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GOE 547 AIRFOIL (goe547-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 547 AIRFOIL (goe547-il)
Reynolds number: 50,000
Max Cl/Cd: 36.92 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe547-il-50000.txt
Download as CSV file: xf-goe547-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 547 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3645   0.10838   0.10166  -0.0268   1.0000   0.2570
  -8.000  -0.3607   0.10525   0.09858  -0.0249   1.0000   0.2649
  -7.750  -0.3791   0.10486   0.09832  -0.0225   1.0000   0.2729
  -7.500  -0.3712   0.10146   0.09493  -0.0204   1.0000   0.2827
  -7.250  -0.4011   0.10191   0.09556  -0.0172   1.0000   0.2890
  -7.000  -0.3878   0.09804   0.09170  -0.0152   1.0000   0.2991
  -6.750  -0.4259   0.09897   0.09282  -0.0110   1.0000   0.3047
  -6.500  -0.4095   0.09486   0.08871  -0.0093   1.0000   0.3149
  -6.250  -0.4574   0.09627   0.09033  -0.0059   1.0000   0.3209
  -6.000  -0.4361   0.09190   0.08594  -0.0030   1.0000   0.3320
  -5.750  -0.4467   0.08988   0.08402  -0.0006   1.0000   0.3409
  -5.250  -0.4723   0.08686   0.08116   0.0033   1.0000   0.3668
  -5.000  -0.4634   0.08361   0.07793   0.0066   1.0000   0.3775
  -4.750  -0.4672   0.08140   0.07579   0.0090   1.0000   0.3924
  -4.500  -0.4838   0.08028   0.07475   0.0097   1.0000   0.4141
  -4.250  -0.4759   0.07719   0.07169   0.0142   1.0000   0.4326
  -4.000  -0.4074   0.05495   0.04795  -0.0388   1.0000   0.1959
  -3.750  -0.3813   0.04942   0.04196  -0.0424   1.0000   0.1773
  -3.500  -0.3518   0.04428   0.03603  -0.0461   1.0000   0.1639
  -3.250  -0.3278   0.04116   0.03242  -0.0471   1.0000   0.1592
  -3.000  -0.3029   0.03847   0.02911  -0.0478   1.0000   0.1566
  -2.750  -0.2808   0.03684   0.02715  -0.0476   1.0000   0.1592
  -2.500  -0.2583   0.03548   0.02539  -0.0474   1.0000   0.1634
  -2.250  -0.2349   0.03417   0.02359  -0.0470   1.0000   0.1664
  -2.000  -0.2132   0.03309   0.02236  -0.0465   1.0000   0.1702
  -1.750  -0.1907   0.03232   0.02142  -0.0460   1.0000   0.1766
  -1.500  -0.1692   0.03168   0.02065  -0.0453   1.0000   0.1868
  -1.250  -0.1485   0.03121   0.02017  -0.0445   1.0000   0.2048
  -1.000  -0.1235   0.03074   0.01966  -0.0442   1.0000   0.2322
  -0.750  -0.0960   0.02996   0.01931  -0.0444   1.0000   0.3127
  -0.500  -0.0746   0.02801   0.01963  -0.0413   1.0000   0.7057
  -0.250  -0.0480   0.02748   0.01907  -0.0423   1.0000   1.0000
   0.000  -0.0267   0.02810   0.01924  -0.0424   1.0000   1.0000
   0.250  -0.0063   0.02875   0.01952  -0.0422   1.0000   1.0000
   0.500   0.0135   0.02943   0.01990  -0.0420   1.0000   1.0000
   0.750   0.0330   0.03014   0.02036  -0.0418   1.0000   1.0000
   1.000   0.0522   0.03088   0.02088  -0.0416   1.0000   1.0000
   1.250   0.0711   0.03166   0.02145  -0.0413   1.0000   1.0000
   1.500   0.0897   0.03247   0.02208  -0.0411   1.0000   1.0000
   1.750   0.1081   0.03331   0.02278  -0.0409   1.0000   1.0000
   2.000   0.1263   0.03419   0.02353  -0.0407   1.0000   1.0000
