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E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E174 (Dicke 8.92%) (e174-il)
Reynolds number: 500,000
Max Cl/Cd: 117.35 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e174-il-500000.txt
Download as CSV file: xf-e174-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E174  (Dicke 8.92%)                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3350   0.08401   0.08190  -0.0346   1.0000   0.0168
  -7.750  -0.3355   0.08084   0.07878  -0.0360   1.0000   0.0169
  -7.500  -0.3395   0.07813   0.07614  -0.0362   1.0000   0.0169
  -7.250  -0.3300   0.07356   0.07161  -0.0418   0.9915   0.0170
  -7.000  -0.3036   0.06475   0.06277  -0.0555   0.9743   0.0172
  -6.750  -0.2782   0.05988   0.05785  -0.0627   0.9553   0.0179
  -6.500  -0.2514   0.05563   0.05350  -0.0692   0.9271   0.0185
  -6.250  -0.2346   0.05156   0.04925  -0.0732   0.8942   0.0191
  -6.000  -0.2192   0.04729   0.04478  -0.0764   0.8680   0.0198
  -5.750  -0.2012   0.04250   0.03974  -0.0795   0.8468   0.0211
  -5.500  -0.1742   0.03741   0.03411  -0.0822   0.8297   0.0231
  -5.250  -0.1622   0.03065   0.02700  -0.0843   0.8151   0.0244
  -5.000  -0.1404   0.02895   0.02515  -0.0846   0.8015   0.0254
  -4.750  -0.1169   0.02698   0.02295  -0.0849   0.7893   0.0273
  -4.500  -0.0866   0.02712   0.02260  -0.0842   0.7780   0.0313
  -4.250  -0.0659   0.01686   0.01132  -0.0842   0.7698   0.0190
  -4.000  -0.0389   0.01505   0.00913  -0.0839   0.7600   0.0188
  -3.750  -0.0112   0.01369   0.00741  -0.0833   0.7512   0.0176
  -3.500   0.0163   0.01304   0.00659  -0.0830   0.7422   0.0172
  -3.250   0.0435   0.01215   0.00556  -0.0828   0.7340   0.0170
  -3.000   0.0703   0.01116   0.00443  -0.0824   0.7263   0.0172
  -2.750   0.0974   0.01029   0.00346  -0.0823   0.7185   0.0181
  -2.500   0.1249   0.00989   0.00297  -0.0821   0.7114   0.0201
  -2.250   0.1529   0.00960   0.00261  -0.0820   0.7042   0.0225
  -2.000   0.1808   0.00927   0.00223  -0.0819   0.6975   0.0335
  -1.750   0.2083   0.00872   0.00200  -0.0820   0.6908   0.1223
  -1.500   0.2356   0.00840   0.00189  -0.0821   0.6843   0.2029
  -1.250   0.2626   0.00795   0.00185  -0.0822   0.6783   0.3412
  -1.000   0.2888   0.00741   0.00185  -0.0822   0.6719   0.5201
  -0.750   0.3132   0.00693   0.00187  -0.0815   0.6664   0.7004
  -0.500   0.3323   0.00643   0.00191  -0.0791   0.6604   0.8839
  -0.250   0.3739   0.00633   0.00179  -0.0817   0.6545   1.0000
   0.000   0.4017   0.00640   0.00177  -0.0817   0.6487   1.0000
   0.250   0.4294   0.00646   0.00175  -0.0816   0.6429   1.0000
   0.500   0.4571   0.00657   0.00175  -0.0816   0.6376   1.0000
   0.750   0.4850   0.00662   0.00176  -0.0816   0.6316   1.0000
   1.000   0.5128   0.00670   0.00178  -0.0815   0.6261   1.0000
   1.250   0.5406   0.00679   0.00181  -0.0815   0.6206   1.0000
   1.500   0.5684   0.00686   0.00185  -0.0815   0.6146   1.0000
   2.000   0.6239   0.00703   0.00196  -0.0814   0.6031   1.0000
   2.250   0.6516   0.00713   0.00200  -0.0813   0.5970   1.0000
   2.500   0.6792   0.00721   0.00207  -0.0813   0.5902   1.0000
