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E195 (11.82%) (e195-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E195 (11.82%) (e195-il)
Reynolds number: 1,000,000
Max Cl/Cd: 137.13 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e195-il-1000000.txt
Download as CSV file: xf-e195-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E195  (11.82%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4233   0.08176   0.08020  -0.0445   1.0000   0.0146
  -9.750  -0.4263   0.07767   0.07613  -0.0464   1.0000   0.0148
  -9.500  -0.4345   0.07260   0.07110  -0.0489   1.0000   0.0150
  -9.250  -0.5362   0.04236   0.04047  -0.0750   0.9883   0.0146
  -9.000  -0.5201   0.03817   0.03607  -0.0799   0.9785   0.0148
  -8.750  -0.5284   0.02738   0.02440  -0.0832   0.9532   0.0122
  -8.500  -0.5176   0.02349   0.01999  -0.0825   0.9209   0.0120
  -8.250  -0.5071   0.02053   0.01651  -0.0805   0.8879   0.0119
  -8.000  -0.4895   0.01901   0.01467  -0.0791   0.8627   0.0120
  -7.750  -0.4697   0.01780   0.01319  -0.0780   0.8409   0.0122
  -7.500  -0.4486   0.01668   0.01183  -0.0770   0.8221   0.0123
  -7.250  -0.4261   0.01576   0.01069  -0.0762   0.8051   0.0125
  -7.000  -0.4032   0.01484   0.00959  -0.0754   0.7899   0.0126
  -6.750  -0.3792   0.01415   0.00875  -0.0748   0.7763   0.0128
  -6.500  -0.3552   0.01344   0.00790  -0.0742   0.7636   0.0130
  -6.250  -0.3307   0.01282   0.00715  -0.0737   0.7518   0.0131
  -6.000  -0.3056   0.01229   0.00651  -0.0732   0.7412   0.0133
  -5.750  -0.2793   0.01203   0.00616  -0.0729   0.7315   0.0136
  -5.500  -0.2558   0.01119   0.00519  -0.0722   0.7221   0.0140
  -5.250  -0.2313   0.01053   0.00442  -0.0717   0.7136   0.0145
  -4.750  -0.1790   0.00980   0.00354  -0.0711   0.6981   0.0158
  -4.250  -0.1252   0.00930   0.00292  -0.0707   0.6842   0.0172
  -4.000  -0.0981   0.00912   0.00266  -0.0705   0.6777   0.0178
  -3.750  -0.0709   0.00888   0.00236  -0.0704   0.6717   0.0194
  -3.500  -0.0436   0.00867   0.00213  -0.0702   0.6656   0.0232
  -3.250  -0.0176   0.00828   0.00189  -0.0700   0.6602   0.0623
  -3.000   0.0093   0.00797   0.00174  -0.0699   0.6548   0.1043
  -2.750   0.0362   0.00773   0.00161  -0.0698   0.6493   0.1452
  -2.500   0.0630   0.00750   0.00151  -0.0697   0.6443   0.1912
  -2.250   0.0901   0.00725   0.00142  -0.0697   0.6394   0.2439
  -2.000   0.1167   0.00700   0.00135  -0.0696   0.6344   0.3079
  -1.750   0.1434   0.00677   0.00130  -0.0695   0.6297   0.3745
  -1.500   0.1707   0.00659   0.00127  -0.0695   0.6250   0.4290
  -1.250   0.1980   0.00646   0.00125  -0.0694   0.6203   0.4750
  -0.750   0.2526   0.00623   0.00123  -0.0692   0.6113   0.5633
  -0.500   0.2801   0.00616   0.00123  -0.0691   0.6067   0.5965
  -0.250   0.3072   0.00610   0.00124  -0.0690   0.6022   0.6334
   0.000   0.3345   0.00599   0.00125  -0.0689   0.5980   0.6749
   0.250   0.3613   0.00588   0.00127  -0.0686   0.5935   0.7223
   0.500   0.3873   0.00578   0.00130  -0.0682   0.5890   0.7738
   0.750   0.4126   0.00566   0.00135  -0.0675   0.5847   0.8307
   1.000   0.4371   0.00553   0.00140  -0.0665   0.5804   0.8943
   1.250   0.4670   0.00552   0.00147  -0.0667   0.5757   0.9486
   1.500   0.5035   0.00559   0.00152  -0.0685   0.5709   0.9730
   1.750   0.5419   0.00562   0.00155  -0.0708   0.5658   0.9851
   2.000   0.5830   0.00569   0.00157  -0.0738   0.5600   0.9915
   2.250   0.6239   0.00574   0.00160  -0.0767   0.5539   0.9970
   2.500   0.6607   0.00578   0.00162  -0.0787   0.5471   1.0000
   2.750   0.6853   0.00585   0.00167  -0.0781   0.5409   1.0000
   3.000   0.7104   0.00590   0.00172  -0.0775   0.5343   1.0000
   3.250   0.7349   0.00600   0.00178  -0.0769   0.5277   1.0000
   3.500   0.7603   0.00605   0.00183  -0.0764   0.5204   1.0000
   3.750   0.7850   0.00615   0.00190  -0.0758   0.5131   1.0000
   4.000   0.8105   0.00622   0.00198  -0.0753   0.5051   1.0000
