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Coanda 3 (coanda3-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: Coanda 3 (coanda3-il)
Reynolds number: 500,000
Max Cl/Cd: 75.96 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-coanda3-il-500000-n5.txt
Download as CSV file: xf-coanda3-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Coanda 3                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4208   0.09145   0.08933  -0.0239   1.0000   0.0069
  -8.750  -0.4254   0.08860   0.08651  -0.0236   1.0000   0.0071
  -8.500  -0.4324   0.08613   0.08408  -0.0227   1.0000   0.0072
  -8.250  -0.4319   0.08242   0.08041  -0.0252   0.9985   0.0072
  -8.000  -0.4188   0.07736   0.07534  -0.0320   0.9941   0.0074
  -7.750  -0.4015   0.07167   0.06964  -0.0394   0.9896   0.0074
  -7.500  -0.3838   0.06580   0.06373  -0.0465   0.9858   0.0075
  -7.250  -0.3659   0.05996   0.05783  -0.0528   0.9809   0.0075
  -7.000  -0.3436   0.05372   0.05147  -0.0593   0.9775   0.0075
  -6.500  -0.3104   0.03451   0.03168  -0.0680   0.9653   0.0050
  -6.250  -0.2958   0.02746   0.02412  -0.0682   0.9597   0.0046
  -6.000  -0.2748   0.02308   0.01916  -0.0682   0.9569   0.0043
  -5.750  -0.2502   0.02002   0.01554  -0.0680   0.9548   0.0041
  -5.500  -0.2326   0.01814   0.01328  -0.0658   0.9491   0.0039
  -5.250  -0.2067   0.01634   0.01111  -0.0652   0.9462   0.0038
  -5.000  -0.1779   0.01495   0.00947  -0.0653   0.9441   0.0040
  -4.750  -0.1480   0.01374   0.00804  -0.0656   0.9423   0.0040
  -4.500  -0.1220   0.01284   0.00699  -0.0650   0.9385   0.0044
  -4.250  -0.0952   0.01201   0.00604  -0.0646   0.9336   0.0047
  -4.000  -0.0620   0.01157   0.00548  -0.0655   0.9297   0.0055
  -3.750  -0.0349   0.01063   0.00450  -0.0654   0.9247   0.0065
  -3.500  -0.0070   0.01011   0.00391  -0.0652   0.9189   0.0070
  -3.250   0.0262   0.00966   0.00333  -0.0662   0.9144   0.0077
  -3.000   0.0517   0.00935   0.00292  -0.0655   0.9071   0.0090
  -2.750   0.0823   0.00898   0.00241  -0.0660   0.9011   0.0114
  -2.500   0.1081   0.00873   0.00205  -0.0653   0.8928   0.0154
  -2.250   0.1361   0.00836   0.00182  -0.0654   0.8857   0.0652
  -2.000   0.1622   0.00831   0.00181  -0.0649   0.8763   0.0776
  -1.750   0.1896   0.00830   0.00175  -0.0648   0.8653   0.0830
  -1.500   0.2165   0.00824   0.00169  -0.0645   0.8524   0.0895
  -1.250   0.2430   0.00818   0.00159  -0.0641   0.8355   0.0928
  -1.000   0.2689   0.00813   0.00144  -0.0636   0.8065   0.0947
  -0.750   0.2933   0.00818   0.00129  -0.0626   0.7651   0.0966
  -0.500   0.3155   0.00829   0.00122  -0.0613   0.7261   0.0992
  -0.250   0.3380   0.00837   0.00119  -0.0601   0.6976   0.1027
   0.000   0.3610   0.00846   0.00119  -0.0590   0.6734   0.1063
   0.250   0.3842   0.00854   0.00119  -0.0580   0.6487   0.1096
   0.500   0.4070   0.00864   0.00120  -0.0569   0.6213   0.1130
   0.750   0.4296   0.00872   0.00123  -0.0558   0.5935   0.1192
