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Coanda 3 (coanda3-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Coanda 3 (coanda3-il)
Reynolds number: 50,000
Max Cl/Cd: 37.26 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-coanda3-il-50000-n5.txt
Download as CSV file: xf-coanda3-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4288   0.09361   0.08710  -0.0293   1.0000   0.0348
  -8.250  -0.4327   0.09078   0.08436  -0.0287   1.0000   0.0344
  -8.000  -0.4347   0.08779   0.08145  -0.0284   1.0000   0.0339
  -7.750  -0.4367   0.08463   0.07837  -0.0286   1.0000   0.0336
  -7.500  -0.4388   0.08124   0.07504  -0.0290   1.0000   0.0334
  -7.250  -0.4397   0.07778   0.07162  -0.0293   1.0000   0.0331
  -7.000  -0.4391   0.07432   0.06818  -0.0296   1.0000   0.0328
  -6.750  -0.4375   0.07055   0.06441  -0.0300   1.0000   0.0327
  -6.500  -0.4342   0.06676   0.06052  -0.0302   1.0000   0.0324
  -6.250  -0.4293   0.06277   0.05646  -0.0305   1.0000   0.0322
  -6.000  -0.4226   0.05865   0.05222  -0.0306   1.0000   0.0323
  -5.750  -0.4141   0.05443   0.04783  -0.0306   1.0000   0.0321
  -5.500  -0.4037   0.05032   0.04350  -0.0302   1.0000   0.0318
  -5.250  -0.3919   0.04589   0.03877  -0.0297   1.0000   0.0318
  -5.000  -0.3784   0.04139   0.03387  -0.0289   1.0000   0.0316
  -4.750  -0.3630   0.03677   0.02869  -0.0278   1.0000   0.0313
  -4.500  -0.3447   0.03244   0.02366  -0.0265   1.0000   0.0312
  -4.250  -0.3238   0.02936   0.01993  -0.0251   1.0000   0.0317
  -4.000  -0.3008   0.02708   0.01709  -0.0238   1.0000   0.0328
  -3.750  -0.2760   0.02541   0.01493  -0.0228   1.0000   0.0349
  -3.500  -0.2523   0.02465   0.01416  -0.0220   1.0000   0.0417
  -3.250  -0.2290   0.02433   0.01380  -0.0211   1.0000   0.0525
  -3.000  -0.2042   0.02411   0.01317  -0.0200   1.0000   0.0861
  -2.750  -0.1839   0.02426   0.01298  -0.0186   1.0000   0.1088
  -2.500  -0.1630   0.02429   0.01267  -0.0174   1.0000   0.1248
  -2.250  -0.1406   0.02415   0.01235  -0.0167   1.0000   0.1337
  -2.000  -0.1236   0.02432   0.01247  -0.0156   1.0000   0.1623
  -1.750  -0.1004   0.02418   0.01208  -0.0151   1.0000   0.1707
  -1.500  -0.0761   0.02396   0.01168  -0.0147   1.0000   0.1733
  -1.250  -0.0442   0.02380   0.01132  -0.0159   0.9967   0.1766
  -1.000  -0.0071   0.02373   0.01102  -0.0181   0.9904   0.1810
  -0.750   0.0292   0.02365   0.01084  -0.0203   0.9839   0.1867
  -0.500   0.0656   0.02363   0.01073  -0.0225   0.9772   0.1957
  -0.250   0.1007   0.02356   0.01067  -0.0245   0.9695   0.2085
   0.000   0.1364   0.02334   0.01070  -0.0267   0.9606   0.2450
   0.250   0.2160   0.02146   0.01072  -0.0376   0.9570   1.0000
   0.500   0.2646   0.02164   0.01065  -0.0417   0.9418   1.0000
   0.750   0.3082   0.02163   0.01051  -0.0447   0.9236   1.0000
   1.000   0.3489   0.02164   0.01044  -0.0471   0.9077   1.0000
   1.250   0.3860   0.02168   0.01045  -0.0489   0.8940   1.0000
