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Coanda 2 (coanda2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: Coanda 2 (coanda2-il)
Reynolds number: 1,000,000
Max Cl/Cd: 58.9 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-coanda2-il-1000000-n5.txt
Download as CSV file: xf-coanda2-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4529   0.08612   0.08463  -0.0152   1.0000   0.0026
  -8.500  -0.4610   0.08292   0.08146  -0.0151   1.0000   0.0024
  -8.250  -0.4694   0.08087   0.07944  -0.0137   1.0000   0.0026
  -8.000  -0.4726   0.07635   0.07495  -0.0158   0.9995   0.0026
  -7.750  -0.4539   0.06971   0.06829  -0.0244   0.9970   0.0027
  -7.500  -0.4350   0.06065   0.05918  -0.0353   0.9933   0.0025
  -7.250  -0.4178   0.04481   0.04308  -0.0501   0.9878   0.0023
  -7.000  -0.4121   0.02839   0.02589  -0.0566   0.9798   0.0021
  -6.750  -0.4033   0.01948   0.01623  -0.0554   0.9739   0.0021
  -6.500  -0.3815   0.01690   0.01328  -0.0546   0.9698   0.0021
  -6.250  -0.3559   0.01483   0.01085  -0.0543   0.9673   0.0021
  -6.000  -0.3359   0.01363   0.00945  -0.0526   0.9607   0.0022
  -5.750  -0.3088   0.01258   0.00820  -0.0524   0.9567   0.0024
  -5.500  -0.2788   0.01157   0.00697  -0.0528   0.9533   0.0025
  -5.250  -0.2520   0.01084   0.00607  -0.0523   0.9465   0.0027
  -5.000  -0.2160   0.01023   0.00533  -0.0540   0.9417   0.0031
  -4.750  -0.1837   0.00964   0.00460  -0.0549   0.9347   0.0034
  -4.500  -0.1500   0.00908   0.00396  -0.0562   0.9284   0.0041
  -4.250  -0.1180   0.00866   0.00345  -0.0570   0.9199   0.0048
  -4.000  -0.0857   0.00830   0.00298  -0.0578   0.9095   0.0055
  -3.750  -0.0562   0.00789   0.00241  -0.0580   0.8980   0.0067
  -3.250  -0.0019   0.00748   0.00179  -0.0574   0.8719   0.0121
  -3.000   0.0224   0.00709   0.00153  -0.0566   0.8577   0.0548
  -2.750   0.0499   0.00732   0.00179  -0.0563   0.8403   0.0639
  -2.500   0.0758   0.00755   0.00193  -0.0556   0.8157   0.0673
  -2.250   0.0992   0.00771   0.00194  -0.0544   0.7785   0.0683
  -2.000   0.1201   0.00813   0.00215  -0.0527   0.7191   0.0692
  -1.750   0.1394   0.00835   0.00210  -0.0507   0.6553   0.0694
  -1.500   0.1613   0.00848   0.00205  -0.0493   0.6136   0.0695
  -1.250   0.1841   0.00842   0.00186  -0.0482   0.5822   0.0702
  -1.000   0.2071   0.00834   0.00166  -0.0471   0.5526   0.0710
  -0.750   0.2300   0.00838   0.00155  -0.0460   0.5139   0.0717
  -0.500   0.2530   0.00845   0.00148  -0.0450   0.4749   0.0722
  -0.250   0.2765   0.00854   0.00143  -0.0441   0.4429   0.0727
   0.000   0.3008   0.00858   0.00140  -0.0433   0.4188   0.0731
   0.250   0.3253   0.00864   0.00137  -0.0426   0.3991   0.0734
   0.500   0.3501   0.00867   0.00135  -0.0419   0.3809   0.0737
   0.750   0.3753   0.00869   0.00134  -0.0413   0.3693   0.0741
   1.000   0.4006   0.00870   0.00134  -0.0408   0.3576   0.0744
   1.250   0.4261   0.00872   0.00134  -0.0403   0.3468   0.0748
   1.500   0.4513   0.00876   0.00136  -0.0397   0.3339   0.0751
   1.750   0.4727   0.00910   0.00144  -0.0385   0.2709   0.0755
   2.000   0.4958   0.00933   0.00153  -0.0376   0.2308   0.0760
   2.250   0.5180   0.00966   0.00167  -0.0366   0.1837   0.0767
   2.500   0.5372   0.01027   0.00191  -0.0350   0.1026   0.0775
   2.750   0.5566   0.01093   0.00228  -0.0334   0.0146   0.0780
   3.000   0.5814   0.01106   0.00246  -0.0328   0.0104   0.0786
   3.250   0.6061   0.01119   0.00265  -0.0322   0.0081   0.0797
   3.500   0.6307   0.01135   0.00286  -0.0315   0.0068   0.0808
   3.750   0.6542   0.01162   0.00324  -0.0306   0.0055   0.0819
   4.000   0.6785   0.01181   0.00347  -0.0300   0.0047   0.0830
   4.250   0.7023   0.01204   0.00375  -0.0292   0.0041   0.0843
   4.500   0.7256   0.01232   0.00407  -0.0283   0.0035   0.0871
   4.750   0.7468   0.01283   0.00470  -0.0270   0.0032   0.0905
   5.000   0.7681   0.01334   0.00532  -0.0257   0.0029   0.0934
   5.250   0.7880   0.01395   0.00602  -0.0241   0.0028   0.0956
   5.500   0.8055   0.01476   0.00694  -0.0221   0.0026   0.0990
   5.750   0.8232   0.01553   0.00780  -0.0201   0.0025   0.1059
   6.000   0.8401   0.01474   0.00852  -0.0185   0.0022   0.8133
   6.500   1.0329   0.02069   0.01521  -0.0511   0.0013   0.9973
   6.750   1.0643   0.02297   0.01771  -0.0520   0.0012   0.9991
   7.000   1.0898   0.02537   0.02036  -0.0518   0.0012   1.0000
   7.250   1.1048   0.02761   0.02283  -0.0494   0.0012   1.0000
   7.500   1.1179   0.02990   0.02537  -0.0468   0.0013   1.0000
   7.750   1.1279   0.03261   0.02835  -0.0438   0.0013   1.0000
   8.000   1.1352   0.03548   0.03148  -0.0406   0.0014   1.0000
   8.250   1.1409   0.03812   0.03436  -0.0375   0.0014   1.0000
   8.500   1.1422   0.04109   0.03759  -0.0340   0.0014   1.0000
   8.750   1.1415   0.04389   0.04061  -0.0305   0.0015   1.0000
   9.000   1.1348   0.04710   0.04404  -0.0267   0.0015   1.0000
   9.250   1.1284   0.04981   0.04693  -0.0231   0.0015   1.0000
   9.500   1.1071   0.05232   0.04959  -0.0175   0.0016   1.0000
   9.750   1.0900   0.05492   0.05235  -0.0138   0.0016   1.0000
  10.000   1.0721   0.05823   0.05579  -0.0119   0.0016   1.0000
  10.250   1.0544   0.06222   0.05992  -0.0118   0.0016   1.0000
  10.500   1.0388   0.06687   0.06470  -0.0135   0.0016   1.0000
  10.750   1.0208   0.07312   0.07108  -0.0174   0.0016   1.0000
  11.000   1.0034   0.08059   0.07869  -0.0228   0.0016   1.0000
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