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Coanda 3 (coanda3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: Coanda 3 (coanda3-il)
Reynolds number: 1,000,000
Max Cl/Cd: 80.87 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-coanda3-il-1000000-n5.txt
Download as CSV file: xf-coanda3-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4356   0.12567   0.12399  -0.0176   1.0000   0.0033
 -11.500  -0.4329   0.12212   0.12045  -0.0184   1.0000   0.0033
 -10.000  -0.4282   0.10058   0.09901  -0.0223   1.0000   0.0035
  -9.000  -0.4210   0.08834   0.08684  -0.0259   0.9991   0.0037
  -8.750  -0.4141   0.08188   0.08040  -0.0319   0.9970   0.0036
  -8.500  -0.4036   0.07822   0.07674  -0.0364   0.9943   0.0037
  -8.250  -0.3941   0.07397   0.07249  -0.0420   0.9899   0.0038
  -8.000  -0.3770   0.06815   0.06666  -0.0498   0.9870   0.0039
  -7.750  -0.3637   0.06289   0.06137  -0.0556   0.9815   0.0039
  -7.000  -0.3100   0.03987   0.03795  -0.0743   0.9678   0.0030
  -6.750  -0.2967   0.03083   0.02857  -0.0767   0.9598   0.0028
  -6.500  -0.2761   0.02325   0.02039  -0.0783   0.9557   0.0027
  -6.250  -0.2582   0.02005   0.01675  -0.0772   0.9489   0.0025
  -6.000  -0.2356   0.01732   0.01358  -0.0766   0.9442   0.0024
  -5.750  -0.2109   0.01520   0.01106  -0.0759   0.9403   0.0023
  -5.500  -0.1880   0.01364   0.00922  -0.0747   0.9346   0.0023
  -5.250  -0.1609   0.01215   0.00747  -0.0744   0.9291   0.0023
  -5.000  -0.1359   0.01109   0.00622  -0.0735   0.9228   0.0025
  -4.750  -0.1097   0.01016   0.00514  -0.0730   0.9163   0.0025
  -4.500  -0.0842   0.00951   0.00437  -0.0723   0.9101   0.0030
  -4.250  -0.0583   0.00898   0.00373  -0.0717   0.9035   0.0032
  -4.000  -0.0325   0.00850   0.00314  -0.0712   0.8977   0.0035
  -3.750  -0.0067   0.00823   0.00284  -0.0707   0.8907   0.0041
  -3.500   0.0195   0.00800   0.00254  -0.0703   0.8828   0.0049
  -3.250   0.0450   0.00771   0.00217  -0.0696   0.8748   0.0054
  -3.000   0.0700   0.00741   0.00177  -0.0689   0.8663   0.0064
  -2.750   0.0956   0.00726   0.00154  -0.0683   0.8563   0.0076
  -2.500   0.1208   0.00716   0.00136  -0.0676   0.8413   0.0094
  -2.250   0.1457   0.00707   0.00114  -0.0668   0.8230   0.0130
  -2.000   0.1668   0.00687   0.00094  -0.0652   0.7891   0.0557
  -1.750   0.1864   0.00701   0.00092  -0.0633   0.7379   0.0696
  -1.500   0.2078   0.00714   0.00091  -0.0619   0.7034   0.0759
  -1.250   0.2309   0.00723   0.00090  -0.0608   0.6759   0.0791
  -1.000   0.2548   0.00731   0.00090  -0.0600   0.6518   0.0823
  -0.750   0.2782   0.00743   0.00090  -0.0590   0.6227   0.0840
  -0.500   0.3015   0.00749   0.00087  -0.0581   0.5948   0.0869
  -0.250   0.3246   0.00760   0.00087  -0.0571   0.5613   0.0893
   0.000   0.3474   0.00774   0.00089  -0.0560   0.5220   0.0924
   0.250   0.3692   0.00798   0.00094  -0.0548   0.4699   0.0950
   0.500   0.3908   0.00825   0.00101  -0.0536   0.4152   0.0967
