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Coanda 2 (coanda2-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Coanda 2 (coanda2-il)
Reynolds number: 100,000
Max Cl/Cd: 53.21 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-coanda2-il-100000.txt
Download as CSV file: xf-coanda2-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4267   0.10150   0.09669  -0.0179   1.0000   0.0723
  -8.500  -0.4355   0.09981   0.09511  -0.0192   1.0000   0.0727
  -8.250  -0.4411   0.09788   0.09325  -0.0214   1.0000   0.0729
  -8.000  -0.4419   0.09535   0.09076  -0.0247   1.0000   0.0731
  -7.750  -0.4396   0.09238   0.08779  -0.0275   1.0000   0.0733
  -7.500  -0.4325   0.08568   0.08119  -0.0216   1.0000   0.0746
  -7.250  -0.4264   0.08198   0.07748  -0.0191   1.0000   0.0763
  -7.000  -0.4227   0.07872   0.07425  -0.0194   1.0000   0.0771
  -6.750  -0.4184   0.07546   0.07101  -0.0200   1.0000   0.0779
  -6.500  -0.4134   0.07205   0.06760  -0.0207   1.0000   0.0790
  -6.250  -0.4069   0.06865   0.06418  -0.0215   1.0000   0.0801
  -6.000  -0.3989   0.06517   0.06066  -0.0223   1.0000   0.0811
  -5.750  -0.3895   0.06157   0.05699  -0.0232   1.0000   0.0821
  -5.500  -0.3734   0.05317   0.04805  -0.0281   1.0000   0.0609
  -5.250  -0.3654   0.04968   0.04459  -0.0262   1.0000   0.0596
  -5.000  -0.3545   0.04587   0.04063  -0.0251   1.0000   0.0582
  -4.750  -0.3418   0.04167   0.03617  -0.0239   1.0000   0.0578
  -4.500  -0.3280   0.03725   0.03131  -0.0224   1.0000   0.0592
  -4.250  -0.3123   0.03645   0.03046  -0.0206   1.0000   0.0682
  -3.750  -0.2824   0.02980   0.02277  -0.0157   1.0000   0.0885
  -3.500  -0.2684   0.02920   0.02191  -0.0135   1.0000   0.1246
  -3.000  -0.2956   0.03077   0.02561   0.0004   1.0000   0.4104
  -2.750  -0.3008   0.02945   0.02456   0.0091   1.0000   0.4928
  -2.500  -0.2954   0.02800   0.02316   0.0146   1.0000   0.5404
  -2.250  -0.1864   0.02549   0.01773  -0.0057   1.0000   0.2238
  -2.000  -0.1621   0.02428   0.01622  -0.0046   1.0000   0.2042
  -1.750  -0.1391   0.02376   0.01523  -0.0033   1.0000   0.1943
  -1.500  -0.1180   0.02279   0.01414  -0.0022   1.0000   0.1910
  -1.250  -0.0956   0.02251   0.01340  -0.0007   1.0000   0.1810
  -1.000  -0.0747   0.02169   0.01255   0.0002   1.0000   0.1784
  -0.750  -0.0541   0.02118   0.01195   0.0013   1.0000   0.1757
  -0.500  -0.0168   0.02087   0.01148  -0.0010   0.9947   0.1730
  -0.250   0.0387   0.02062   0.01106  -0.0067   0.9830   0.1712
   0.000   0.0931   0.02027   0.01066  -0.0121   0.9702   0.1714
   0.250   0.1476   0.01987   0.01032  -0.0176   0.9566   0.1760
   0.500   0.2027   0.01935   0.00985  -0.0229   0.9426   0.1787
   0.750   0.2545   0.01869   0.00931  -0.0273   0.9264   0.1801
   1.000   0.3114   0.01787   0.00867  -0.0327   0.9099   0.1833
   1.250   0.3725   0.01700   0.00797  -0.0386   0.8933   0.1901
   1.500   0.4359   0.01604   0.00718  -0.0448   0.8750   0.2016
   1.750   0.4907   0.01511   0.00653  -0.0491   0.8460   0.2280
   2.000   0.6326   0.01270   0.00585  -0.0722   0.7794   1.0000
   2.250   0.6680   0.01271   0.00555  -0.0726   0.7119   1.0000
   2.500   0.6960   0.01308   0.00558  -0.0718   0.6542   1.0000
   2.750   0.7163   0.01361   0.00569  -0.0695   0.5913   1.0000
   3.000   0.7358   0.01410   0.00587  -0.0674   0.5384   1.0000
   3.250   0.7558   0.01453   0.00610  -0.0656   0.4931   1.0000
   3.500   0.7777   0.01495   0.00641  -0.0642   0.4606   1.0000
   3.750   0.7998   0.01538   0.00683  -0.0629   0.4312   1.0000
   4.000   0.8182   0.01583   0.00706  -0.0609   0.3783   1.0000
   4.250   0.8386   0.01627   0.00736  -0.0594   0.3325   1.0000
   4.500   0.8608   0.01670   0.00779  -0.0581   0.2982   1.0000
   4.750   0.8817   0.01728   0.00824  -0.0567   0.2503   1.0000
   5.000   0.9003   0.01823   0.00879  -0.0550   0.1728   1.0000
   5.250   0.9135   0.02018   0.00993  -0.0528   0.0586   1.0000
   5.500   0.9314   0.02154   0.01128  -0.0508   0.0443   1.0000
   5.750   0.9489   0.02287   0.01274  -0.0488   0.0396   1.0000
   6.000   0.9661   0.02412   0.01419  -0.0466   0.0384   1.0000
   6.250   0.9822   0.02544   0.01570  -0.0443   0.0377   1.0000
   6.500   0.9975   0.02693   0.01733  -0.0419   0.0375   1.0000
   6.750   1.0142   0.02864   0.01912  -0.0397   0.0375   1.0000
   7.000   1.0338   0.03070   0.02125  -0.0380   0.0377   1.0000
   7.250   1.0567   0.03335   0.02399  -0.0367   0.0383   1.0000
   7.500   1.0808   0.03706   0.02791  -0.0359   0.0392   1.0000
   7.750   1.1015   0.03844   0.02968  -0.0339   0.0405   1.0000
   8.000   1.1181   0.04128   0.03312  -0.0313   0.0426   1.0000
   8.250   1.1264   0.04489   0.03733  -0.0283   0.0437   1.0000
   8.500   1.1304   0.04855   0.04150  -0.0251   0.0442   1.0000
   8.750   1.1290   0.05275   0.04620  -0.0218   0.0457   1.0000
   9.000   1.1243   0.05724   0.05108  -0.0187   0.0475   1.0000
   9.250   1.1199   0.06216   0.05622  -0.0164   0.0494   1.0000
   9.500   1.1132   0.06578   0.06026  -0.0132   0.0530   1.0000
   9.750   1.0795   0.06979   0.06465  -0.0091   0.0543   1.0000
  10.000   1.0485   0.07430   0.06939  -0.0074   0.0552   1.0000
  10.250   1.0212   0.07964   0.07489  -0.0086   0.0553   1.0000
  10.500   0.9855   0.08852   0.08394  -0.0144   0.0583   1.0000
  10.750   0.9531   0.09947   0.09494  -0.0231   0.0585   1.0000
  11.000   0.9326   0.10976   0.10512  -0.0291   0.0603   1.0000
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