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E186 (10.27%) (e186-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E186 (10.27%) (e186-il)
Reynolds number: 500,000
Max Cl/Cd: 79.73 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e186-il-500000.txt
Download as CSV file: xf-e186-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E186  (10.27%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6829   0.08369   0.08188   0.0173   1.0000   0.0210
  -9.000  -0.7047   0.07479   0.07300   0.0086   1.0000   0.0203
  -8.750  -0.7281   0.06827   0.06641   0.0061   1.0000   0.0202
  -8.500  -0.7431   0.06288   0.06090   0.0058   1.0000   0.0204
  -8.250  -0.7509   0.05758   0.05544   0.0058   1.0000   0.0209
  -8.000  -0.7540   0.05240   0.05005   0.0064   1.0000   0.0216
  -7.750  -0.7420   0.05022   0.04741   0.0081   1.0000   0.0242
  -7.500  -0.7647   0.04176   0.03829   0.0120   0.8933   0.0250
  -7.250  -0.7598   0.03837   0.03468   0.0144   0.8536   0.0260
  -7.000  -0.7447   0.03676   0.03292   0.0157   0.8241   0.0269
  -6.500  -0.7195   0.02842   0.02347   0.0214   0.7845   0.0226
  -6.250  -0.7069   0.02256   0.01677   0.0247   0.7698   0.0195
  -6.000  -0.6844   0.01997   0.01372   0.0263   0.7549   0.0187
  -5.750  -0.6605   0.01842   0.01192   0.0273   0.7412   0.0188
  -5.500  -0.6361   0.01716   0.01047   0.0281   0.7289   0.0191
  -5.250  -0.6115   0.01611   0.00927   0.0289   0.7173   0.0194
  -5.000  -0.5867   0.01525   0.00829   0.0296   0.7066   0.0200
  -4.750  -0.5618   0.01459   0.00753   0.0302   0.6969   0.0209
  -4.500  -0.5371   0.01390   0.00671   0.0310   0.6880   0.0216
  -4.250  -0.5124   0.01322   0.00593   0.0318   0.6792   0.0222
  -4.000  -0.4875   0.01268   0.00527   0.0325   0.6716   0.0230
  -3.750  -0.4619   0.01222   0.00473   0.0331   0.6635   0.0239
  -3.500  -0.4365   0.01179   0.00417   0.0338   0.6567   0.0249
  -3.250  -0.4107   0.01133   0.00364   0.0343   0.6492   0.0277
  -3.000  -0.3844   0.01106   0.00330   0.0348   0.6430   0.0328
  -2.750  -0.3605   0.01033   0.00290   0.0355   0.6363   0.0984
  -2.500  -0.3368   0.00974   0.00262   0.0362   0.6303   0.1873
  -2.250  -0.3128   0.00920   0.00243   0.0368   0.6241   0.2779
  -2.000  -0.2896   0.00865   0.00225   0.0375   0.6182   0.3834
  -1.750  -0.2686   0.00802   0.00209   0.0388   0.6129   0.5129
  -1.500  -0.2520   0.00724   0.00196   0.0412   0.6072   0.6731
  -1.250  -0.2316   0.00665   0.00189   0.0432   0.6020   0.8116
  -1.000  -0.1364   0.00690   0.00239   0.0295   0.5946   0.9338
  -0.750  -0.1006   0.00716   0.00255   0.0282   0.5889   0.9489
  -0.500  -0.0655   0.00739   0.00269   0.0270   0.5835   0.9599
  -0.250  -0.0254   0.00760   0.00283   0.0246   0.5774   0.9684
   0.000   0.0159   0.00779   0.00291   0.0219   0.5720   0.9744
   0.250   0.0564   0.00790   0.00298   0.0193   0.5661   0.9805
   0.500   0.0969   0.00797   0.00299   0.0166   0.5604   0.9853
   0.750   0.1403   0.00799   0.00294   0.0133   0.5549   0.9896
   1.000   0.1803   0.00800   0.00293   0.0107   0.5488   0.9943
   1.250   0.2222   0.00791   0.00277   0.0076   0.5434   0.9978
   1.500   0.2574   0.00783   0.00270   0.0060   0.5376   1.0000
