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Coanda 1 (coanda1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: Coanda 1 (coanda1-il)
Reynolds number: 1,000,000
Max Cl/Cd: 57.68 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-coanda1-il-1000000-n5.txt
Download as CSV file: xf-coanda1-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Coanda 1                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4441   0.10440   0.10279  -0.0106   1.0000   0.0016
  -9.000  -0.4396   0.09825   0.09668  -0.0121   1.0000   0.0024
  -8.750  -0.4427   0.09332   0.09177  -0.0130   1.0000   0.0018
  -8.500  -0.4394   0.09167   0.09014  -0.0134   1.0000   0.0023
  -8.250  -0.4460   0.08727   0.08577  -0.0139   1.0000   0.0017
  -8.000  -0.4456   0.08577   0.08429  -0.0138   1.0000   0.0025
  -7.750  -0.4587   0.08296   0.08153  -0.0125   1.0000   0.0022
  -7.500  -0.4644   0.07938   0.07797  -0.0125   1.0000   0.0021
  -7.250  -0.4457   0.07345   0.07202  -0.0199   0.9979   0.0021
  -6.750  -0.4019   0.06381   0.06229  -0.0321   0.9926   0.0027
  -6.500  -0.3767   0.05719   0.05561  -0.0393   0.9890   0.0029
  -6.250  -0.3530   0.05075   0.04906  -0.0450   0.9848   0.0028
  -6.000  -0.3313   0.04259   0.04072  -0.0498   0.9798   0.0026
  -5.750  -0.3177   0.03279   0.03056  -0.0515   0.9729   0.0025
  -5.500  -0.3100   0.01955   0.01638  -0.0500   0.9674   0.0022
  -5.250  -0.2970   0.01584   0.01211  -0.0469   0.9598   0.0021
  -5.000  -0.2719   0.01374   0.00961  -0.0463   0.9566   0.0022
  -4.750  -0.2447   0.01230   0.00789  -0.0460   0.9534   0.0022
  -4.500  -0.2191   0.01131   0.00671  -0.0454   0.9481   0.0023
  -4.250  -0.1882   0.01039   0.00559  -0.0459   0.9444   0.0024
  -4.000  -0.1546   0.00971   0.00478  -0.0471   0.9411   0.0028
  -3.750  -0.1250   0.00922   0.00417  -0.0473   0.9346   0.0033
  -3.500  -0.0917   0.00873   0.00356  -0.0484   0.9290   0.0034
  -3.250  -0.0597   0.00827   0.00305  -0.0493   0.9198   0.0046
  -3.000  -0.0269   0.00791   0.00258  -0.0503   0.9063   0.0054
  -2.750   0.0037   0.00759   0.00208  -0.0507   0.8851   0.0067
  -2.500   0.0298   0.00739   0.00171  -0.0502   0.8559   0.0096
  -2.250   0.0536   0.00732   0.00147  -0.0491   0.8184   0.0160
  -2.000   0.0726   0.00725   0.00134  -0.0471   0.7609   0.0585
  -1.750   0.0946   0.00752   0.00146  -0.0456   0.7151   0.0634
  -1.500   0.1181   0.00778   0.00159  -0.0445   0.6771   0.0666
  -1.250   0.1419   0.00802   0.00169  -0.0436   0.6392   0.0689
  -1.000   0.1654   0.00816   0.00166  -0.0426   0.6026   0.0702
  -0.750   0.1891   0.00818   0.00156  -0.0417   0.5719   0.0707
  -0.500   0.2131   0.00826   0.00152  -0.0408   0.5410   0.0714
  -0.250   0.2376   0.00830   0.00145  -0.0401   0.5179   0.0718
   0.000   0.2627   0.00835   0.00144  -0.0395   0.4992   0.0722
   0.250   0.2879   0.00839   0.00143  -0.0390   0.4808   0.0725
   0.500   0.3126   0.00844   0.00140  -0.0383   0.4588   0.0727
   0.750   0.3367   0.00844   0.00131  -0.0376   0.4308   0.0738
   1.000   0.3601   0.00853   0.00126  -0.0367   0.3909   0.0747
   1.250   0.3830   0.00872   0.00129  -0.0358   0.3449   0.0756
   1.500   0.4068   0.00887   0.00134  -0.0350   0.3136   0.0763
   1.750   0.4312   0.00898   0.00138  -0.0343   0.2909   0.0769
   2.000   0.4547   0.00917   0.00145  -0.0335   0.2553   0.0775
   2.250   0.4766   0.00950   0.00156  -0.0325   0.1985   0.0780
   2.500   0.4998   0.00974   0.00168  -0.0316   0.1656   0.0786
   2.750   0.5234   0.00994   0.00179  -0.0309   0.1406   0.0792
   3.000   0.5449   0.01033   0.00195  -0.0298   0.0896   0.0797
   3.250   0.5644   0.01094   0.00234  -0.0282   0.0134   0.0801
   3.500   0.5889   0.01108   0.00253  -0.0276   0.0088   0.0808
   3.750   0.6134   0.01122   0.00273  -0.0269   0.0070   0.0814
   4.000   0.6368   0.01147   0.00308  -0.0260   0.0056   0.0823
   4.250   0.6609   0.01165   0.00333  -0.0253   0.0047   0.0841
   4.500   0.6847   0.01187   0.00358  -0.0246   0.0038   0.0853
   4.750   0.7064   0.01231   0.00412  -0.0234   0.0034   0.0861
   5.000   0.7283   0.01273   0.00462  -0.0222   0.0030   0.0880
   5.250   0.7489   0.01329   0.00529  -0.0207   0.0028   0.0916
   5.500   0.7676   0.01402   0.00613  -0.0189   0.0026   0.0942
   5.750   0.7894   0.01439   0.00658  -0.0179   0.0023   0.0974
   6.000   0.8119   0.01468   0.00691  -0.0171   0.0020   0.1001
   6.250   0.8263   0.01577   0.00812  -0.0146   0.0019   0.1066
   6.500   0.8437   0.01665   0.00911  -0.0124   0.0014   0.1237
   7.000   0.9329   0.01982   0.01434  -0.0210   0.0012   0.9807
   7.250   0.9596   0.02178   0.01650  -0.0210   0.0012   0.9840
   7.500   0.9765   0.02381   0.01875  -0.0187   0.0012   0.9867
   7.750   1.0026   0.02665   0.02189  -0.0188   0.0013   0.9884
   8.000   1.0227   0.02967   0.02523  -0.0179   0.0014   0.9898
   8.250   1.0396   0.03215   0.02796  -0.0168   0.0015   0.9912
   8.500   1.0516   0.03517   0.03126  -0.0151   0.0016   0.9931
   8.750   1.0594   0.03820   0.03455  -0.0132   0.0017   0.9951
  11.250   0.9378   0.07754   0.07552  -0.0039   0.0019   1.0000
  11.500   0.9222   0.08437   0.08244  -0.0084   0.0019   1.0000
  11.750   0.9073   0.09208   0.09025  -0.0137   0.0019   1.0000
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