   2.750   0.7068   0.00729   0.00213  -0.0812   0.5830   1.0000
   3.000   0.7343   0.00737   0.00222  -0.0812   0.5755   1.0000
   3.250   0.7617   0.00746   0.00229  -0.0811   0.5680   1.0000
   3.500   0.7892   0.00754   0.00238  -0.0810   0.5601   1.0000
   3.750   0.8165   0.00766   0.00248  -0.0809   0.5523   1.0000
   4.000   0.8439   0.00773   0.00259  -0.0808   0.5433   1.0000
   4.250   0.8711   0.00784   0.00270  -0.0807   0.5344   1.0000
   4.500   0.8981   0.00795   0.00281  -0.0806   0.5247   1.0000
   4.750   0.9253   0.00804   0.00296  -0.0805   0.5141   1.0000
   5.000   0.9518   0.00817   0.00308  -0.0803   0.4989   1.0000
   5.250   0.9775   0.00833   0.00319  -0.0799   0.4724   1.0000
   5.500   1.0030   0.00857   0.00335  -0.0795   0.4455   1.0000
   5.750   1.0283   0.00885   0.00358  -0.0792   0.4175   1.0000
   6.000   1.0517   0.00932   0.00387  -0.0786   0.3711   1.0000
   6.500   1.0904   0.01122   0.00503  -0.0766   0.2232   1.0000
   6.750   1.1079   0.01238   0.00578  -0.0754   0.1507   1.0000
   7.000   1.1253   0.01350   0.00655  -0.0742   0.0917   1.0000
   7.250   1.1395   0.01492   0.00757  -0.0725   0.0311   1.0000
   7.500   1.1586   0.01580   0.00839  -0.0713   0.0189   1.0000
   7.750   1.1793   0.01647   0.00912  -0.0703   0.0166   1.0000
   8.000   1.1983   0.01727   0.01001  -0.0691   0.0152   1.0000
   8.250   1.2148   0.01825   0.01109  -0.0675   0.0142   1.0000
   8.500   1.2328   0.01901   0.01194  -0.0662   0.0135   1.0000
   8.750   1.2484   0.01993   0.01294  -0.0645   0.0132   1.0000
   9.000   1.2620   0.02093   0.01404  -0.0627   0.0128   1.0000
   9.250   1.2733   0.02197   0.01518  -0.0605   0.0125   1.0000
   9.500   1.2804   0.02308   0.01639  -0.0576   0.0123   1.0000
   9.750   1.2866   0.02429   0.01769  -0.0549   0.0120   1.0000
  10.000   1.2924   0.02562   0.01911  -0.0524   0.0118   1.0000
  10.250   1.2979   0.02712   0.02070  -0.0501   0.0116   1.0000
  10.500   1.3038   0.02874   0.02242  -0.0481   0.0114   1.0000
  10.750   1.3100   0.03049   0.02426  -0.0463   0.0112   1.0000
  11.000   1.3168   0.03238   0.02624  -0.0446   0.0111   1.0000
  11.250   1.3247   0.03434   0.02831  -0.0431   0.0109   1.0000
  11.500   1.3336   0.03640   0.03049  -0.0418   0.0108   1.0000
  11.750   1.3428   0.03883   0.03306  -0.0405   0.0105   1.0000
  12.000   1.3523   0.04186   0.03627  -0.0392   0.0104   1.0000
  12.250   1.3586   0.04467   0.03927  -0.0380   0.0103   1.0000
  12.500   1.3617   0.04743   0.04222  -0.0369   0.0104   1.0000
  12.750   1.3628   0.05008   0.04506  -0.0360   0.0104   1.0000
  13.000   1.3611   0.05312   0.04829  -0.0352   0.0105   1.0000
  13.250   1.3562   0.05670   0.05209  -0.0347   0.0105   1.0000
  13.500   1.3496   0.06032   0.05591  -0.0345   0.0106   1.0000
  13.750   1.3037   0.07081   0.06718  -0.0352   0.0124   1.0000
  14.000   1.2802   0.07773   0.07436  -0.0370   0.0128   1.0000
  14.250   1.2575   0.08476   0.08160  -0.0395   0.0132   1.0000
  14.500   1.2347   0.09218   0.08921  -0.0427   0.0135   1.0000
  14.750   1.2113   0.10030   0.09750  -0.0468   0.0137   1.0000
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