   1.750   0.2824   0.00781   0.00266   0.0064   0.5319   1.0000
   2.000   0.3076   0.00783   0.00264   0.0069   0.5263   1.0000
   2.250   0.3330   0.00780   0.00263   0.0073   0.5195   1.0000
   2.500   0.3583   0.00783   0.00261   0.0077   0.5131   1.0000
   2.750   0.3840   0.00780   0.00262   0.0081   0.5058   1.0000
   3.000   0.4096   0.00784   0.00262   0.0085   0.4991   1.0000
   3.250   0.4355   0.00783   0.00265   0.0089   0.4908   1.0000
   3.500   0.4614   0.00786   0.00268   0.0092   0.4833   1.0000
   3.750   0.4874   0.00787   0.00271   0.0096   0.4746   1.0000
   4.000   0.5135   0.00791   0.00278   0.0099   0.4657   1.0000
   4.250   0.5395   0.00796   0.00282   0.0102   0.4563   1.0000
   4.500   0.5657   0.00800   0.00290   0.0105   0.4455   1.0000
   4.750   0.5919   0.00805   0.00298   0.0108   0.4332   1.0000
   5.000   0.6181   0.00813   0.00307   0.0110   0.4170   1.0000
   5.250   0.6444   0.00824   0.00317   0.0112   0.3986   1.0000
   5.500   0.6705   0.00841   0.00329   0.0114   0.3689   1.0000
   5.750   0.6965   0.00876   0.00348   0.0115   0.3200   1.0000
   6.000   0.7220   0.00940   0.00384   0.0113   0.2511   1.0000
   6.250   0.7465   0.01038   0.00442   0.0109   0.1698   1.0000
   6.500   0.7707   0.01117   0.00496   0.0109   0.1173   1.0000
   6.750   0.7946   0.01195   0.00553   0.0109   0.0753   1.0000
   7.000   0.8164   0.01322   0.00646   0.0110   0.0236   1.0000
   7.250   0.8393   0.01404   0.00731   0.0115   0.0158   1.0000
   7.500   0.8615   0.01488   0.00822   0.0121   0.0135   1.0000
   7.750   0.8829   0.01572   0.00917   0.0127   0.0124   1.0000
   8.000   0.9045   0.01640   0.00992   0.0133   0.0115   1.0000
   8.250   0.9245   0.01725   0.01085   0.0141   0.0109   1.0000
   8.500   0.9432   0.01820   0.01188   0.0151   0.0104   1.0000
   8.750   0.9602   0.01924   0.01300   0.0161   0.0099   1.0000
   9.000   0.9746   0.02051   0.01437   0.0175   0.0096   1.0000
   9.250   0.9854   0.02207   0.01602   0.0192   0.0093   1.0000
   9.500   0.9916   0.02412   0.01819   0.0215   0.0090   1.0000
   9.750   1.0001   0.02598   0.02018   0.0237   0.0088   1.0000
  10.000   1.0103   0.02755   0.02187   0.0256   0.0088   1.0000
  10.250   1.0194   0.02925   0.02370   0.0275   0.0088   1.0000
  10.500   1.0265   0.03137   0.02597   0.0295   0.0088   1.0000
  10.750   1.0285   0.03355   0.02833   0.0320   0.0088   1.0000
  11.000   1.0287   0.03607   0.03101   0.0345   0.0089   1.0000
  11.250   1.0283   0.03753   0.03257   0.0366   0.0090   1.0000
  11.500   1.0275   0.03942   0.03460   0.0380   0.0091   1.0000
  11.750   1.0253   0.04174   0.03711   0.0390   0.0091   1.0000
  12.000   1.0240   0.04391   0.03944   0.0394   0.0093   1.0000
  12.250   0.9826   0.05241   0.04864   0.0393   0.0111   1.0000
  12.500   0.9639   0.05756   0.05400   0.0381   0.0116   1.0000
  12.750   0.9414   0.06351   0.06015   0.0360   0.0120   1.0000
  13.000   0.9171   0.07008   0.06688   0.0332   0.0123   1.0000
  14.250   0.7397   0.09111   0.08851   0.0259   0.0113   1.0000
  14.500   0.7146   0.09975   0.09726   0.0217   0.0113   1.0000
  14.750   0.5563   0.13931   0.13705   0.0047   0.0235   1.0000
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