   4.250   0.8355   0.00632   0.00207  -0.0748   0.4970   1.0000
   4.500   0.8605   0.00642   0.00216  -0.0742   0.4870   1.0000
   4.750   0.8858   0.00652   0.00227  -0.0737   0.4778   1.0000
   5.000   0.9107   0.00666   0.00238  -0.0732   0.4675   1.0000
   5.250   0.9352   0.00682   0.00250  -0.0726   0.4497   1.0000
   5.500   0.9586   0.00707   0.00265  -0.0718   0.4253   1.0000
   5.750   0.9816   0.00736   0.00284  -0.0710   0.3973   1.0000
   6.000   1.0027   0.00781   0.00310  -0.0699   0.3548   1.0000
   6.250   1.0228   0.00835   0.00343  -0.0687   0.3086   1.0000
   6.500   1.0414   0.00901   0.00384  -0.0673   0.2588   1.0000
   6.750   1.0596   0.00968   0.00430  -0.0659   0.2137   1.0000
   7.000   1.0773   0.01038   0.00477  -0.0643   0.1706   1.0000
   7.250   1.0955   0.01104   0.00523  -0.0629   0.1342   1.0000
   7.500   1.1123   0.01175   0.00575  -0.0613   0.0989   1.0000
   7.750   1.1290   0.01245   0.00628  -0.0596   0.0704   1.0000
   8.000   1.1445   0.01318   0.00686  -0.0578   0.0454   1.0000
   8.250   1.1556   0.01415   0.00763  -0.0553   0.0178   1.0000
   8.500   1.1711   0.01480   0.00824  -0.0534   0.0111   1.0000
   8.750   1.1876   0.01534   0.00881  -0.0516   0.0096   1.0000
   9.000   1.2017   0.01588   0.00939  -0.0494   0.0088   1.0000
   9.250   1.2129   0.01649   0.01006  -0.0467   0.0083   1.0000
   9.500   1.2259   0.01703   0.01066  -0.0445   0.0080   1.0000
   9.750   1.2380   0.01765   0.01132  -0.0422   0.0079   1.0000
  10.000   1.2488   0.01836   0.01210  -0.0399   0.0074   1.0000
  10.250   1.2587   0.01916   0.01296  -0.0376   0.0071   1.0000
  10.500   1.2683   0.02003   0.01388  -0.0354   0.0070   1.0000
  10.750   1.2761   0.02105   0.01497  -0.0332   0.0067   1.0000
  11.000   1.2805   0.02236   0.01635  -0.0309   0.0064   1.0000
  11.250   1.2862   0.02369   0.01776  -0.0290   0.0063   1.0000
  11.500   1.2825   0.02580   0.01998  -0.0265   0.0061   1.0000
  11.750   1.2851   0.02758   0.02185  -0.0249   0.0059   1.0000
  12.000   1.2893   0.02932   0.02367  -0.0235   0.0059   1.0000
  12.250   1.2953   0.03098   0.02541  -0.0224   0.0059   1.0000
  12.500   1.2994   0.03287   0.02738  -0.0214   0.0058   1.0000
  12.750   1.3037   0.03480   0.02939  -0.0205   0.0057   1.0000
  13.000   1.3070   0.03688   0.03155  -0.0196   0.0057   1.0000
  13.250   1.3091   0.03912   0.03388  -0.0189   0.0057   1.0000
  13.500   1.3146   0.04109   0.03593  -0.0184   0.0056   1.0000
  13.750   1.3109   0.04403   0.03898  -0.0176   0.0056   1.0000
  14.000   1.3165   0.04608   0.04110  -0.0174   0.0055   1.0000
  14.250   1.3184   0.04860   0.04371  -0.0172   0.0054   1.0000
  14.500   1.3157   0.05168   0.04689  -0.0168   0.0055   1.0000
  14.750   1.3163   0.05451   0.04982  -0.0168   0.0054   1.0000
  15.000   1.3186   0.05723   0.05262  -0.0170   0.0052   1.0000
  15.250   1.3173   0.06042   0.05591  -0.0172   0.0053   1.0000
  15.500   1.3161   0.06372   0.05931  -0.0175   0.0052   1.0000
  15.750   1.3160   0.06699   0.06268  -0.0182   0.0051   1.0000
  16.000   1.3128   0.07073   0.06654  -0.0188   0.0051   1.0000
  16.250   1.3123   0.07426   0.07015  -0.0198   0.0050   1.0000
  16.500   1.3068   0.07853   0.07455  -0.0208   0.0051   1.0000
  16.750   1.3029   0.08276   0.07891  -0.0221   0.0050   1.0000
  17.000   1.3000   0.08696   0.08320  -0.0238   0.0048   1.0000
  17.250   1.2942   0.09170   0.08805  -0.0255   0.0048   1.0000
  17.500   1.2872   0.09674   0.09322  -0.0274   0.0048   1.0000
  17.750   1.2788   0.10219   0.09881  -0.0297   0.0048   1.0000
  18.000   1.2714   0.10760   0.10433  -0.0322   0.0048   1.0000
  18.250   1.2619   0.11354   0.11041  -0.0351   0.0048   1.0000
  18.500   1.2532   0.11955   0.11653  -0.0382   0.0047   1.0000
  18.750   1.2436   0.12584   0.12294  -0.0416   0.0047   1.0000
  19.000   1.2258   0.13396   0.13126  -0.0460   0.0048   1.0000
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