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E168 (12.45%) (e168-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E168 (12.45%) (e168-il)
Reynolds number: 100,000
Max Cl/Cd: 38.36 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e168-il-100000.txt
Download as CSV file: xf-e168-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E168  (12.45%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.7162   0.13545   0.13032   0.0138   1.0000   0.0731
 -13.500  -0.8147   0.10241   0.09733  -0.0062   1.0000   0.0604
 -13.250  -0.8431   0.09234   0.08722  -0.0121   1.0000   0.0594
 -13.000  -0.8739   0.08294   0.07773  -0.0182   1.0000   0.0579
 -12.750  -0.9093   0.07414   0.06875  -0.0244   1.0000   0.0568
 -12.500  -0.9423   0.06677   0.06118  -0.0290   1.0000   0.0555
 -12.250  -0.9701   0.06115   0.05530  -0.0316   1.0000   0.0550
 -12.000  -0.9929   0.05670   0.05059  -0.0323   1.0000   0.0546
 -11.750  -1.0084   0.05332   0.04697  -0.0314   1.0000   0.0550
 -11.500  -1.0197   0.05049   0.04392  -0.0293   1.0000   0.0560
 -11.250  -1.0263   0.04769   0.04081  -0.0273   1.0000   0.0573
 -11.000  -1.0282   0.04478   0.03751  -0.0253   1.0000   0.0586
 -10.750  -1.0257   0.04207   0.03435  -0.0233   1.0000   0.0601
 -10.500  -1.0124   0.03885   0.03107  -0.0224   1.0000   0.0632
 -10.250  -0.9988   0.03704   0.02919  -0.0213   1.0000   0.0674
 -10.000  -0.9861   0.03501   0.02680  -0.0196   1.0000   0.0716
  -9.750  -0.9677   0.03259   0.02448  -0.0188   1.0000   0.0770
  -9.500  -0.9531   0.03102   0.02264  -0.0172   1.0000   0.0843
  -9.250  -0.9360   0.02907   0.02086  -0.0161   1.0000   0.0935
  -9.000  -0.9206   0.02739   0.01919  -0.0147   1.0000   0.1054
  -8.750  -0.9056   0.02586   0.01768  -0.0131   1.0000   0.1212
  -8.500  -0.8907   0.02446   0.01637  -0.0115   1.0000   0.1410
  -8.250  -0.8751   0.02339   0.01529  -0.0099   1.0000   0.1658
  -8.000  -0.8586   0.02254   0.01460  -0.0085   1.0000   0.1914
  -7.750  -0.8408   0.02192   0.01403  -0.0070   1.0000   0.2173
  -7.500  -0.8219   0.02143   0.01354  -0.0056   1.0000   0.2421
  -7.250  -0.8019   0.02105   0.01312  -0.0043   1.0000   0.2653
  -7.000  -0.7808   0.02065   0.01274  -0.0031   1.0000   0.2857
  -6.750  -0.7589   0.02033   0.01243  -0.0020   1.0000   0.3047
  -6.500  -0.7369   0.01999   0.01204  -0.0009   1.0000   0.3233
  -6.250  -0.7149   0.01964   0.01162   0.0003   1.0000   0.3413
  -6.000  -0.6924   0.01929   0.01125   0.0014   1.0000   0.3582
  -5.750  -0.6694   0.01895   0.01094   0.0024   1.0000   0.3742
  -5.500  -0.6465   0.01862   0.01060   0.0035   1.0000   0.3898
  -5.250  -0.6237   0.01827   0.01026   0.0045   1.0000   0.4052
  -5.000  -0.6009   0.01793   0.00993   0.0056   1.0000   0.4204
  -4.750  -0.5783   0.01759   0.00960   0.0067   1.0000   0.4355
  -4.500  -0.5557   0.01726   0.00927   0.0077   1.0000   0.4506
  -4.250  -0.5335   0.01694   0.00897   0.0088   1.0000   0.4655
  -4.000  -0.5116   0.01663   0.00869   0.0100   1.0000   0.4805
  -3.750  -0.4903   0.01634   0.00843   0.0111   1.0000   0.4956
  -3.500  -0.4699   0.01607   0.00821   0.0124   1.0000   0.5106
  -3.250  -0.4510   0.01585   0.00804   0.0139   1.0000   0.5257
  -3.000  -0.4340   0.01567   0.00792   0.0155   1.0000   0.5407
  -2.750  -0.4189   0.01557   0.00786   0.0172   1.0000   0.5557
  -2.500  -0.4053   0.01555   0.00791   0.0189   1.0000   0.5705
  -2.250  -0.3480   0.01554   0.00803   0.0128   0.9827   0.5923
  -2.000  -0.2954   0.01543   0.00796   0.0078   0.9631   0.6154
  -1.750  -0.2419   0.01526   0.00790   0.0031   0.9455   0.6373
  -1.500  -0.1910   0.01505   0.00776  -0.0009   0.9276   0.6599
  -1.250  -0.1468   0.01485   0.00762  -0.0034   0.9064   0.6816
  -1.000  -0.1086   0.01469   0.00752  -0.0045   0.8830   0.7020
