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GOE 795 smoothed (goe795sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 795 smoothed (goe795sm-il)
Reynolds number: 50,000
Max Cl/Cd: 38.04 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe795sm-il-50000-n5.txt
Download as CSV file: xf-goe795sm-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4468   0.09730   0.09009  -0.0291   1.0000   0.0563
  -8.500  -0.4487   0.09359   0.08646  -0.0301   1.0000   0.0548
  -8.250  -0.4529   0.08990   0.08287  -0.0312   1.0000   0.0533
  -8.000  -0.4611   0.08607   0.07914  -0.0325   1.0000   0.0519
  -7.500  -0.4802   0.07471   0.06783  -0.0408   1.0000   0.0477
  -7.250  -0.4800   0.07070   0.06381  -0.0411   1.0000   0.0475
  -7.000  -0.4805   0.06635   0.05938  -0.0416   1.0000   0.0475
  -6.750  -0.4802   0.06198   0.05486  -0.0420   1.0000   0.0476
  -6.500  -0.4773   0.05824   0.05106  -0.0414   1.0000   0.0488
  -6.250  -0.4681   0.05671   0.04960  -0.0397   1.0000   0.0517
  -6.000  -0.4624   0.05295   0.04564  -0.0392   1.0000   0.0526
  -5.750  -0.4553   0.04902   0.04142  -0.0386   1.0000   0.0531
  -5.500  -0.4463   0.04516   0.03720  -0.0376   1.0000   0.0535
  -5.250  -0.4350   0.04161   0.03323  -0.0364   1.0000   0.0542
  -5.000  -0.4217   0.03840   0.02954  -0.0350   1.0000   0.0556
  -4.750  -0.4063   0.03553   0.02600  -0.0334   1.0000   0.0595
  -4.500  -0.3900   0.03320   0.02332  -0.0320   1.0000   0.0632
  -4.250  -0.3718   0.03123   0.02103  -0.0306   1.0000   0.0661
  -4.000  -0.3519   0.02932   0.01869  -0.0292   1.0000   0.0704
  -3.750  -0.3320   0.02782   0.01687  -0.0279   1.0000   0.0772
  -3.500  -0.3112   0.02651   0.01533  -0.0266   1.0000   0.0838
  -3.250  -0.2890   0.02519   0.01375  -0.0254   1.0000   0.0901
  -3.000  -0.2670   0.02435   0.01274  -0.0244   1.0000   0.1023
  -2.750  -0.2436   0.02345   0.01174  -0.0237   1.0000   0.1125
  -2.500  -0.2209   0.02279   0.01098  -0.0229   1.0000   0.1281
  -2.250  -0.1988   0.02218   0.01041  -0.0221   1.0000   0.1485
  -2.000  -0.1768   0.02160   0.00990  -0.0213   1.0000   0.1779
  -1.750  -0.1551   0.02097   0.00953  -0.0206   1.0000   0.2423
  -1.500  -0.1335   0.02012   0.00922  -0.0201   0.9997   0.3601
  -1.250  -0.0712   0.01819   0.00905  -0.0261   1.0000   1.0000
  -1.000  -0.0321   0.01851   0.00893  -0.0290   0.9915   1.0000
  -0.750   0.0073   0.01886   0.00891  -0.0318   0.9831   1.0000
  -0.500   0.0443   0.01914   0.00890  -0.0342   0.9735   1.0000
  -0.250   0.0808   0.01942   0.00895  -0.0365   0.9638   1.0000
   0.000   0.1188   0.01970   0.00902  -0.0389   0.9544   1.0000
   0.250   0.1561   0.01996   0.00912  -0.0412   0.9445   1.0000
   0.500   0.1905   0.02018   0.00922  -0.0429   0.9334   1.0000
   0.750   0.2261   0.02039   0.00934  -0.0447   0.9223   1.0000
   1.000   0.2632   0.02058   0.00946  -0.0468   0.9116   1.0000
   1.250   0.3041   0.02071   0.00956  -0.0494   0.9016   1.0000
