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E197 (13.49%) (e197-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E197 (13.49%) (e197-il)
Reynolds number: 50,000
Max Cl/Cd: 25.89 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e197-il-50000-n5.txt
Download as CSV file: xf-e197-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E197  (13.49%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4147   0.10053   0.09348  -0.0451   1.0000   0.0539
 -10.500  -0.4203   0.09521   0.08825  -0.0476   1.0000   0.0535
 -10.250  -0.4281   0.08950   0.08262  -0.0504   1.0000   0.0529
 -10.000  -0.4413   0.08253   0.07574  -0.0543   1.0000   0.0522
  -9.750  -0.4619   0.07508   0.06838  -0.0593   1.0000   0.0513
  -9.500  -0.4913   0.06845   0.06179  -0.0636   1.0000   0.0505
  -9.250  -0.5229   0.06415   0.05750  -0.0639   1.0000   0.0499
  -9.000  -0.5489   0.06062   0.05391  -0.0623   1.0000   0.0495
  -8.750  -0.5692   0.05748   0.05067  -0.0600   1.0000   0.0494
  -8.500  -0.5862   0.05475   0.04779  -0.0571   1.0000   0.0492
  -8.250  -0.6007   0.05239   0.04527  -0.0537   1.0000   0.0494
  -8.000  -0.6127   0.05028   0.04297  -0.0502   1.0000   0.0495
  -7.750  -0.5993   0.04670   0.03896  -0.0514   0.9911   0.0503
  -7.500  -0.5740   0.04307   0.03480  -0.0540   0.9795   0.0516
  -7.250  -0.5456   0.04009   0.03123  -0.0562   0.9688   0.0546
  -7.000  -0.5165   0.03748   0.02809  -0.0579   0.9580   0.0579
  -6.750  -0.4870   0.03555   0.02606  -0.0593   0.9478   0.0613
  -6.500  -0.4532   0.03360   0.02383  -0.0609   0.9396   0.0652
  -6.250  -0.4211   0.03186   0.02177  -0.0618   0.9304   0.0702
  -6.000  -0.3914   0.03047   0.02034  -0.0629   0.9210   0.0785
  -5.750  -0.3587   0.02905   0.01882  -0.0644   0.9134   0.0934
  -5.500  -0.3338   0.02776   0.01756  -0.0647   0.9030   0.1141
  -5.250  -0.3064   0.02648   0.01645  -0.0656   0.8945   0.1560
  -5.000  -0.2807   0.02529   0.01555  -0.0662   0.8855   0.2148
  -4.750  -0.2572   0.02438   0.01487  -0.0661   0.8762   0.2787
  -4.500  -0.2293   0.02375   0.01451  -0.0664   0.8689   0.3546
  -4.250  -0.2080   0.02358   0.01442  -0.0652   0.8590   0.4178
  -4.000  -0.1811   0.02345   0.01425  -0.0647   0.8521   0.4735
  -3.750  -0.1592   0.02343   0.01417  -0.0633   0.8430   0.5157
  -3.500  -0.1337   0.02338   0.01403  -0.0624   0.8358   0.5544
  -3.250  -0.1105   0.02337   0.01396  -0.0612   0.8279   0.5878
  -3.000  -0.0853   0.02333   0.01383  -0.0602   0.8211   0.6197
  -2.750  -0.0622   0.02334   0.01375  -0.0589   0.8133   0.6486
  -2.500  -0.0356   0.02329   0.01362  -0.0582   0.8072   0.6772
  -2.250  -0.0137   0.02334   0.01361  -0.0569   0.7994   0.7040
  -2.000   0.0156   0.02325   0.01343  -0.0565   0.7944   0.7321
  -1.750   0.0358   0.02338   0.01353  -0.0549   0.7861   0.7582
  -1.500   0.0657   0.02335   0.01343  -0.0547   0.7809   0.7862
  -1.250   0.0912   0.02348   0.01353  -0.0541   0.7737   0.8144
  -1.000   0.1255   0.02352   0.01349  -0.0549   0.7680   0.8435
  -0.750   0.1666   0.02356   0.01342  -0.0571   0.7633   0.8724
  -0.500   0.2069   0.02376   0.01353  -0.0598   0.7563   0.9013
  -0.250   0.2570   0.02376   0.01340  -0.0641   0.7517   0.9285
   0.000   0.3049   0.02392   0.01344  -0.0687   0.7456   0.9562
   0.250   0.3561   0.02399   0.01340  -0.0739   0.7397   0.9824
   0.500   0.4009   0.02393   0.01321  -0.0778   0.7353   1.0000
   0.750   0.4047   0.02448   0.01369  -0.0749   0.7266   1.0000
   1.000   0.4247   0.02466   0.01375  -0.0740   0.7213   1.0000
   1.250   0.4340   0.02528   0.01429  -0.0717   0.7133   1.0000
   1.500   0.4550   0.02557   0.01451  -0.0708   0.7078   1.0000
   1.750   0.4694   0.02615   0.01502  -0.0691   0.7007   1.0000
   2.000   0.4886   0.02660   0.01542  -0.0680   0.6945   1.0000
   2.250   0.5119   0.02694   0.01570  -0.0673   0.6894   1.0000
