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GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 178 AIRFOIL (goe178-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.98 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe178-il-1000000.txt
Download as CSV file: xf-goe178-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 178 AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4164   0.10817   0.10661  -0.0070   1.0000   0.0141
  -9.250  -0.4121   0.10409   0.10253  -0.0089   1.0000   0.0142
  -8.750  -0.4075   0.09552   0.09399  -0.0123   1.0000   0.0146
  -8.500  -0.3978   0.09328   0.09175  -0.0131   1.0000   0.0148
  -8.250  -0.3889   0.09083   0.08931  -0.0143   1.0000   0.0151
  -8.000  -0.3811   0.08807   0.08657  -0.0159   1.0000   0.0155
  -7.750  -0.3746   0.08504   0.08356  -0.0179   1.0000   0.0161
  -6.750  -0.3094   0.02194   0.01906  -0.0862   0.9727   0.0191
  -6.500  -0.2834   0.02223   0.01942  -0.0858   0.9642   0.0196
  -6.250  -0.2583   0.02344   0.02076  -0.0847   0.9546   0.0200
  -6.000  -0.2343   0.02338   0.02067  -0.0841   0.9427   0.0205
  -5.750  -0.2103   0.01993   0.01680  -0.0849   0.9288   0.0216
  -5.500  -0.1855   0.01790   0.01443  -0.0849   0.9100   0.0225
  -5.250  -0.1604   0.01736   0.01365  -0.0842   0.8796   0.0233
  -5.000  -0.1352   0.01572   0.01150  -0.0840   0.8459   0.0244
  -4.750  -0.1093   0.01369   0.00910  -0.0842   0.8194   0.0253
  -4.250  -0.0545   0.01258   0.00765  -0.0842   0.7728   0.0269
  -4.000  -0.0267   0.01210   0.00700  -0.0842   0.7473   0.0277
  -3.750   0.0014   0.01148   0.00613  -0.0842   0.7153   0.0280
  -3.500   0.0293   0.01096   0.00535  -0.0842   0.6745   0.0282
  -3.250   0.0573   0.01058   0.00472  -0.0842   0.6322   0.0286
  -3.000   0.0854   0.01026   0.00418  -0.0842   0.5952   0.0290
  -2.750   0.1137   0.01006   0.00381  -0.0842   0.5649   0.0298
  -2.500   0.1421   0.00982   0.00341  -0.0843   0.5405   0.0303
  -2.250   0.1706   0.00963   0.00310  -0.0844   0.5208   0.0307
  -2.000   0.1991   0.00949   0.00285  -0.0844   0.5046   0.0310
  -1.750   0.2277   0.00935   0.00263  -0.0845   0.4913   0.0312
  -1.500   0.2564   0.00914   0.00233  -0.0846   0.4800   0.0314
  -1.000   0.3140   0.00878   0.00181  -0.0849   0.4629   0.0324
  -0.750   0.3427   0.00868   0.00164  -0.0849   0.4560   0.0339
  -0.500   0.3715   0.00859   0.00153  -0.0850   0.4505   0.0354
  -0.250   0.4002   0.00854   0.00144  -0.0851   0.4448   0.0375
   0.000   0.4288   0.00853   0.00139  -0.0852   0.4395   0.0400
   0.250   0.4576   0.00844   0.00138  -0.0853   0.4353   0.0622
   0.500   0.4862   0.00843   0.00140  -0.0854   0.4305   0.0798
   0.750   0.5147   0.00846   0.00142  -0.0855   0.4259   0.0878
   1.000   0.5433   0.00845   0.00144  -0.0856   0.4213   0.0968
   1.250   0.5718   0.00845   0.00145  -0.0857   0.4154   0.1077
   1.500   0.6003   0.00837   0.00151  -0.0859   0.4106   0.1719
   1.750   0.6292   0.00802   0.00160  -0.0863   0.4072   0.3502
   2.750   0.7370   0.00686   0.00189  -0.0856   0.3914   1.0000
   3.000   0.7655   0.00694   0.00195  -0.0857   0.3860   1.0000
   3.250   0.7936   0.00706   0.00203  -0.0857   0.3808   1.0000
   3.500   0.8221   0.00713   0.00210  -0.0858   0.3766   1.0000
   3.750   0.8504   0.00722   0.00217  -0.0859   0.3702   1.0000
   4.000   0.8785   0.00732   0.00225  -0.0859   0.3611   1.0000
   4.250   0.9065   0.00745   0.00232  -0.0860   0.3476   1.0000
   4.500   0.9343   0.00760   0.00242  -0.0860   0.3340   1.0000
