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E169 (14.4%) (e169-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E169 (14.4%) (e169-il)
Reynolds number: 50,000
Max Cl/Cd: 16.65 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e169-il-50000.txt
Download as CSV file: xf-e169-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E169  (14.4%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.5568   0.13694   0.12909   0.0278   1.0000   0.3390
 -11.750  -0.5611   0.13374   0.12589   0.0267   1.0000   0.3466
 -11.500  -0.6180   0.12098   0.11324   0.0159   1.0000   0.2697
 -11.250  -0.5997   0.11786   0.11003   0.0165   1.0000   0.2812
 -11.000  -0.6046   0.11244   0.10459   0.0144   1.0000   0.2806
 -10.750  -0.6135   0.10679   0.09894   0.0122   1.0000   0.2807
 -10.500  -0.6271   0.10069   0.09286   0.0095   1.0000   0.2815
 -10.250  -0.6157   0.09822   0.09033   0.0101   1.0000   0.2947
 -10.000  -0.5562   0.10757   0.09951   0.0208   1.0000   0.3902
  -9.750  -0.5357   0.10282   0.09466   0.0201   1.0000   0.3943
  -9.500  -0.6150   0.08705   0.07907   0.0085   1.0000   0.3238
  -9.250  -0.6481   0.07977   0.07190   0.0053   1.0000   0.3275
  -9.000  -0.6327   0.07810   0.07014   0.0065   1.0000   0.3412
  -8.750  -0.6205   0.07611   0.06809   0.0074   1.0000   0.3549
  -8.500  -0.6148   0.07337   0.06531   0.0078   1.0000   0.3667
  -8.250  -0.6596   0.06584   0.05793   0.0054   1.0000   0.3727
  -8.000  -0.6413   0.06475   0.05675   0.0070   1.0000   0.3866
  -7.750  -0.6294   0.06293   0.05485   0.0082   1.0000   0.3993
  -7.500  -0.6796   0.05496   0.04700   0.0064   1.0000   0.4080
  -7.250  -0.6951   0.05047   0.04243   0.0066   1.0000   0.4209
  -7.000  -0.6604   0.05113   0.04300   0.0088   1.0000   0.4345
  -6.750  -0.6352   0.05070   0.04250   0.0106   1.0000   0.4473
  -6.500  -0.6232   0.04893   0.04068   0.0118   1.0000   0.4597
  -6.250  -0.6197   0.04640   0.03809   0.0127   1.0000   0.4723
  -6.000  -0.6200   0.04351   0.03512   0.0135   1.0000   0.4852
  -5.750  -0.6076   0.04193   0.03345   0.0147   1.0000   0.4981
  -5.500  -0.5816   0.04155   0.03306   0.0164   1.0000   0.5090
  -5.250  -0.5683   0.04008   0.03156   0.0177   1.0000   0.5211
  -5.000  -0.5605   0.03822   0.02965   0.0190   1.0000   0.5336
  -4.750  -0.5540   0.03637   0.02772   0.0203   1.0000   0.5467
  -4.500  -0.5318   0.03598   0.02738   0.0222   1.0000   0.5574
  -4.250  -0.5195   0.03487   0.02628   0.0240   1.0000   0.5686
  -4.000  -0.5136   0.03354   0.02495   0.0259   1.0000   0.5808
  -3.750  -0.5109   0.03238   0.02377   0.0282   1.0000   0.5928
  -3.500  -0.5034   0.03193   0.02337   0.0311   1.0000   0.6022
  -3.250  -0.5036   0.03107   0.02249   0.0336   1.0000   0.6133
  -3.000  -0.5028   0.03019   0.02156   0.0354   1.0000   0.6256
  -2.750  -0.4953   0.02992   0.02132   0.0376   1.0000   0.6357
  -2.500  -0.4881   0.02949   0.02087   0.0391   1.0000   0.6473
  -2.250  -0.4420   0.02944   0.02076   0.0342   0.9843   0.6637
  -2.000  -0.3852   0.02943   0.02070   0.0279   0.9625   0.6815
  -1.750  -0.3287   0.02934   0.02056   0.0221   0.9421   0.6991
  -1.500  -0.2718   0.02921   0.02039   0.0164   0.9233   0.7172
  -1.250  -0.2221   0.02905   0.02019   0.0122   0.9042   0.7345
  -1.000  -0.1726   0.02888   0.02001   0.0084   0.8859   0.7517
  -0.750  -0.1259   0.02878   0.01991   0.0055   0.8683   0.7681