   2.500   0.5246   0.02770   0.01647  -0.0655   0.6813   1.0000
   2.750   0.5517   0.02794   0.01668  -0.0653   0.6769   1.0000
   3.000   0.5621   0.02886   0.01761  -0.0634   0.6683   1.0000
   3.250   0.5877   0.02919   0.01793  -0.0630   0.6633   1.0000
   3.500   0.6007   0.03007   0.01886  -0.0614   0.6554   1.0000
   3.750   0.6240   0.03051   0.01933  -0.0608   0.6495   1.0000
   4.000   0.6407   0.03128   0.02013  -0.0595   0.6424   1.0000
   4.250   0.6606   0.03189   0.02079  -0.0586   0.6355   1.0000
   4.500   0.6815   0.03248   0.02146  -0.0578   0.6291   1.0000
   4.750   0.6978   0.03326   0.02231  -0.0565   0.6210   1.0000
   5.000   0.7185   0.03384   0.02297  -0.0556   0.6142   1.0000
   5.250   0.7358   0.03456   0.02377  -0.0544   0.6060   1.0000
   5.500   0.7507   0.03541   0.02471  -0.0529   0.5973   1.0000
   5.750   0.7761   0.03567   0.02511  -0.0523   0.5904   1.0000
   6.000   0.7857   0.03674   0.02628  -0.0504   0.5800   1.0000
   6.250   0.8205   0.03641   0.02609  -0.0504   0.5742   1.0000
   6.500   0.8269   0.03758   0.02737  -0.0481   0.5625   1.0000
   6.750   0.8404   0.03833   0.02824  -0.0464   0.5520   1.0000
   7.000   0.8772   0.03765   0.02777  -0.0463   0.5451   1.0000
   7.250   0.8851   0.03858   0.02883  -0.0440   0.5326   1.0000
   7.500   0.8956   0.03926   0.02965  -0.0418   0.5204   1.0000
   7.750   0.9109   0.03957   0.03011  -0.0399   0.5085   1.0000
   8.000   0.9341   0.03929   0.03005  -0.0384   0.4969   1.0000
   8.250   0.9594   0.03874   0.02968  -0.0369   0.4844   1.0000
   8.500   0.9736   0.03882   0.02993  -0.0346   0.4697   1.0000
   8.750   0.9825   0.03929   0.03055  -0.0322   0.4534   1.0000
   9.000   0.9938   0.03957   0.03099  -0.0300   0.4358   1.0000
   9.250   1.0130   0.03913   0.03070  -0.0279   0.4167   1.0000
   9.500   1.0188   0.03995   0.03167  -0.0257   0.3948   1.0000
   9.750   1.0331   0.04000   0.03181  -0.0237   0.3700   1.0000
  10.000   1.0426   0.04060   0.03242  -0.0216   0.3417   1.0000
  10.250   1.0492   0.04157   0.03335  -0.0197   0.3109   1.0000
  10.500   1.0533   0.04291   0.03454  -0.0178   0.2793   1.0000
  10.750   1.0540   0.04475   0.03621  -0.0161   0.2499   1.0000
  11.000   1.0523   0.04701   0.03830  -0.0146   0.2238   1.0000
  11.250   1.0496   0.04951   0.04063  -0.0134   0.2013   1.0000
  11.500   1.0469   0.05224   0.04330  -0.0125   0.1804   1.0000
  11.750   1.0441   0.05505   0.04605  -0.0118   0.1623   1.0000
  12.000   1.0419   0.05790   0.04880  -0.0111   0.1466   1.0000
  12.250   1.0401   0.06081   0.05163  -0.0107   0.1323   1.0000
  12.500   1.0390   0.06377   0.05456  -0.0103   0.1190   1.0000
  12.750   1.0378   0.06684   0.05765  -0.0101   0.1067   1.0000
  13.000   1.0371   0.06999   0.06085  -0.0100   0.0956   1.0000
  13.250   1.0356   0.07334   0.06425  -0.0101   0.0854   1.0000
  13.500   1.0348   0.07663   0.06754  -0.0103   0.0772   1.0000
  13.750   1.0332   0.08012   0.07107  -0.0107   0.0696   1.0000
  14.000   1.0334   0.08362   0.07472  -0.0111   0.0631   1.0000
  14.250   1.0326   0.08715   0.07827  -0.0116   0.0578   1.0000
  14.500   1.0325   0.09091   0.08220  -0.0122   0.0531   1.0000
  14.750   1.0321   0.09481   0.08632  -0.0129   0.0496   1.0000
  15.000   1.0324   0.09838   0.08995  -0.0138   0.0466   1.0000
  15.250   1.0305   0.10266   0.09438  -0.0149   0.0443   1.0000
  15.500   1.0226   0.10835   0.10041  -0.0170   0.0425   1.0000
  15.750   1.0140   0.11429   0.10661  -0.0195   0.0413   1.0000
  16.000   1.0030   0.12094   0.11350  -0.0226   0.0406   1.0000
  16.250   0.9881   0.12878   0.12157  -0.0268   0.0403   1.0000
  16.500   0.9674   0.13858   0.13159  -0.0323   0.0404   1.0000
  16.750   0.9407   0.15118   0.14429  -0.0397   0.0413   1.0000
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