   4.750   0.9617   0.00782   0.00255  -0.0860   0.3103   1.0000
   5.000   0.9877   0.00828   0.00278  -0.0859   0.2679   1.0000
   5.250   1.0133   0.00880   0.00310  -0.0857   0.2308   1.0000
   5.500   1.0393   0.00924   0.00341  -0.0855   0.2051   1.0000
   5.750   1.0645   0.00981   0.00377  -0.0853   0.1660   1.0000
   6.000   1.0838   0.01139   0.00478  -0.0845   0.0565   1.0000
   6.250   1.1097   0.01177   0.00513  -0.0843   0.0479   1.0000
   6.500   1.1354   0.01219   0.00549  -0.0840   0.0311   1.0000
   6.750   1.1597   0.01280   0.00599  -0.0836   0.0169   1.0000
   7.000   1.1851   0.01322   0.00645  -0.0832   0.0149   1.0000
   7.250   1.2103   0.01363   0.00691  -0.0829   0.0138   1.0000
   7.500   1.2349   0.01412   0.00745  -0.0825   0.0128   1.0000
   7.750   1.2584   0.01474   0.00813  -0.0819   0.0119   1.0000
   8.000   1.2797   0.01565   0.00915  -0.0810   0.0110   1.0000
   8.250   1.3034   0.01616   0.00970  -0.0805   0.0107   1.0000
   8.500   1.3260   0.01676   0.01036  -0.0798   0.0103   1.0000
   8.750   1.3480   0.01741   0.01108  -0.0791   0.0098   1.0000
   9.000   1.3695   0.01806   0.01177  -0.0783   0.0093   1.0000
   9.250   1.3898   0.01879   0.01255  -0.0774   0.0088   1.0000
   9.500   1.4069   0.01980   0.01363  -0.0761   0.0084   1.0000
   9.750   1.4137   0.02169   0.01565  -0.0734   0.0080   1.0000
  10.000   1.4262   0.02291   0.01695  -0.0715   0.0078   1.0000
  10.250   1.4420   0.02376   0.01788  -0.0700   0.0077   1.0000
  10.500   1.4543   0.02478   0.01898  -0.0681   0.0075   1.0000
  10.750   1.4615   0.02589   0.02017  -0.0654   0.0074   1.0000
  11.000   1.4664   0.02718   0.02155  -0.0627   0.0072   1.0000
  11.250   1.4706   0.02867   0.02313  -0.0603   0.0071   1.0000
  11.500   1.4747   0.03031   0.02486  -0.0583   0.0069   1.0000
  11.750   1.4776   0.03222   0.02686  -0.0566   0.0068   1.0000
  12.000   1.4805   0.03430   0.02904  -0.0553   0.0067   1.0000
  12.250   1.4835   0.03655   0.03139  -0.0544   0.0065   1.0000
  12.500   1.4862   0.03896   0.03388  -0.0538   0.0064   1.0000
  12.750   1.4882   0.04156   0.03658  -0.0534   0.0063   1.0000
  13.000   1.4894   0.04435   0.03946  -0.0532   0.0062   1.0000
  13.250   1.4907   0.04722   0.04241  -0.0533   0.0061   1.0000
  13.500   1.4908   0.05031   0.04559  -0.0535   0.0060   1.0000
  13.750   1.4893   0.05360   0.04896  -0.0538   0.0059   1.0000
  14.000   1.4850   0.05719   0.05263  -0.0537   0.0057   1.0000
  14.250   1.4747   0.06128   0.05684  -0.0527   0.0056   1.0000
  14.500   1.4609   0.06599   0.06173  -0.0517   0.0055   1.0000
  14.750   1.4568   0.06999   0.06586  -0.0530   0.0054   1.0000
  15.000   1.4515   0.07422   0.07023  -0.0542   0.0054   1.0000
  15.250   1.4451   0.07869   0.07484  -0.0555   0.0053   1.0000
  15.500   1.4375   0.08344   0.07972  -0.0569   0.0053   1.0000
  15.750   1.4284   0.08849   0.08491  -0.0585   0.0053   1.0000
  16.000   1.4186   0.09379   0.09036  -0.0603   0.0053   1.0000
  16.250   1.4079   0.09939   0.09609  -0.0624   0.0052   1.0000
  16.500   1.3962   0.10529   0.10214  -0.0648   0.0052   1.0000
  16.750   1.3834   0.11150   0.10849  -0.0674   0.0052   1.0000
  17.000   1.3693   0.11816   0.11530  -0.0704   0.0052   1.0000
  17.250   1.3556   0.12498   0.12226  -0.0737   0.0052   1.0000
  17.500   1.3401   0.13236   0.12979  -0.0774   0.0052   1.0000
  17.750   1.3247   0.14000   0.13757  -0.0816   0.0052   1.0000
  18.000   1.3082   0.14824   0.14596  -0.0863   0.0053   1.0000
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