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E169 (14.4%) (e169-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E169 (14.4%) (e169-il)
Reynolds number: 50,000
Max Cl/Cd: 26.97 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e169-il-50000-n5.txt
Download as CSV file: xf-e169-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.8151   0.10288   0.09544  -0.0045   1.0000   0.0804
 -13.750  -0.8538   0.09112   0.08348  -0.0110   1.0000   0.0807
 -13.500  -0.8774   0.08308   0.07521  -0.0153   1.0000   0.0822
 -13.250  -0.8963   0.07624   0.06810  -0.0187   1.0000   0.0844
 -13.000  -0.8970   0.07286   0.06476  -0.0195   1.0000   0.0885
 -12.750  -0.9013   0.06901   0.06085  -0.0208   1.0000   0.0929
 -12.500  -0.9125   0.06403   0.05563  -0.0228   1.0000   0.0972
 -12.250  -0.9120   0.06117   0.05285  -0.0233   1.0000   0.1025
 -12.000  -0.9175   0.05746   0.04902  -0.0244   1.0000   0.1085
 -11.750  -0.9208   0.05427   0.04583  -0.0250   1.0000   0.1150
 -11.500  -0.9253   0.05104   0.04251  -0.0256   1.0000   0.1223
 -11.250  -0.9276   0.04834   0.03985  -0.0257   1.0000   0.1300
 -11.000  -0.9334   0.04536   0.03673  -0.0257   1.0000   0.1389
 -10.750  -0.9351   0.04329   0.03473  -0.0248   1.0000   0.1481
 -10.500  -0.9379   0.04131   0.03276  -0.0234   1.0000   0.1582
 -10.250  -0.9405   0.03952   0.03094  -0.0215   1.0000   0.1694
 -10.000  -0.9385   0.03792   0.02927  -0.0197   1.0000   0.1824
  -9.750  -0.9334   0.03658   0.02789  -0.0180   1.0000   0.1965
  -9.500  -0.9252   0.03542   0.02670  -0.0163   1.0000   0.2112
  -9.250  -0.9145   0.03447   0.02571  -0.0147   1.0000   0.2264
  -9.000  -0.9016   0.03365   0.02485  -0.0131   1.0000   0.2417
  -8.750  -0.8870   0.03294   0.02408  -0.0116   1.0000   0.2569
  -8.500  -0.8710   0.03231   0.02335  -0.0102   1.0000   0.2718
  -8.250  -0.8541   0.03171   0.02266  -0.0088   1.0000   0.2863
  -8.000  -0.8364   0.03112   0.02196  -0.0075   1.0000   0.3005
  -7.750  -0.8183   0.03054   0.02125  -0.0063   1.0000   0.3145
  -7.500  -0.7977   0.03014   0.02079  -0.0051   1.0000   0.3273
  -7.250  -0.7765   0.02977   0.02036  -0.0039   1.0000   0.3394
  -7.000  -0.7558   0.02930   0.01981  -0.0028   1.0000   0.3514
  -6.750  -0.7357   0.02873   0.01914  -0.0017   1.0000   0.3636
  -6.500  -0.7162   0.02809   0.01836  -0.0006   1.0000   0.3760
  -6.250  -0.6939   0.02772   0.01794   0.0004   1.0000   0.3865
  -6.000  -0.6723   0.02725   0.01743   0.0015   1.0000   0.3969
  -5.750  -0.6521   0.02667   0.01675   0.0025   1.0000   0.4083
  -5.500  -0.6313   0.02619   0.01621   0.0036   1.0000   0.4189
  -5.250  -0.6098   0.02581   0.01581   0.0047   1.0000   0.4286
  -5.000  -0.5902   0.02528   0.01522   0.0059   1.0000   0.4394
  -4.750  -0.5705   0.02486   0.01478   0.0070   1.0000   0.4497
  -4.500  -0.5508   0.02451   0.01445   0.0083   1.0000   0.4591
  -4.250  -0.5337   0.02407   0.01396   0.0096   1.0000   0.4697
  -4.000  -0.5173   0.02381   0.01373   0.0112   1.0000   0.4790
  -3.750  -0.4848   0.02356   0.01347   0.0096   0.9852   0.4901
  -3.500  -0.4406   0.02330   0.01313   0.0060   0.9590   0.5032
  -3.250  -0.3961   0.02302   0.01277   0.0025   0.9346   0.5164
  -3.000  -0.3524   0.02279   0.01247  -0.0005   0.9111   0.5293
  -2.750  -0.3113   0.02261   0.01227  -0.0028   0.8872   0.5409
  -2.500  -0.2732   0.02242   0.01202  -0.0044   0.8638   0.5529
  -2.250  -0.2400   0.02225   0.01174  -0.0052   0.8402   0.5651
  -2.000  -0.2096   0.02211   0.01149  -0.0054   0.8179   0.5777
  -1.750  -0.1805   0.02205   0.01138  -0.0051   0.7971   0.5884
  -1.500  -0.1537   0.02197   0.01125  -0.0045   0.7766   0.6000
  -1.250  -0.1274   0.02190   0.01110  -0.0039   0.7577   0.6124
  -1.000  -0.1018   0.02184   0.01096  -0.0032   0.7400   0.6255
  -0.750  -0.0761   0.02182   0.01092  -0.0024   0.7234   0.6374