  -0.500  -0.0819   0.02869   0.01982   0.0032   0.8510   0.7844
  -0.250  -0.0402   0.02864   0.01977   0.0015   0.8340   0.8008
   0.000   0.0000   0.02861   0.01973   0.0000   0.8172   0.8172
   0.250   0.0402   0.02864   0.01976  -0.0015   0.8008   0.8340
   0.500   0.0818   0.02869   0.01981  -0.0032   0.7844   0.8509
   0.750   0.1261   0.02878   0.01991  -0.0055   0.7680   0.8683
   1.000   0.1726   0.02887   0.02000  -0.0084   0.7517   0.8859
   1.250   0.2221   0.02905   0.02019  -0.0122   0.7344   0.9042
   1.500   0.2719   0.02920   0.02039  -0.0164   0.7172   0.9232
   1.750   0.3290   0.02934   0.02056  -0.0221   0.6992   0.9422
   2.000   0.3851   0.02943   0.02070  -0.0279   0.6816   0.9625
   2.250   0.4419   0.02943   0.02077  -0.0342   0.6637   0.9843
   2.500   0.4881   0.02948   0.02087  -0.0391   0.6474   1.0000
   2.750   0.4953   0.02993   0.02133  -0.0376   0.6357   1.0000
   3.000   0.5028   0.03019   0.02155  -0.0354   0.6256   1.0000
   3.250   0.5037   0.03106   0.02249  -0.0336   0.6133   1.0000
   3.500   0.5034   0.03193   0.02337  -0.0311   0.6022   1.0000
   3.750   0.5110   0.03237   0.02376  -0.0282   0.5929   1.0000
   4.000   0.5137   0.03354   0.02495  -0.0259   0.5808   1.0000
   4.250   0.5195   0.03487   0.02628  -0.0240   0.5686   1.0000
   4.500   0.5318   0.03598   0.02738  -0.0222   0.5575   1.0000
   4.750   0.5541   0.03636   0.02771  -0.0203   0.5467   1.0000
   5.000   0.5606   0.03820   0.02963  -0.0190   0.5336   1.0000
   5.250   0.5684   0.04008   0.03155  -0.0177   0.5211   1.0000
   5.500   0.5816   0.04155   0.03306  -0.0164   0.5090   1.0000
   5.750   0.6078   0.04191   0.03344  -0.0147   0.4981   1.0000
   6.000   0.6201   0.04349   0.03509  -0.0135   0.4852   1.0000
   6.250   0.6199   0.04637   0.03806  -0.0127   0.4723   1.0000
   6.500   0.6235   0.04889   0.04064  -0.0118   0.4596   1.0000
   6.750   0.6352   0.05068   0.04248  -0.0106   0.4472   1.0000
   7.000   0.6606   0.05110   0.04298  -0.0088   0.4345   1.0000
   7.250   0.6958   0.05040   0.04236  -0.0065   0.4210   1.0000
   7.500   0.6763   0.05531   0.04734  -0.0066   0.4082   1.0000
   7.750   0.6295   0.06293   0.05484  -0.0082   0.3994   1.0000
   8.000   0.6416   0.06472   0.05672  -0.0070   0.3867   1.0000
   8.250   0.6590   0.06590   0.05798  -0.0054   0.3726   1.0000
   8.500   0.6151   0.07335   0.06529  -0.0079   0.3668   1.0000
   8.750   0.6208   0.07610   0.06808  -0.0074   0.3549   1.0000
   9.000   0.7179   0.06786   0.06023   0.0006   0.3288   1.0000
   9.250   0.6477   0.07982   0.07194  -0.0054   0.3274   1.0000
   9.500   0.6156   0.08696   0.07899  -0.0085   0.3236   1.0000
   9.750   0.6252   0.08941   0.08150  -0.0080   0.3103   1.0000
  10.000   0.6393   0.09152   0.08369  -0.0071   0.2971   1.0000
  10.250   0.6161   0.09819   0.09029  -0.0101   0.2946   1.0000
  10.500   0.6275   0.10067   0.09284  -0.0096   0.2814   1.0000
  10.750   0.6136   0.10678   0.09892  -0.0122   0.2806   1.0000
  11.000   0.6047   0.11242   0.10457  -0.0145   0.2804   1.0000
  11.250   0.6002   0.11785   0.11001  -0.0166   0.2812   1.0000
  11.500   0.6182   0.12098   0.11324  -0.0160   0.2698   1.0000
  11.750   0.5634   0.13385   0.12601  -0.0268   0.3463   1.0000
  12.000   0.5575   0.13694   0.12908  -0.0278   0.3390   1.0000
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