  -0.750  -0.0772   0.01459   0.00743  -0.0042   0.8581   0.7234
  -0.500  -0.0491   0.01453   0.00738  -0.0032   0.8343   0.7438
  -0.250  -0.0244   0.01451   0.00738  -0.0017   0.8094   0.7645
   0.000   0.0000   0.01449   0.00733   0.0000   0.7876   0.7876
   0.250   0.0243   0.01451   0.00738   0.0017   0.7645   0.8094
   0.500   0.0490   0.01453   0.00738   0.0032   0.7438   0.8343
   0.750   0.0772   0.01459   0.00743   0.0043   0.7234   0.8581
   1.000   0.1086   0.01469   0.00752   0.0045   0.7020   0.8830
   1.250   0.1468   0.01485   0.00763   0.0034   0.6816   0.9064
   1.500   0.1910   0.01505   0.00776   0.0009   0.6599   0.9276
   1.750   0.2419   0.01526   0.00790  -0.0031   0.6373   0.9455
   2.000   0.2954   0.01543   0.00796  -0.0078   0.6154   0.9631
   2.250   0.3478   0.01554   0.00803  -0.0128   0.5923   0.9827
   2.500   0.4052   0.01554   0.00791  -0.0189   0.5705   1.0000
   2.750   0.4189   0.01557   0.00786  -0.0172   0.5556   1.0000
   3.000   0.4340   0.01567   0.00792  -0.0155   0.5408   1.0000
   3.250   0.4510   0.01584   0.00804  -0.0139   0.5256   1.0000
   3.500   0.4699   0.01607   0.00821  -0.0124   0.5106   1.0000
   3.750   0.4903   0.01634   0.00843  -0.0111   0.4955   1.0000
   4.000   0.5116   0.01663   0.00869  -0.0100   0.4805   1.0000
   4.250   0.5335   0.01693   0.00897  -0.0088   0.4655   1.0000
   4.500   0.5557   0.01726   0.00927  -0.0077   0.4505   1.0000
   4.750   0.5783   0.01759   0.00960  -0.0067   0.4355   1.0000
   5.000   0.6009   0.01793   0.00993  -0.0056   0.4204   1.0000
   5.250   0.6237   0.01827   0.01026  -0.0045   0.4052   1.0000
   5.500   0.6465   0.01862   0.01060  -0.0035   0.3898   1.0000
   5.750   0.6694   0.01895   0.01094  -0.0024   0.3741   1.0000
   6.000   0.6924   0.01929   0.01125  -0.0013   0.3582   1.0000
   6.250   0.7149   0.01964   0.01162  -0.0003   0.3413   1.0000
   6.500   0.7369   0.01999   0.01204   0.0009   0.3233   1.0000
   6.750   0.7589   0.02033   0.01244   0.0020   0.3047   1.0000
   7.000   0.7808   0.02065   0.01274   0.0031   0.2857   1.0000
   7.250   0.8019   0.02105   0.01312   0.0043   0.2653   1.0000
   7.500   0.8219   0.02143   0.01354   0.0057   0.2421   1.0000
   7.750   0.8408   0.02192   0.01403   0.0070   0.2173   1.0000
   8.000   0.8586   0.02254   0.01459   0.0085   0.1913   1.0000
   8.250   0.8751   0.02339   0.01530   0.0100   0.1657   1.0000
   8.500   0.8907   0.02446   0.01637   0.0115   0.1410   1.0000
   8.750   0.9056   0.02586   0.01768   0.0131   0.1211   1.0000
   9.000   0.9205   0.02739   0.01919   0.0147   0.1052   1.0000
   9.250   0.9359   0.02906   0.02086   0.0161   0.0934   1.0000
   9.500   0.9532   0.03103   0.02264   0.0172   0.0844   1.0000
   9.750   0.9680   0.03261   0.02451   0.0188   0.0772   1.0000
  10.000   0.9863   0.03501   0.02680   0.0196   0.0717   1.0000
  10.250   0.9987   0.03700   0.02916   0.0212   0.0674   1.0000
  10.500   1.0124   0.03884   0.03106   0.0224   0.0631   1.0000
  10.750   1.0259   0.04209   0.03437   0.0233   0.0601   1.0000
  11.000   1.0285   0.04478   0.03750   0.0253   0.0587   1.0000
  11.250   1.0263   0.04771   0.04083   0.0273   0.0573   1.0000
  11.500   1.0197   0.05053   0.04396   0.0293   0.0560   1.0000
  11.750   1.0083   0.05338   0.04704   0.0313   0.0551   1.0000
  12.000   0.9933   0.05671   0.05060   0.0322   0.0546   1.0000
  12.250   0.9730   0.06087   0.05500   0.0317   0.0546   1.0000
  12.500   0.9460   0.06633   0.06071   0.0292   0.0548   1.0000
  12.750   0.9096   0.07415   0.06877   0.0243   0.0567   1.0000
  13.000   0.8747   0.08297   0.07776   0.0181   0.0580   1.0000
  13.250   0.8442   0.09233   0.08721   0.0120   0.0595   1.0000
  13.500   0.8157   0.10240   0.09731   0.0060   0.0604   1.0000
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