   1.500   0.3390   0.02083   0.00968  -0.0508   0.8891   1.0000
   1.750   0.3745   0.02092   0.00978  -0.0523   0.8765   1.0000
   2.000   0.4104   0.02098   0.00988  -0.0537   0.8638   1.0000
   2.250   0.4451   0.02103   0.00998  -0.0548   0.8507   1.0000
   2.500   0.4790   0.02107   0.01012  -0.0557   0.8371   1.0000
   2.750   0.5123   0.02109   0.01023  -0.0563   0.8228   1.0000
   3.000   0.5451   0.02111   0.01035  -0.0568   0.8079   1.0000
   3.250   0.5775   0.02111   0.01051  -0.0571   0.7923   1.0000
   3.500   0.6101   0.02107   0.01060  -0.0573   0.7761   1.0000
   3.750   0.6376   0.02114   0.01080  -0.0566   0.7569   1.0000
   4.000   0.6663   0.02114   0.01095  -0.0560   0.7367   1.0000
   4.250   0.6938   0.02115   0.01113  -0.0551   0.7141   1.0000
   4.500   0.7211   0.02110   0.01121  -0.0539   0.6884   1.0000
   4.750   0.7451   0.02111   0.01133  -0.0522   0.6576   1.0000
   5.000   0.7688   0.02113   0.01141  -0.0503   0.6227   1.0000
   5.250   0.7903   0.02126   0.01160  -0.0482   0.5841   1.0000
   5.500   0.8109   0.02148   0.01188  -0.0460   0.5417   1.0000
   5.750   0.8300   0.02182   0.01217  -0.0436   0.4951   1.0000
   6.000   0.8467   0.02235   0.01259  -0.0410   0.4431   1.0000
   6.250   0.8614   0.02308   0.01315  -0.0383   0.3871   1.0000
   6.500   0.8735   0.02404   0.01388  -0.0355   0.3270   1.0000
   6.750   0.8838   0.02524   0.01480  -0.0327   0.2641   1.0000
   7.000   0.8932   0.02668   0.01597  -0.0300   0.2065   1.0000
   7.250   0.9030   0.02831   0.01730  -0.0276   0.1617   1.0000
   7.500   0.9135   0.03006   0.01884  -0.0254   0.1279   1.0000
   7.750   0.9247   0.03185   0.02051  -0.0232   0.1024   1.0000
   8.000   0.9384   0.03367   0.02237  -0.0213   0.0850   1.0000
   8.250   0.9524   0.03543   0.02419  -0.0194   0.0719   1.0000
   8.500   0.9696   0.03748   0.02627  -0.0179   0.0644   1.0000
   8.750   0.9868   0.03937   0.02843  -0.0165   0.0566   1.0000
   9.000   1.0050   0.04166   0.03089  -0.0153   0.0512   1.0000
   9.250   1.0256   0.04440   0.03400  -0.0142   0.0478   1.0000
   9.500   1.0400   0.04698   0.03682  -0.0127   0.0449   1.0000
   9.750   1.0513   0.04981   0.03968  -0.0114   0.0422   1.0000
  10.000   1.0551   0.05284   0.04329  -0.0089   0.0405   1.0000
  10.250   1.0539   0.05604   0.04694  -0.0063   0.0387   1.0000
  10.500   1.0483   0.05931   0.05055  -0.0035   0.0380   1.0000
  10.750   1.0381   0.06277   0.05433  -0.0008   0.0377   1.0000
  11.000   1.0245   0.06644   0.05828   0.0013   0.0375   1.0000
  11.250   1.0080   0.07047   0.06257   0.0024   0.0375   1.0000
  11.500   0.9885   0.07511   0.06743   0.0024   0.0376   1.0000
  11.750   0.9669   0.08047   0.07299   0.0010   0.0378   1.0000
  12.000   0.9438   0.08681   0.07949  -0.0018   0.0381   1.0000
  12.250   0.9209   0.09410   0.08689  -0.0060   0.0387   1.0000
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