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GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 257 AIRFOIL (goe257-il)
Reynolds number: 200,000
Max Cl/Cd: 72.55 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe257-il-200000-n5.txt
Download as CSV file: xf-goe257-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 257 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3849   0.09403   0.09072  -0.0184   1.0000   0.0210
  -7.750  -0.3826   0.09083   0.08757  -0.0198   1.0000   0.0214
  -7.500  -0.3789   0.08747   0.08425  -0.0220   1.0000   0.0218
  -7.000  -0.3550   0.07903   0.07581  -0.0363   1.0000   0.0252
  -6.750  -0.3418   0.07456   0.07131  -0.0406   1.0000   0.0253
  -6.500  -0.3287   0.07011   0.06682  -0.0437   0.9992   0.0253
  -6.000  -0.2781   0.05938   0.05589  -0.0537   0.9787   0.0248
  -5.750  -0.2484   0.05373   0.05008  -0.0598   0.9657   0.0266
  -5.500  -0.2228   0.05145   0.04774  -0.0622   0.9505   0.0296
  -5.250  -0.1764   0.04691   0.04263  -0.0684   0.9342   0.0338
  -4.750  -0.1315   0.03856   0.03398  -0.0720   0.8926   0.0362
  -4.500  -0.1078   0.03654   0.03177  -0.0725   0.8652   0.0391
  -4.250  -0.0803   0.03351   0.02836  -0.0731   0.8372   0.0401
  -4.000  -0.0521   0.03027   0.02466  -0.0736   0.8112   0.0387
  -3.750  -0.0243   0.02821   0.02219  -0.0737   0.7893   0.0412
  -3.500   0.0055   0.02506   0.01846  -0.0739   0.7725   0.0374
  -3.250   0.0356   0.02268   0.01547  -0.0738   0.7583   0.0359
  -3.000   0.0627   0.02171   0.01428  -0.0740   0.7454   0.0376
  -2.750   0.0914   0.02052   0.01277  -0.0741   0.7341   0.0384
  -2.500   0.1208   0.01917   0.01105  -0.0742   0.7243   0.0374
  -2.250   0.1497   0.01817   0.00974  -0.0742   0.7156   0.0371
  -2.000   0.1785   0.01734   0.00868  -0.0743   0.7073   0.0372
  -1.750   0.2071   0.01666   0.00782  -0.0743   0.6997   0.0374
  -1.500   0.2356   0.01607   0.00711  -0.0744   0.6917   0.0378
  -1.250   0.2639   0.01565   0.00659  -0.0745   0.6843   0.0395
  -1.000   0.2923   0.01522   0.00609  -0.0746   0.6763   0.0405
  -0.750   0.3207   0.01479   0.00560  -0.0747   0.6689   0.0403
  -0.500   0.3491   0.01441   0.00518  -0.0748   0.6613   0.0402
  -0.250   0.3776   0.01411   0.00484  -0.0749   0.6542   0.0402
   0.000   0.4060   0.01385   0.00456  -0.0751   0.6466   0.0404
   0.250   0.4345   0.01364   0.00432  -0.0753   0.6384   0.0407
   0.500   0.4629   0.01350   0.00411  -0.0754   0.6289   0.0413
   0.750   0.4914   0.01338   0.00395  -0.0756   0.6178   0.0421
   1.000   0.5198   0.01331   0.00381  -0.0757   0.6071   0.0432
   1.250   0.5481   0.01328   0.00370  -0.0758   0.5969   0.0444
   1.500   0.5765   0.01323   0.00363  -0.0759   0.5858   0.0479
   1.750   0.6049   0.01319   0.00363  -0.0761   0.5750   0.0566
   2.000   0.6285   0.01098   0.00360  -0.0755   0.5645   1.0000
   2.250   0.6566   0.01110   0.00361  -0.0755   0.5518   1.0000
   2.500   0.6846   0.01123   0.00366  -0.0756   0.5391   1.0000
   2.750   0.7126   0.01137   0.00373  -0.0757   0.5266   1.0000
   3.000   0.7405   0.01152   0.00381  -0.0758   0.5130   1.0000
   3.250   0.7681   0.01169   0.00391  -0.0758   0.4985   1.0000
   3.500   0.7956   0.01187   0.00403  -0.0759   0.4845   1.0000
   3.750   0.8230   0.01208   0.00417  -0.0759   0.4705   1.0000
   4.000   0.8503   0.01231   0.00436  -0.0759   0.4562   1.0000