   1.250   0.4723   0.00905   0.00134  -0.0532   0.5126   0.1396
   1.500   0.4911   0.00931   0.00144  -0.0514   0.4516   0.1664
   1.750   0.4883   0.00799   0.00157  -0.0454   0.4168   0.7407
   2.250   0.6447   0.00875   0.00249  -0.0689   0.3258   0.9913
   2.500   0.6879   0.00915   0.00271  -0.0728   0.2845   0.9978
   2.750   0.7201   0.00948   0.00287  -0.0741   0.2443   1.0000
   3.000   0.7377   0.01000   0.00308  -0.0723   0.1816   1.0000
   3.250   0.7501   0.01099   0.00352  -0.0697   0.0797   1.0000
   3.500   0.7659   0.01178   0.00407  -0.0674   0.0141   1.0000
   3.750   0.7864   0.01216   0.00455  -0.0658   0.0092   1.0000
   4.000   0.8071   0.01253   0.00501  -0.0643   0.0079   1.0000
   4.250   0.8276   0.01290   0.00548  -0.0629   0.0067   1.0000
   4.500   0.8468   0.01342   0.00605  -0.0613   0.0054   1.0000
   4.750   0.8649   0.01406   0.00679  -0.0594   0.0050   1.0000
   5.000   0.8830   0.01470   0.00751  -0.0574   0.0046   1.0000
   5.250   0.8994   0.01547   0.00837  -0.0552   0.0043   1.0000
   5.500   0.9148   0.01632   0.00930  -0.0528   0.0040   1.0000
   5.750   0.9294   0.01726   0.01032  -0.0502   0.0039   1.0000
   6.000   0.9454   0.01807   0.01122  -0.0481   0.0036   1.0000
   6.250   0.9601   0.01902   0.01220  -0.0459   0.0033   1.0000
   6.500   0.9762   0.02005   0.01337  -0.0436   0.0026   1.0000
   6.750   0.9916   0.02138   0.01481  -0.0413   0.0025   1.0000
   7.000   1.0080   0.02301   0.01657  -0.0392   0.0024   1.0000
   7.250   1.0249   0.02465   0.01837  -0.0372   0.0022   1.0000
   7.500   1.0417   0.02659   0.02049  -0.0352   0.0022   1.0000
   7.750   1.0560   0.02851   0.02261  -0.0329   0.0020   1.0000
   8.000   1.0684   0.03097   0.02534  -0.0302   0.0021   1.0000
   8.250   1.0769   0.03357   0.02824  -0.0269   0.0021   1.0000
   8.500   1.0826   0.03620   0.03115  -0.0235   0.0023   1.0000
   8.750   1.0838   0.03898   0.03423  -0.0195   0.0023   1.0000
   9.000   1.0829   0.04142   0.03692  -0.0156   0.0024   1.0000
   9.250   1.0767   0.04400   0.03974  -0.0111   0.0025   1.0000
   9.500   1.0645   0.04634   0.04228  -0.0059   0.0026   1.0000
   9.750   1.0503   0.04894   0.04508  -0.0012   0.0026   1.0000
  10.000   1.0384   0.05139   0.04774   0.0021   0.0027   1.0000
  10.250   1.0215   0.05464   0.05118   0.0050   0.0027   1.0000
  10.500   1.0060   0.05799   0.05469   0.0065   0.0027   1.0000
  10.750   0.9901   0.06182   0.05868   0.0070   0.0028   1.0000
  11.000   0.9724   0.06650   0.06352   0.0061   0.0028   1.0000
  11.250   0.9536   0.07212   0.06925   0.0037   0.0028   1.0000
  11.500   0.9366   0.07833   0.07559   0.0002   0.0028   1.0000
  11.750   0.9226   0.08499   0.08238  -0.0044   0.0028   1.0000
  12.000   0.9060   0.09330   0.09081  -0.0101   0.0028   1.0000
  12.250   0.8914   0.10205   0.09966  -0.0159   0.0028   1.0000
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