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E195 (11.82%) (e195-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E195 (11.82%) (e195-il)
Reynolds number: 500,000
Max Cl/Cd: 112.4 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e195-il-500000.txt
Download as CSV file: xf-e195-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3851   0.08535   0.08317  -0.0436   1.0000   0.0267
  -9.250  -0.3880   0.08139   0.07925  -0.0452   1.0000   0.0275
  -9.000  -0.3961   0.07644   0.07435  -0.0477   1.0000   0.0286
  -8.000  -0.4423   0.04023   0.03720  -0.0812   0.9630   0.0316
  -7.750  -0.4180   0.03709   0.03403  -0.0835   0.9486   0.0325
  -7.500  -0.4290   0.02225   0.01745  -0.0813   0.9191   0.0190
  -7.250  -0.4065   0.02051   0.01533  -0.0806   0.8976   0.0187
  -7.000  -0.3845   0.01925   0.01378  -0.0796   0.8756   0.0185
  -6.750  -0.3631   0.01773   0.01199  -0.0785   0.8564   0.0186
  -6.500  -0.3412   0.01641   0.01047  -0.0776   0.8390   0.0190
  -6.250  -0.3181   0.01551   0.00941  -0.0768   0.8231   0.0196
  -6.000  -0.2944   0.01469   0.00843  -0.0761   0.8089   0.0199
  -5.750  -0.2705   0.01392   0.00752  -0.0753   0.7958   0.0202
  -5.500  -0.2462   0.01326   0.00674  -0.0747   0.7838   0.0207
  -5.250  -0.2215   0.01269   0.00606  -0.0741   0.7729   0.0213
  -5.000  -0.1966   0.01221   0.00545  -0.0735   0.7632   0.0222
  -4.750  -0.1711   0.01177   0.00491  -0.0730   0.7536   0.0229
  -4.500  -0.1452   0.01142   0.00446  -0.0726   0.7449   0.0236
  -4.250  -0.1200   0.01091   0.00385  -0.0721   0.7367   0.0259
  -4.000  -0.0934   0.01064   0.00353  -0.0719   0.7289   0.0292
  -3.750  -0.0672   0.01029   0.00314  -0.0715   0.7217   0.0386
  -3.500  -0.0421   0.00969   0.00281  -0.0711   0.7145   0.0999
  -3.250  -0.0160   0.00939   0.00261  -0.0709   0.7079   0.1462
  -3.000   0.0102   0.00908   0.00247  -0.0708   0.7016   0.1983
  -2.750   0.0361   0.00873   0.00234  -0.0706   0.6952   0.2689
  -2.500   0.0619   0.00843   0.00224  -0.0704   0.6896   0.3434
  -2.250   0.0883   0.00818   0.00218  -0.0702   0.6835   0.4088
  -2.000   0.1146   0.00800   0.00214  -0.0700   0.6780   0.4729
  -1.750   0.1412   0.00787   0.00212  -0.0697   0.6726   0.5205
  -1.500   0.1679   0.00773   0.00209  -0.0695   0.6670   0.5652
  -1.250   0.1942   0.00762   0.00207  -0.0691   0.6621   0.6132
  -1.000   0.2207   0.00751   0.00207  -0.0688   0.6569   0.6555
  -0.750   0.2469   0.00739   0.00207  -0.0684   0.6516   0.7004
  -0.500   0.2725   0.00729   0.00208  -0.0678   0.6470   0.7501
  -0.250   0.2974   0.00716   0.00212  -0.0670   0.6421   0.8066
   0.000   0.3220   0.00703   0.00216  -0.0659   0.6370   0.8682
   0.250   0.3532   0.00703   0.00221  -0.0662   0.6325   0.9253
   0.500   0.3934   0.00709   0.00226  -0.0687   0.6275   0.9595
   0.750   0.4352   0.00713   0.00227  -0.0716   0.6222   0.9782
   1.000   0.4793   0.00721   0.00226  -0.0752   0.6175   0.9890
   1.250   0.5246   0.00724   0.00228  -0.0790   0.6123   0.9979
   1.500   0.5553   0.00728   0.00229  -0.0798   0.6072   1.0000
   1.750   0.5797   0.00737   0.00232  -0.0791   0.6027   1.0000
   2.000   0.6041   0.00744   0.00238  -0.0785   0.5977   1.0000
   2.250   0.6288   0.00750   0.00243  -0.0779   0.5923   1.0000
   2.500   0.6537   0.00761   0.00248  -0.0773   0.5874   1.0000
   2.750   0.6785   0.00766   0.00256  -0.0767   0.5814   1.0000
   3.000   0.7034   0.00773   0.00262  -0.0761   0.5754   1.0000
   3.250   0.7283   0.00782   0.00269  -0.0756   0.5692   1.0000
   3.500   0.7532   0.00788   0.00276  -0.0750   0.5622   1.0000
   3.750   0.7782   0.00799   0.00284  -0.0744   0.5559   1.0000
   4.000   0.8033   0.00804   0.00294  -0.0739   0.5485   1.0000