   1.500   0.4220   0.02169   0.01050  -0.0504   0.8800   1.0000
   1.750   0.4575   0.02163   0.01050  -0.0517   0.8649   1.0000
   2.000   0.4933   0.02150   0.01046  -0.0528   0.8489   1.0000
   2.250   0.5305   0.02127   0.01040  -0.0541   0.8318   1.0000
   2.500   0.5583   0.02111   0.01038  -0.0534   0.8091   1.0000
   2.750   0.5906   0.02079   0.01020  -0.0534   0.7840   1.0000
   3.000   0.6247   0.02042   0.01004  -0.0534   0.7539   1.0000
   3.250   0.6633   0.02002   0.00976  -0.0541   0.7178   1.0000
   3.500   0.6969   0.01986   0.00970  -0.0540   0.6739   1.0000
   3.750   0.7246   0.01997   0.00990  -0.0530   0.6227   1.0000
   4.000   0.7495   0.02025   0.01016  -0.0516   0.5655   1.0000
   4.250   0.7720   0.02072   0.01055  -0.0500   0.5107   1.0000
   4.500   0.7930   0.02135   0.01109  -0.0483   0.4651   1.0000
   4.750   0.8025   0.02233   0.01155  -0.0447   0.3904   1.0000
   5.000   0.8155   0.02327   0.01225  -0.0420   0.3375   1.0000
   5.250   0.8282   0.02416   0.01297  -0.0395   0.2843   1.0000
   5.500   0.8431   0.02495   0.01369  -0.0373   0.2257   1.0000
   5.750   0.8575   0.02609   0.01447  -0.0351   0.1448   1.0000
   6.000   0.8681   0.02893   0.01621  -0.0333   0.0396   1.0000
   6.250   0.8858   0.03046   0.01795  -0.0316   0.0341   1.0000
   6.500   0.9001   0.03219   0.01998  -0.0295   0.0317   1.0000
   6.750   0.9138   0.03368   0.02176  -0.0272   0.0304   1.0000
   7.000   0.9249   0.03536   0.02372  -0.0247   0.0282   1.0000
   7.250   0.9341   0.03719   0.02576  -0.0221   0.0264   1.0000
   7.500   0.9413   0.03923   0.02796  -0.0195   0.0250   1.0000
   7.750   0.9496   0.04155   0.03045  -0.0169   0.0242   1.0000
   8.000   0.9634   0.04392   0.03299  -0.0149   0.0238   1.0000
   8.250   0.9806   0.04635   0.03570  -0.0133   0.0236   1.0000
   8.500   0.9968   0.04897   0.03863  -0.0118   0.0235   1.0000
   8.750   1.0101   0.05198   0.04198  -0.0101   0.0235   1.0000
   9.000   1.0184   0.05495   0.04528  -0.0081   0.0235   1.0000
   9.250   1.0200   0.05799   0.04867  -0.0054   0.0235   1.0000
   9.500   1.0161   0.06099   0.05200  -0.0025   0.0234   1.0000
   9.750   1.0076   0.06397   0.05530   0.0003   0.0232   1.0000
  10.000   0.9990   0.06733   0.05892   0.0024   0.0233   1.0000
  10.250   0.9867   0.07087   0.06272   0.0040   0.0233   1.0000
  10.500   0.9725   0.07476   0.06684   0.0046   0.0233   1.0000
  10.750   0.9590   0.07901   0.07128   0.0045   0.0235   1.0000
  11.000   0.9437   0.08386   0.07630   0.0033   0.0236   1.0000
  11.250   0.9271   0.08930   0.08189   0.0010   0.0236   1.0000
  11.500   0.9108   0.09529   0.08803  -0.0022   0.0236   1.0000
  11.750   0.9006   0.10103   0.09393  -0.0054   0.0242   1.0000
  12.000   0.8819   0.10928   0.10235  -0.0114   0.0247   1.0000
  12.250   0.8581   0.12096   0.11417  -0.0194   0.0261   1.0000
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