   4.250   0.8774   0.01256   0.00456  -0.0759   0.4421   1.0000
   4.500   0.9045   0.01281   0.00478  -0.0760   0.4292   1.0000
   4.750   0.9315   0.01307   0.00504  -0.0760   0.4163   1.0000
   5.000   0.9583   0.01334   0.00531  -0.0760   0.4013   1.0000
   5.250   0.9851   0.01361   0.00559  -0.0759   0.3864   1.0000
   5.500   1.0113   0.01394   0.00588  -0.0759   0.3626   1.0000
   5.750   1.0356   0.01446   0.00620  -0.0756   0.3037   1.0000
   6.000   1.0577   0.01535   0.00672  -0.0752   0.2470   1.0000
   6.250   1.0814   0.01601   0.00728  -0.0749   0.2211   1.0000
   6.500   1.1050   0.01667   0.00785  -0.0746   0.1960   1.0000
   6.750   1.1288   0.01727   0.00843  -0.0742   0.1728   1.0000
   7.000   1.1430   0.01915   0.00962  -0.0730   0.0651   1.0000
   7.250   1.1631   0.02019   0.01061  -0.0721   0.0385   1.0000
   7.500   1.1828   0.02123   0.01154  -0.0711   0.0216   1.0000
   7.750   1.2039   0.02204   0.01248  -0.0703   0.0189   1.0000
   8.000   1.2235   0.02297   0.01357  -0.0692   0.0167   1.0000
   8.250   1.2408   0.02406   0.01483  -0.0679   0.0150   1.0000
   8.500   1.2550   0.02538   0.01634  -0.0661   0.0140   1.0000
   8.750   1.2654   0.02689   0.01802  -0.0639   0.0134   1.0000
   9.000   1.2763   0.02818   0.01946  -0.0617   0.0130   1.0000
   9.250   1.2849   0.02954   0.02096  -0.0593   0.0126   1.0000
   9.500   1.2909   0.03094   0.02248  -0.0565   0.0120   1.0000
   9.750   1.2938   0.03244   0.02414  -0.0534   0.0114   1.0000
  10.000   1.2965   0.03415   0.02597  -0.0508   0.0109   1.0000
  10.250   1.2985   0.03611   0.02804  -0.0485   0.0105   1.0000
  10.500   1.3006   0.03823   0.03029  -0.0465   0.0103   1.0000
  10.750   1.3029   0.04049   0.03266  -0.0448   0.0100   1.0000
  11.000   1.3054   0.04287   0.03516  -0.0433   0.0098   1.0000
  11.250   1.3079   0.04537   0.03776  -0.0420   0.0096   1.0000
  11.500   1.3107   0.04794   0.04044  -0.0407   0.0094   1.0000
  11.750   1.3137   0.05063   0.04323  -0.0394   0.0092   1.0000
  12.000   1.3176   0.05341   0.04615  -0.0381   0.0090   1.0000
  12.250   1.3219   0.05643   0.04931  -0.0365   0.0089   1.0000
  12.500   1.3229   0.05961   0.05268  -0.0357   0.0087   1.0000
  12.750   1.3213   0.06282   0.05613  -0.0354   0.0086   1.0000
  13.000   1.3182   0.06629   0.05984  -0.0354   0.0085   1.0000
  13.250   1.3136   0.07007   0.06386  -0.0357   0.0083   1.0000
  13.500   1.3074   0.07418   0.06820  -0.0362   0.0081   1.0000
  13.750   1.2996   0.07858   0.07283  -0.0370   0.0079   1.0000
  14.000   1.2902   0.08335   0.07782  -0.0381   0.0078   1.0000
  14.250   1.2796   0.08850   0.08318  -0.0396   0.0077   1.0000
  14.500   1.2678   0.09406   0.08896  -0.0415   0.0076   1.0000
  14.750   1.2550   0.10007   0.09518  -0.0439   0.0076   1.0000
  15.000   1.2414   0.10654   0.10185  -0.0468   0.0076   1.0000
  15.250   1.2273   0.11344   0.10895  -0.0503   0.0076   1.0000
  15.500   1.2127   0.12080   0.11650  -0.0543   0.0076   1.0000
  15.750   1.1979   0.12859   0.12448  -0.0588   0.0076   1.0000
  16.000   1.1829   0.13689   0.13295  -0.0638   0.0077   1.0000
  16.250   1.1679   0.14572   0.14195  -0.0693   0.0077   1.0000
  16.500   1.1527   0.15524   0.15161  -0.0754   0.0078   1.0000
  16.750   1.1373   0.16547   0.16198  -0.0820   0.0079   1.0000
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