   4.250   0.8283   0.00815   0.00303  -0.0733   0.5413   1.0000
   4.500   0.8535   0.00822   0.00313  -0.0728   0.5330   1.0000
   4.750   0.8787   0.00832   0.00325  -0.0723   0.5251   1.0000
   5.000   0.9037   0.00842   0.00335  -0.0717   0.5159   1.0000
   5.250   0.9290   0.00851   0.00348  -0.0712   0.5061   1.0000
   5.500   0.9540   0.00864   0.00361  -0.0707   0.4963   1.0000
   5.750   0.9785   0.00878   0.00376  -0.0701   0.4841   1.0000
   6.000   1.0026   0.00892   0.00390  -0.0694   0.4657   1.0000
   6.250   1.0256   0.00914   0.00407  -0.0686   0.4429   1.0000
   6.500   1.0481   0.00942   0.00429  -0.0677   0.4158   1.0000
   6.750   1.0687   0.00983   0.00457  -0.0665   0.3801   1.0000
   7.000   1.0861   0.01046   0.00498  -0.0649   0.3288   1.0000
   7.250   1.1000   0.01137   0.00556  -0.0628   0.2683   1.0000
   7.500   1.1140   0.01227   0.00619  -0.0608   0.2165   1.0000
   7.750   1.1280   0.01314   0.00683  -0.0588   0.1729   1.0000
   8.000   1.1412   0.01403   0.00750  -0.0567   0.1333   1.0000
   8.250   1.1543   0.01487   0.00817  -0.0546   0.1026   1.0000
   8.500   1.1664   0.01571   0.00886  -0.0523   0.0759   1.0000
   8.750   1.1722   0.01678   0.00972  -0.0490   0.0449   1.0000
   9.000   1.1723   0.01796   0.01074  -0.0448   0.0224   1.0000
   9.250   1.1785   0.01892   0.01167  -0.0417   0.0165   1.0000
   9.500   1.1872   0.01981   0.01263  -0.0391   0.0147   1.0000
   9.750   1.1975   0.02065   0.01355  -0.0369   0.0139   1.0000
  10.000   1.2057   0.02167   0.01463  -0.0347   0.0129   1.0000
  10.250   1.2116   0.02289   0.01591  -0.0324   0.0121   1.0000
  10.500   1.2164   0.02428   0.01738  -0.0303   0.0118   1.0000
  10.750   1.2161   0.02613   0.01934  -0.0280   0.0113   1.0000
  11.000   1.2221   0.02765   0.02095  -0.0265   0.0111   1.0000
  11.250   1.2269   0.02932   0.02271  -0.0250   0.0110   1.0000
  11.500   1.2304   0.03118   0.02468  -0.0237   0.0108   1.0000
  11.750   1.2346   0.03307   0.02665  -0.0225   0.0105   1.0000
  12.000   1.2372   0.03515   0.02883  -0.0214   0.0104   1.0000
  12.250   1.2401   0.03727   0.03104  -0.0204   0.0102   1.0000
  12.500   1.2423   0.03952   0.03338  -0.0195   0.0100   1.0000
  12.750   1.2459   0.04168   0.03563  -0.0188   0.0098   1.0000
  13.000   1.2493   0.04389   0.03792  -0.0182   0.0096   1.0000
  13.250   1.2526   0.04616   0.04027  -0.0176   0.0095   1.0000
  13.500   1.2565   0.04841   0.04257  -0.0173   0.0091   1.0000
  13.750   1.2575   0.05104   0.04532  -0.0166   0.0091   1.0000
  14.000   1.2606   0.05348   0.04783  -0.0164   0.0089   1.0000
  14.250   1.2624   0.05615   0.05059  -0.0160   0.0088   1.0000
  14.500   1.2654   0.05877   0.05331  -0.0157   0.0088   1.0000
  14.750   1.2672   0.06161   0.05626  -0.0154   0.0087   1.0000
  15.000   1.2680   0.06470   0.05947  -0.0150   0.0085   1.0000
  15.250   1.2695   0.06772   0.06263  -0.0152   0.0086   1.0000
  15.500   1.2678   0.07136   0.06643  -0.0153   0.0085   1.0000
  15.750   1.2641   0.07536   0.07060  -0.0157   0.0085   1.0000
  16.000   1.2614   0.07919   0.07457  -0.0167   0.0085   1.0000
  16.250   1.2504   0.08456   0.08016  -0.0179   0.0084   1.0000
  16.500   1.2467   0.08873   0.08446  -0.0195   0.0085   1.0000
  16.750   1.2369   0.09412   0.09003  -0.0215   0.0085   1.0000
  17.000   1.2220   0.10057   0.09668  -0.0242   0.0084   1.0000
  17.250   1.2133   0.10610   0.10235  -0.0269   0.0085   1.0000
  17.500   1.2043   0.11189   0.10830  -0.0299   0.0085   1.0000
  17.750   1.1940   0.11816   0.11473  -0.0334   0.0086   1.0000
  18.000   1.1821   0.12496   0.12169  -0.0373   0.0086   1.0000
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