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E178 (8.69%) (e178-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E178 (8.69%) (e178-il)
Reynolds number: 500,000
Max Cl/Cd: 105.01 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e178-il-500000.txt
Download as CSV file: xf-e178-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E178  (8.69%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4638   0.08851   0.08646  -0.0137   1.0000   0.0155
  -8.500  -0.4608   0.08513   0.08311  -0.0151   1.0000   0.0158
  -8.250  -0.4584   0.08177   0.07978  -0.0167   1.0000   0.0161
  -8.000  -0.4578   0.07819   0.07624  -0.0187   1.0000   0.0162
  -7.750  -0.4602   0.07445   0.07254  -0.0211   1.0000   0.0164
  -7.500  -0.4569   0.07035   0.06846  -0.0251   1.0000   0.0167
  -7.250  -0.4508   0.06543   0.06355  -0.0303   1.0000   0.0169
  -7.000  -0.4419   0.06028   0.05837  -0.0352   1.0000   0.0172
  -6.500  -0.4046   0.04833   0.04600  -0.0466   0.9017   0.0187
  -6.250  -0.3937   0.04340   0.04077  -0.0477   0.8751   0.0195
  -6.000  -0.3700   0.04019   0.03714  -0.0477   0.8554   0.0225
  -5.000  -0.3053   0.01982   0.01469  -0.0463   0.8017   0.0193
  -4.750  -0.2803   0.01795   0.01244  -0.0456   0.7909   0.0202
  -4.500  -0.2547   0.01589   0.01000  -0.0449   0.7809   0.0204
  -4.250  -0.2285   0.01459   0.00844  -0.0444   0.7717   0.0211
  -4.000  -0.2019   0.01363   0.00728  -0.0439   0.7628   0.0218
  -3.750  -0.1747   0.01307   0.00659  -0.0436   0.7540   0.0230
  -3.500  -0.1497   0.01158   0.00489  -0.0430   0.7465   0.0242
  -3.250  -0.1232   0.01085   0.00406  -0.0426   0.7383   0.0258
  -3.000  -0.0963   0.01041   0.00353  -0.0423   0.7312   0.0273
  -2.750  -0.0689   0.01006   0.00312  -0.0421   0.7237   0.0293
  -2.500  -0.0415   0.00981   0.00275  -0.0419   0.7170   0.0321
  -2.250  -0.0139   0.00943   0.00233  -0.0417   0.7101   0.0401
  -2.000   0.0125   0.00886   0.00204  -0.0416   0.7040   0.1210
  -1.750   0.0394   0.00846   0.00190  -0.0415   0.6972   0.2034
  -1.500   0.0656   0.00805   0.00180  -0.0414   0.6916   0.3133
  -1.250   0.0910   0.00745   0.00174  -0.0413   0.6850   0.4755
  -1.000   0.1153   0.00694   0.00170  -0.0406   0.6793   0.6305
  -0.750   0.1359   0.00634   0.00172  -0.0388   0.6736   0.8125
  -0.500   0.1889   0.00608   0.00170  -0.0434   0.6676   0.9831
  -0.250   0.2341   0.00611   0.00161  -0.0472   0.6620   1.0000
   0.000   0.2603   0.00614   0.00158  -0.0469   0.6559   1.0000
   0.250   0.2864   0.00622   0.00156  -0.0465   0.6506   1.0000
   0.500   0.3129   0.00626   0.00156  -0.0462   0.6445   1.0000
   0.750   0.3393   0.00632   0.00155  -0.0458   0.6389   1.0000
   1.000   0.3658   0.00639   0.00157  -0.0455   0.6334   1.0000
   1.250   0.3925   0.00644   0.00160  -0.0452   0.6273   1.0000
   1.500   0.4190   0.00653   0.00162  -0.0449   0.6216   1.0000
   1.750   0.4458   0.00657   0.00165  -0.0447   0.6139   1.0000
   2.000   0.4725   0.00665   0.00167  -0.0444   0.6073   1.0000
   2.250   0.4995   0.00669   0.00172  -0.0442   0.5997   1.0000
   2.500   0.5263   0.00678   0.00177  -0.0439   0.5926   1.0000
   2.750   0.5534   0.00682   0.00182  -0.0437   0.5842   1.0000
   3.000   0.5804   0.00690   0.00189  -0.0435   0.5761   1.0000
   3.250   0.6073   0.00698   0.00194  -0.0433   0.5674   1.0000
   3.500   0.6345   0.00703   0.00204  -0.0431   0.5580   1.0000
   3.750   0.6615   0.00712   0.00213  -0.0430   0.5488   1.0000
   4.000   0.6884   0.00721   0.00221  -0.0428   0.5384   1.0000
   4.250   0.7154   0.00730   0.00231  -0.0426   0.5261   1.0000
   4.500   0.7423   0.00740   0.00244  -0.0424   0.5127   1.0000
   4.750   0.7690   0.00753   0.00257  -0.0422   0.4978   1.0000
   5.000   0.7958   0.00765   0.00272  -0.0420   0.4812   1.0000
   5.250   0.8222   0.00783   0.00288  -0.0418   0.4586   1.0000
   5.500   0.8480   0.00808   0.00309  -0.0415   0.4285   1.0000
   5.750   0.8722   0.00854   0.00335  -0.0410   0.3720   1.0000
   6.000   0.8926   0.00957   0.00388  -0.0403   0.2715   1.0000
   6.250   0.9131   0.01060   0.00450  -0.0397   0.1921   1.0000
   6.500   0.9344   0.01149   0.00509  -0.0391   0.1332   1.0000
   6.750   0.9559   0.01231   0.00568  -0.0386   0.0901   1.0000
   7.000   0.9772   0.01314   0.00633  -0.0379   0.0539   1.0000
   7.250   0.9944   0.01454   0.00746  -0.0366   0.0156   1.0000
   7.500   1.0152   0.01543   0.00847  -0.0356   0.0124   1.0000
   7.750   1.0361   0.01623   0.00937  -0.0346   0.0113   1.0000
   8.000   1.0557   0.01712   0.01034  -0.0336   0.0103   1.0000
   8.250   1.0723   0.01828   0.01159  -0.0322   0.0093   1.0000
   8.500   1.0834   0.02002   0.01346  -0.0302   0.0086   1.0000
   8.750   1.0994   0.02115   0.01473  -0.0287   0.0084   1.0000
   9.000   1.1155   0.02225   0.01594  -0.0273   0.0081   1.0000
   9.250   1.1295   0.02360   0.01742  -0.0256   0.0079   1.0000
   9.500   1.1432   0.02500   0.01894  -0.0240   0.0076   1.0000
   9.750   1.1559   0.02659   0.02068  -0.0222   0.0073   1.0000
  10.000   1.1669   0.02848   0.02274  -0.0203   0.0073   1.0000
  10.250   1.1762   0.03049   0.02493  -0.0182   0.0071   1.0000
  10.500   1.1832   0.03299   0.02766  -0.0160   0.0072   1.0000
  10.750   1.1864   0.03576   0.03069  -0.0138   0.0073   1.0000
  11.000   1.1841   0.03900   0.03422  -0.0114   0.0075   1.0000
  11.250   1.1761   0.04266   0.03817  -0.0093   0.0077   1.0000
  11.500   1.1644   0.04657   0.04234  -0.0077   0.0080   1.0000
  11.750   1.1485   0.05110   0.04711  -0.0069   0.0082   1.0000
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