  -0.500  -0.0506   0.02180   0.01088  -0.0016   0.7074   0.6501
  -0.250  -0.0253   0.02178   0.01084  -0.0008   0.6922   0.6634
   0.000   0.0000   0.02178   0.01083   0.0000   0.6775   0.6775
   0.250   0.0252   0.02178   0.01084   0.0008   0.6634   0.6922
   0.500   0.0506   0.02180   0.01088   0.0016   0.6501   0.7074
   0.750   0.0760   0.02182   0.01092   0.0024   0.6374   0.7234
   1.000   0.1018   0.02184   0.01096   0.0032   0.6255   0.7400
   1.250   0.1274   0.02190   0.01110   0.0039   0.6124   0.7576
   1.500   0.1537   0.02197   0.01125   0.0045   0.6001   0.7766
   1.750   0.1805   0.02205   0.01138   0.0051   0.5885   0.7971
   2.000   0.2096   0.02211   0.01149   0.0054   0.5777   0.8178
   2.250   0.2400   0.02225   0.01174   0.0052   0.5651   0.8402
   2.500   0.2732   0.02242   0.01202   0.0044   0.5529   0.8638
   2.750   0.3113   0.02261   0.01227   0.0028   0.5409   0.8872
   3.000   0.3524   0.02279   0.01249   0.0005   0.5293   0.9111
   3.250   0.3961   0.02302   0.01277  -0.0025   0.5164   0.9347
   3.500   0.4406   0.02330   0.01313  -0.0060   0.5032   0.9590
   3.750   0.4848   0.02356   0.01347  -0.0096   0.4902   0.9852
   4.000   0.5174   0.02381   0.01373  -0.0112   0.4790   1.0000
   4.250   0.5338   0.02407   0.01396  -0.0096   0.4697   1.0000
   4.500   0.5509   0.02451   0.01446  -0.0083   0.4591   1.0000
   4.750   0.5705   0.02486   0.01478  -0.0071   0.4497   1.0000
   5.000   0.5903   0.02528   0.01522  -0.0059   0.4394   1.0000
   5.250   0.6098   0.02580   0.01581  -0.0047   0.4286   1.0000
   5.500   0.6313   0.02619   0.01621  -0.0036   0.4189   1.0000
   5.750   0.6522   0.02667   0.01675  -0.0025   0.4083   1.0000
   6.000   0.6723   0.02725   0.01743  -0.0015   0.3969   1.0000
   6.250   0.6939   0.02772   0.01794  -0.0004   0.3865   1.0000
   6.500   0.7162   0.02809   0.01836   0.0006   0.3759   1.0000
   6.750   0.7357   0.02873   0.01914   0.0017   0.3636   1.0000
   7.000   0.7558   0.02930   0.01981   0.0028   0.3515   1.0000
   7.250   0.7765   0.02977   0.02036   0.0039   0.3395   1.0000
   7.500   0.7977   0.03013   0.02078   0.0051   0.3273   1.0000
   7.750   0.8182   0.03054   0.02125   0.0063   0.3145   1.0000
   8.000   0.8363   0.03113   0.02197   0.0075   0.3005   1.0000
   8.250   0.8540   0.03170   0.02264   0.0088   0.2863   1.0000
   8.500   0.8710   0.03230   0.02334   0.0102   0.2718   1.0000
   8.750   0.8869   0.03294   0.02407   0.0116   0.2569   1.0000
   9.000   0.9015   0.03364   0.02484   0.0131   0.2417   1.0000
   9.250   0.9144   0.03447   0.02571   0.0147   0.2265   1.0000
   9.500   0.9252   0.03542   0.02670   0.0163   0.2113   1.0000
   9.750   0.9334   0.03657   0.02788   0.0180   0.1965   1.0000
  10.000   0.9385   0.03791   0.02926   0.0197   0.1824   1.0000
  10.250   0.9404   0.03951   0.03092   0.0215   0.1694   1.0000
  10.500   0.9379   0.04129   0.03275   0.0234   0.1581   1.0000
  10.750   0.9352   0.04328   0.03471   0.0248   0.1481   1.0000
  11.000   0.9337   0.04534   0.03671   0.0256   0.1389   1.0000
  11.250   0.9279   0.04832   0.03982   0.0256   0.1300   1.0000
  11.500   0.9256   0.05102   0.04250   0.0256   0.1223   1.0000
  11.750   0.9212   0.05424   0.04580   0.0250   0.1150   1.0000
  12.000   0.9179   0.05743   0.04899   0.0243   0.1085   1.0000
  12.250   0.9126   0.06112   0.05280   0.0233   0.1025   1.0000
  12.500   0.9125   0.06406   0.05566   0.0228   0.0971   1.0000
  12.750   0.9020   0.06896   0.06080   0.0208   0.0929   1.0000
  13.000   0.8980   0.07275   0.06464   0.0195   0.0884   1.0000
  13.250   0.8970   0.07620   0.06806   0.0186   0.0844   1.0000
  13.500   0.8787   0.08295   0.07508   0.0153   0.0824   1.0000
  13.750   0.8549   0.09104   0.08340   0.0111   0.0808   1.0000
  14.000   0.8158   0.10289   0.09545   0.0044   0.0805   1.0000
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