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GOE 290 (MVA 290) AIRFOIL (goe290-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 290 (MVA 290) AIRFOIL (goe290-il)
Reynolds number: 50,000
Max Cl/Cd: 6.59 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe290-il-50000.txt
Download as CSV file: xf-goe290-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 290 (MVA 290) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2477   0.11801   0.11094  -0.0263   1.0000   0.3179
  -9.500  -0.2315   0.11472   0.10769  -0.0259   1.0000   0.3266
  -9.250  -0.2692   0.11587   0.10905  -0.0256   1.0000   0.3341
  -9.000  -0.2299   0.10970   0.10287  -0.0253   1.0000   0.3398
  -8.750  -0.2292   0.10766   0.10094  -0.0245   1.0000   0.3476
  -8.500  -0.2714   0.10871   0.10225  -0.0222   1.0000   0.3535
  -8.250  -0.2520   0.10446   0.09808  -0.0212   1.0000   0.3563
  -8.000  -0.2584   0.10329   0.09710  -0.0178   1.0000   0.3595
  -7.750  -0.2979   0.10574   0.09984  -0.0108   1.0000   0.3610
  -7.250  -0.5087   0.07382   0.06763  -0.0465   0.9705   0.1945
  -7.000  -0.4811   0.06824   0.06188  -0.0521   0.9574   0.1908
  -6.750  -0.4715   0.06083   0.05407  -0.0582   0.9438   0.1859
  -6.500  -0.4575   0.05473   0.04739  -0.0628   0.9309   0.1849
  -6.250  -0.4266   0.05017   0.04227  -0.0675   0.9209   0.1873
  -6.000  -0.4045   0.04694   0.03852  -0.0694   0.9085   0.1894
  -5.750  -0.3795   0.04422   0.03514  -0.0711   0.8973   0.1934
  -5.500  -0.3354   0.04240   0.03332  -0.0746   0.8889   0.2010
  -5.250  -0.3137   0.04109   0.03169  -0.0747   0.8773   0.2071
  -5.000  -0.2660   0.03953   0.03003  -0.0785   0.8706   0.2186
  -4.750  -0.2516   0.03891   0.02907  -0.0772   0.8596   0.2269
  -4.500  -0.2048   0.03783   0.02799  -0.0804   0.8533   0.2440
  -4.250  -0.1929   0.03795   0.02825  -0.0785   0.8429   0.2549
  -4.000  -0.1525   0.03727   0.02756  -0.0806   0.8363   0.2806
  -3.750  -0.1372   0.03749   0.02792  -0.0791   0.8283   0.3029
  -3.500  -0.1157   0.03751   0.02812  -0.0783   0.8210   0.3432
  -3.250  -0.0802   0.03688   0.02791  -0.0784   0.8159   0.4376
  -3.000  -0.0834   0.03770   0.02890  -0.0740   0.8076   0.4792
  -2.750  -0.0656   0.03810   0.02940  -0.0721   0.8014   0.5296
  -2.500  -0.0318   0.03823   0.02959  -0.0720   0.7969   0.5759
  -2.250  -0.0368   0.03936   0.03075  -0.0681   0.7907   0.5960
  -2.000  -0.0272   0.04010   0.03155  -0.0656   0.7848   0.6218
  -1.750  -0.0037   0.04054   0.03205  -0.0643   0.7799   0.6588
  -1.500   0.0171   0.04111   0.03273  -0.0622   0.7759   0.6997
  -1.250   0.0091   0.04240   0.03414  -0.0578   0.7719   0.7251
  -1.000   0.0129   0.04331   0.03516  -0.0545   0.7678   0.7592
  -0.750   0.0241   0.04401   0.03594  -0.0518   0.7638   0.7969
  -0.500   0.0433   0.04459   0.03662  -0.0501   0.7603   0.8385
  -0.250   0.0781   0.04535   0.03744  -0.0514   0.7564   0.8949
   0.000   0.1483   0.04731   0.03936  -0.0632   0.7498   0.9854
   0.250   0.1473   0.04805   0.03974  -0.0652   0.7478   1.0000
   0.500   0.1609   0.04944   0.04082  -0.0660   0.7453   1.0000
   0.750   0.1922   0.05062   0.04172  -0.0680   0.7403   1.0000
   1.000   0.2095   0.05216   0.04305  -0.0682   0.7365   1.0000
   1.250   0.2114   0.05396   0.04472  -0.0670   0.7349   1.0000
   1.500   0.2151   0.05569   0.04634  -0.0659   0.7324   1.0000
   1.750   0.2242   0.05733   0.04786  -0.0653   0.7284   1.0000
   2.000   0.2585   0.05844   0.04879  -0.0664   0.7153   1.0000
   2.250   0.2686   0.05988   0.05014  -0.0655   0.7065   1.0000
   2.500   0.2922   0.06107   0.05120  -0.0654   0.6929   1.0000
   2.750   0.3287   0.06194   0.05194  -0.0662   0.6779   1.0000
   3.000   0.3359   0.06357   0.05351  -0.0651   0.6680   1.0000
   3.250   0.3559   0.06500   0.05485  -0.0648   0.6558   1.0000
   3.500   0.2779   0.07227   0.06236  -0.0637   0.7274   1.0000
   3.750   0.3863   0.06831   0.05804  -0.0639   0.6336   1.0000
   4.000   0.4181   0.06949   0.05914  -0.0642   0.6206   1.0000
   4.250   0.4220   0.07169   0.06133  -0.0633   0.6106   1.0000
   4.500   0.4364   0.07358   0.06318  -0.0628   0.5986   1.0000
   4.750   0.4873   0.07394   0.06345  -0.0637   0.5853   1.0000
   5.000   0.4574   0.07802   0.06756  -0.0619   0.5783   1.0000
   5.250   0.4563   0.08139   0.07094  -0.0618   0.5758   1.0000
   5.500   0.4567   0.08548   0.07503  -0.0626   0.5816   1.0000
   5.750   0.4849   0.08918   0.07872  -0.0647   0.5857   1.0000
   6.000   0.4012   0.09608   0.08579  -0.0646   0.6483   1.0000
   6.250   0.4433   0.10045   0.09011  -0.0675   0.6428   1.0000
   6.500   0.4222   0.10065   0.09031  -0.0642   0.6317   1.0000
   6.750   0.4516   0.10392   0.09355  -0.0658   0.6258   1.0000
   7.000   0.4519   0.10610   0.09571  -0.0650   0.6206   1.0000
   7.250   0.4593   0.10782   0.09742  -0.0644   0.6109   1.0000
   7.500   0.4913   0.11155   0.10114  -0.0662   0.6061   1.0000
   7.750   0.4800   0.11266   0.10225  -0.0644   0.5984   1.0000
   8.000   0.4978   0.11506   0.10463  -0.0647   0.5903   1.0000
   8.250   0.5326   0.11941   0.10899  -0.0667   0.5864   1.0000
   8.500   0.5134   0.11975   0.10932  -0.0645   0.5790   1.0000
   8.750   0.5280   0.12212   0.11171  -0.0648   0.5722   1.0000
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