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GOE 795 smoothed (goe795sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 795 smoothed (goe795sm-il)
Reynolds number: 50,000
Max Cl/Cd: 37.72 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe795sm-il-50000.txt
Download as CSV file: xf-goe795sm-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 795 smoothed                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4521   0.11458   0.10745  -0.0186   1.0000   0.1990
  -9.000  -0.4348   0.10939   0.10224  -0.0172   1.0000   0.2067
  -8.750  -0.4517   0.10868   0.10169  -0.0188   1.0000   0.2134
  -8.500  -0.4343   0.10369   0.09669  -0.0173   1.0000   0.2245
  -8.250  -0.4329   0.10053   0.09361  -0.0170   1.0000   0.2329
  -8.000  -0.4488   0.09948   0.09269  -0.0174   1.0000   0.2418
  -7.750  -0.4431   0.09605   0.08932  -0.0160   1.0000   0.2554
  -7.500  -0.4392   0.09278   0.08607  -0.0147   1.0000   0.2688
  -7.250  -0.4362   0.08962   0.08298  -0.0132   1.0000   0.2817
  -7.000  -0.4359   0.08663   0.08008  -0.0117   1.0000   0.2939
  -6.750  -0.4394   0.08397   0.07752  -0.0099   1.0000   0.3062
  -6.500  -0.4411   0.08121   0.07486  -0.0082   1.0000   0.3210
  -6.250  -0.4437   0.07860   0.07234  -0.0065   1.0000   0.3380
  -6.000  -0.4605   0.07697   0.07086  -0.0054   1.0000   0.3570
  -5.750  -0.4429   0.07297   0.06687  -0.0016   1.0000   0.3781
  -5.500  -0.4440   0.07061   0.06460   0.0023   1.0000   0.4107
  -4.750  -0.4198   0.04814   0.04044  -0.0323   1.0000   0.1575
  -4.500  -0.4053   0.04451   0.03668  -0.0311   1.0000   0.1558
  -4.250  -0.3895   0.04097   0.03284  -0.0302   1.0000   0.1525
  -4.000  -0.3700   0.03685   0.02772  -0.0295   1.0000   0.1435
  -3.750  -0.3507   0.03393   0.02433  -0.0282   1.0000   0.1432
  -3.500  -0.3324   0.03197   0.02232  -0.0269   1.0000   0.1526
  -3.250  -0.3107   0.02976   0.01949  -0.0256   1.0000   0.1583
  -3.000  -0.2888   0.02791   0.01748  -0.0243   1.0000   0.1655
  -2.750  -0.2674   0.02658   0.01589  -0.0231   1.0000   0.1807
  -2.500  -0.2438   0.02527   0.01434  -0.0220   1.0000   0.1963
  -2.250  -0.2191   0.02408   0.01308  -0.0212   1.0000   0.2185
  -2.000  -0.1938   0.02304   0.01201  -0.0205   1.0000   0.2530
  -1.750  -0.1078   0.01780   0.00972  -0.0288   1.0000   1.0000
  -1.500  -0.0888   0.01798   0.00925  -0.0275   1.0000   1.0000
  -1.250  -0.0712   0.01819   0.00905  -0.0261   1.0000   1.0000
  -1.000  -0.0537   0.01843   0.00895  -0.0247   1.0000   1.0000
  -0.750  -0.0363   0.01870   0.00895  -0.0234   1.0000   1.0000
  -0.500  -0.0189   0.01901   0.00898  -0.0222   1.0000   1.0000
  -0.250  -0.0015   0.01934   0.00910  -0.0211   1.0000   1.0000
   0.000   0.0159   0.01972   0.00929  -0.0200   1.0000   1.0000
   0.250   0.0333   0.02012   0.00953  -0.0190   1.0000   1.0000
   0.500   0.0506   0.02057   0.00983  -0.0181   1.0000   1.0000