   0.750   0.4138   0.00845   0.00108  -0.0527   0.3778   0.0991
   1.000   0.4376   0.00858   0.00115  -0.0520   0.3521   0.1041
   1.250   0.4617   0.00871   0.00121  -0.0513   0.3316   0.1091
   1.500   0.4865   0.00879   0.00128  -0.0507   0.3178   0.1145
   1.750   0.5113   0.00885   0.00135  -0.0502   0.3069   0.1245
   2.250   0.5559   0.00857   0.00157  -0.0482   0.2880   0.3517
   2.500   0.5525   0.00728   0.00167  -0.0415   0.2746   0.8830
   3.000   0.6874   0.00850   0.00250  -0.0609   0.1455   0.9843
   3.250   0.7100   0.00971   0.00313  -0.0605   0.0155   0.9896
   3.500   0.7501   0.01003   0.00348  -0.0634   0.0084   0.9948
   3.750   0.7872   0.01030   0.00379  -0.0658   0.0064   0.9970
   4.000   0.8218   0.01063   0.00414  -0.0676   0.0046   0.9989
   4.250   0.8533   0.01094   0.00449  -0.0687   0.0038   1.0000
   4.500   0.8733   0.01136   0.00495  -0.0672   0.0033   1.0000
   4.750   0.8928   0.01183   0.00549  -0.0655   0.0030   1.0000
   5.000   0.9122   0.01231   0.00604  -0.0638   0.0028   1.0000
   5.250   0.9321   0.01272   0.00651  -0.0623   0.0024   1.0000
   5.500   0.9507   0.01326   0.00712  -0.0606   0.0022   1.0000
   5.750   0.9710   0.01360   0.00750  -0.0593   0.0020   1.0000
   6.000   0.9877   0.01429   0.00825  -0.0572   0.0018   1.0000
   6.250   1.0019   0.01517   0.00925  -0.0547   0.0017   1.0000
   6.500   1.0189   0.01582   0.00999  -0.0526   0.0015   1.0000
   6.750   1.0326   0.01678   0.01106  -0.0500   0.0014   1.0000
   7.000   1.0431   0.01821   0.01262  -0.0466   0.0013   1.0000
   7.250   1.0558   0.01967   0.01421  -0.0438   0.0011   1.0000
   7.500   1.0688   0.02187   0.01657  -0.0409   0.0011   1.0000
   7.750   1.0835   0.02382   0.01869  -0.0385   0.0010   1.0000
   8.000   1.0966   0.02686   0.02200  -0.0356   0.0010   1.0000
   8.250   1.1053   0.02989   0.02531  -0.0321   0.0010   1.0000
   8.500   1.1115   0.03257   0.02826  -0.0285   0.0011   1.0000
   8.750   1.1131   0.03558   0.03155  -0.0243   0.0012   1.0000
   9.000   1.1133   0.03805   0.03428  -0.0203   0.0012   1.0000
   9.250   1.1083   0.04075   0.03722  -0.0157   0.0012   1.0000
   9.500   1.0980   0.04330   0.03998  -0.0105   0.0013   1.0000
   9.750   1.0817   0.04575   0.04262  -0.0047   0.0013   1.0000
  10.000   1.0707   0.04786   0.04488  -0.0007   0.0013   1.0000
  10.250   1.0527   0.05097   0.04817   0.0031   0.0013   1.0000
  10.500   1.0370   0.05403   0.05139   0.0055   0.0014   1.0000
  10.750   1.0204   0.05759   0.05510   0.0069   0.0014   1.0000
  11.000   1.0026   0.06179   0.05944   0.0069   0.0014   1.0000
  11.250   0.9818   0.06722   0.06502   0.0052   0.0014   1.0000
  11.500   0.9635   0.07306   0.07099   0.0022   0.0014   1.0000
  11.750   0.9492   0.07929   0.07733  -0.0018   0.0014   1.0000
  12.000   0.9308   0.08746   0.08562  -0.0075   0.0014   1.0000
  12.250   0.9157   0.09606   0.09432  -0.0135   0.0014   1.0000
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