1.0000   0.0109
  -8.500  -0.4292   0.08843   0.08509  -0.0177   1.0000   0.0107
  -8.250  -0.4333   0.08546   0.08218  -0.0178   1.0000   0.0104
  -8.000  -0.4396   0.08279   0.07957  -0.0173   1.0000   0.0102
  -7.750  -0.4436   0.07955   0.07638  -0.0176   1.0000   0.0101
  -7.500  -0.4450   0.07606   0.07294  -0.0185   1.0000   0.0099
  -7.250  -0.4451   0.07235   0.06925  -0.0197   1.0000   0.0097
  -7.000  -0.4444   0.06821   0.06513  -0.0211   1.0000   0.0096
  -6.750  -0.4417   0.06409   0.06100  -0.0223   1.0000   0.0092
  -6.500  -0.4377   0.05961   0.05649  -0.0235   1.0000   0.0090
  -6.250  -0.4332   0.05419   0.05099  -0.0247   1.0000   0.0089
  -6.000  -0.4272   0.04857   0.04523  -0.0254   1.0000   0.0085
  -5.750  -0.4226   0.04101   0.03735  -0.0256   1.0000   0.0082
  -5.500  -0.4065   0.02965   0.02512  -0.0274   0.9964   0.0077
  -5.250  -0.3822   0.02483   0.01963  -0.0276   0.9927   0.0076
  -5.000  -0.3550   0.02218   0.01649  -0.0277   0.9889   0.0080
  -4.750  -0.3251   0.02049   0.01440  -0.0281   0.9857   0.0079
  -4.500  -0.2960   0.01930   0.01285  -0.0282   0.9808   0.0083
  -4.250  -0.2606   0.01835   0.01160  -0.0294   0.9768   0.0093
  -4.000  -0.2285   0.01759   0.01058  -0.0299   0.9703   0.0108
  -3.750  -0.1921   0.01581   0.00834  -0.0313   0.9660   0.0197
  -3.500  -0.1602   0.01537   0.00794  -0.0318   0.9591   0.0604
  -3.250  -0.1232   0.01530   0.00770  -0.0335   0.9542   0.0634
  -3.000  -0.0933   0.01532   0.00763  -0.0337   0.9481   0.0663
  -2.750  -0.0609   0.01522   0.00738  -0.0345   0.9429   0.0701
  -2.500  -0.0243   0.01510   0.00699  -0.0362   0.9393   0.0732
  -2.250   0.0022   0.01471   0.00656  -0.0358   0.9316   0.0745
  -2.000   0.0374   0.01436   0.00619  -0.0372   0.9271   0.0758
  -1.750   0.0663   0.01414   0.00595  -0.0374   0.9190   0.0779
  -1.500   0.1035   0.01420   0.00596  -0.0392   0.9130   0.0845
  -1.250   0.1338   0.01412   0.00578  -0.0395   0.9029   0.0866
  -1.000   0.1681   0.01349   0.00511  -0.0408   0.8935   0.0876
  -0.750   0.2036   0.01300   0.00464  -0.0423   0.8823   0.0887
  -0.500   0.2376   0.01263   0.00431  -0.0435   0.8680   0.0905
  -0.250   0.2724   0.01233   0.00403  -0.0448   0.8493   0.0929
   0.000   0.3075   0.01203   0.00371  -0.0461   0.8239   0.0945
   0.250   0.3426   0.01175   0.00338  -0.0474   0.7868   0.0956
   0.500   0.3750   0.01161   0.00308  -0.0481   0.7302   0.0969
   0.750   0.4008   0.01170   0.00288  -0.0473   0.6656   0.0979
   1.000   0.4228   0.01188   0.00283  -0.0459   0.6157   0.0991
   1.250   0.4446   0.01204   0.00285  -0.0446   0.5748   0.1003
   1.500   0.4663   0.01210   0.00282  -0.0433   0.5392   0.1020
   1.750   0.4884   0.01222   0.00284  -0.0421   0.5056   0.1039
   2.000   0.5098   0.01241   0.00290  -0.0407   0.4677   0.1060
   2.250   0.5301   0.01271   0.00297  -0.0393   0.4221   0.1082
   2.500   0.5528   0.01290   0.00308  -0.0383   0.3945   0.1105
   2.750   0.5766   0.01305   0.00329  -0.0375   0.3746   0.1134
   3.000   0.6005   0.01318   0.00344  -0.0367   0.3528   0.1191
   3.250   0.6243   0.01335   0.00360  -0.0360   0.3279   0.1261
   3.500   0.6432   0.01391   0.00379  -0.0345   0.2434   0.1377
   3.750   0.7837   0.01584   0.00646  -0.0624   0.0127   1.0000
   4.000   0.8066   0.01640   0.00716  -0.0612   0.0118   1.0000
   4.250   0.8285   0.01710   0.00802  -0.0599   0.0099   1.0000
   4.500   0.8455   0.01837   0.00940  -0.0581   0.0072   1.0000
   4.750   0.8676   0.01896   0.01009  -0.0568   0.0059   1.0000
   5.000   0.8855   0.02008   0.01141  -0.0549   0.0056   1.0000
   5.250   0.9033   0.02122   0.01260  -0.0530   0.0054   1.0000
   5.500   0.9212   0.02254   0.01399  -0.0511   0.0052   1.0000
   5.750   0.9400   0.02385   0.01537  -0.0494   0.0052   1.0000
   6.000   0.9594   0.02541   0.01702  -0.0477   0.0051   1.0000
   6.250   0.9794   0.02699   0.01872  -0.0461   0.0051   1.0000
   6.500   0.9992   0.02880   0.02071  -0.0445   0.0052   1.0000
   6.750   1.0180   0.03071   0.02283  -0.0428   0.0053   1.0000
   7.000   1.0353   0.03274   0.02512  -0.0410   0.0054   1.0000
   7.250   1.0500   0.03517   0.02788  -0.0387   0.0055   1.0000
   7.500   1.0628   0.03754   0.03060  -0.0364   0.0057   1.0000
   7.750   1.0725   0.04017   0.03356  -0.0339   0.0059   1.0000
   8.000   1.0796   0.04296   0.03667  -0.0312   0.0061   1.0000
   8.250   1.0827   0.04609   0.04011  -0.0282   0.0063   1.0000
   8.500   1.0837   0.04920   0.04349  -0.0253   0.0065   1.0000
   8.750   1.0796   0.05276   0.04731  -0.0222   0.0067   1.0000
   9.000   1.0732   0.05644   0.05120  -0.0193   0.0068   1.0000
   9.250   1.0891   0.06365   0.05851  -0.0185   0.0128   1.0000
   9.500   1.0773   0.06638   0.06148  -0.0151   0.0128   1.0000
   9.750   1.0610   0.06906   0.06433  -0.0114   0.0128   1.0000
  10.000   1.0428   0.07223   0.06767  -0.0090   0.0128   1.0000
  10.250   1.0253   0.07564   0.07125  -0.0081   0.0128   1.0000
  10.500   1.0083   0.07994   0.07570  -0.0087   0.0128   1.0000
  10.750   0.9921   0.08472   0.08062  -0.0107   0.0128   1.0000
  11.000   0.9764   0.09012   0.08616  -0.0140   0.0128   1.0000
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