   0.750   0.0677   0.02105   0.01017  -0.0172   1.0000   1.0000
   1.000   0.0848   0.02157   0.01059  -0.0165   1.0000   1.0000
   1.250   0.1017   0.02214   0.01107  -0.0157   1.0000   1.0000
   1.500   0.1183   0.02276   0.01162  -0.0151   1.0000   1.0000
   1.750   0.1348   0.02342   0.01223  -0.0145   1.0000   1.0000
   2.000   0.1510   0.02414   0.01290  -0.0139   1.0000   1.0000
   2.250   0.1741   0.02505   0.01379  -0.0150   0.9968   1.0000
   2.500   0.2298   0.02651   0.01528  -0.0221   0.9780   1.0000
   2.750   0.2832   0.02778   0.01661  -0.0285   0.9589   1.0000
   3.000   0.3311   0.02881   0.01772  -0.0336   0.9388   1.0000
   3.250   0.3809   0.02973   0.01880  -0.0386   0.9182   1.0000
   3.500   0.4258   0.03048   0.01969  -0.0425   0.8967   1.0000
   3.750   0.4768   0.03109   0.02049  -0.0470   0.8752   1.0000
   4.000   0.5178   0.03158   0.02122  -0.0495   0.8516   1.0000
   4.250   0.5697   0.03175   0.02165  -0.0531   0.8283   1.0000
   4.500   0.6321   0.03127   0.02153  -0.0575   0.8039   1.0000
   4.750   0.6928   0.03022   0.02092  -0.0606   0.7761   1.0000
   5.000   0.7458   0.02881   0.01988  -0.0612   0.7442   1.0000
   5.250   0.7944   0.02717   0.01858  -0.0606   0.7084   1.0000
   5.500   0.8345   0.02574   0.01744  -0.0586   0.6673   1.0000
   5.750   0.8679   0.02456   0.01637  -0.0556   0.6185   1.0000
   6.000   0.8893   0.02403   0.01581  -0.0514   0.5582   1.0000
   6.250   0.9049   0.02399   0.01546  -0.0465   0.4818   1.0000
   6.500   0.9128   0.02493   0.01579  -0.0413   0.3922   1.0000
   6.750   0.9192   0.02662   0.01686  -0.0368   0.3084   1.0000
   7.000   0.9281   0.02861   0.01824  -0.0332   0.2413   1.0000
   7.250   0.9418   0.03088   0.02019  -0.0306   0.1893   1.0000
   7.500   0.9637   0.03367   0.02279  -0.0291   0.1535   1.0000
   7.750   0.9879   0.03661   0.02555  -0.0282   0.1306   1.0000
   8.000   1.0123   0.03986   0.02894  -0.0273   0.1177   1.0000
   8.250   1.0282   0.04247   0.03197  -0.0252   0.1077   1.0000
   8.500   1.0451   0.04628   0.03612  -0.0235   0.1032   1.0000
   8.750   1.0538   0.05006   0.04059  -0.0207   0.1015   1.0000
   9.000   1.0579   0.05395   0.04501  -0.0178   0.1000   1.0000
   9.250   1.0578   0.05784   0.04936  -0.0150   0.0988   1.0000
   9.500   1.0541   0.06168   0.05357  -0.0121   0.0972   1.0000
   9.750   1.0455   0.06578   0.05802  -0.0094   0.0970   1.0000
  10.000   1.0283   0.07025   0.06283  -0.0067   0.0987   1.0000
  10.250   1.0074   0.07446   0.06726  -0.0041   0.0995   1.0000
  10.500   0.9855   0.07875   0.07168  -0.0022   0.1011   1.0000
  10.750   0.9653   0.08355   0.07657  -0.0017   0.1025   1.0000
  11.000   0.9515   0.08882   0.08189  -0.0021   0.1038   1.0000
  11.250   0.9463   0.09437   0.08746  -0.0028   0.1048   1.0000
  11.500   0.8922   0.10610   0.09922  -0.0114   0.1186   1.0000
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