   2.250   0.1442   0.03511   0.02433  -0.0405   1.0000   1.0000
   2.500   0.1618   0.03607   0.02519  -0.0403   1.0000   1.0000
   2.750   0.2299   0.03894   0.02793  -0.0496   0.9738   1.0000
   3.000   0.2725   0.04059   0.02951  -0.0538   0.9556   1.0000
   3.250   0.3088   0.04195   0.03083  -0.0568   0.9388   1.0000
   3.500   0.3478   0.04335   0.03221  -0.0600   0.9209   1.0000
   3.750   0.3951   0.04489   0.03374  -0.0641   0.9017   1.0000
   4.000   0.4230   0.04583   0.03470  -0.0652   0.8834   1.0000
   4.250   0.4557   0.04686   0.03577  -0.0668   0.8644   1.0000
   4.500   0.4947   0.04790   0.03687  -0.0692   0.8453   1.0000
   5.000   0.5615   0.04974   0.03888  -0.0719   0.8079   1.0000
   5.250   0.5919   0.05056   0.03980  -0.0726   0.7887   1.0000
   5.500   0.6292   0.05125   0.04061  -0.0740   0.7702   1.0000
   5.750   0.6710   0.05176   0.04130  -0.0758   0.7527   1.0000
   6.000   0.6885   0.05266   0.04232  -0.0747   0.7318   1.0000
   6.250   0.7209   0.05317   0.04299  -0.0751   0.7124   1.0000
   6.500   0.7627   0.05322   0.04327  -0.0761   0.6943   1.0000
   6.750   0.7844   0.05386   0.04407  -0.0751   0.6725   1.0000
   7.000   0.8287   0.05296   0.04343  -0.0752   0.6514   1.0000
   7.250   0.8734   0.05135   0.04211  -0.0744   0.6286   1.0000
   7.500   0.9388   0.04725   0.03839  -0.0737   0.6069   1.0000
   7.750   1.0479   0.04004   0.03184  -0.0766   0.5883   1.0000
   8.000   1.1025   0.03652   0.02865  -0.0755   0.5530   1.0000
   8.250   1.1545   0.03252   0.02478  -0.0734   0.5008   1.0000
   8.500   1.1722   0.03175   0.02385  -0.0691   0.4474   1.0000
   8.750   1.1818   0.03212   0.02376  -0.0644   0.3851   1.0000
   9.000   1.1851   0.03370   0.02473  -0.0597   0.3234   1.0000
   9.250   1.1807   0.03555   0.02608  -0.0546   0.2742   1.0000
   9.500   1.1716   0.03743   0.02774  -0.0495   0.2359   1.0000
   9.750   1.1677   0.03951   0.02946  -0.0454   0.1998   1.0000
  10.000   1.1691   0.04181   0.03160  -0.0421   0.1673   1.0000
  10.250   1.1905   0.04462   0.03409  -0.0409   0.1365   1.0000
  10.500   1.2423   0.04889   0.03830  -0.0436   0.1140   1.0000
  10.750   1.2845   0.05351   0.04303  -0.0460   0.1033   1.0000
  11.000   1.2845   0.05628   0.04633  -0.0424   0.0997   1.0000
  11.250   1.2898   0.05949   0.04989  -0.0399   0.0961   1.0000
  11.500   1.2978   0.06320   0.05387  -0.0380   0.0940   1.0000
  11.750   1.3038   0.06727   0.05819  -0.0362   0.0924   1.0000
  12.000   1.2986   0.07118   0.06239  -0.0333   0.0919   1.0000
  12.250   1.2837   0.07478   0.06631  -0.0299   0.0919   1.0000
  12.500   1.1091   0.07507   0.06773  -0.0173   0.0986   1.0000
  12.750   1.0767   0.08079   0.07371  -0.0165   0.0996   1.0000
  13.000   1.0434   0.08703   0.08018  -0.0167   0.1010   1.0000
  13.250   1.0112   0.09363   0.08693  -0.0179   0.1023   1.0000
  13.500   0.9820   0.10037   0.09381  -0.0198   0.1036   1.0000
  13.750   1.0636   0.11114   0.10423  -0.0300   0.1015   1.0000
  14.000   1.0124   0.12484   0.11800  -0.0388   0.1066   1.0000
  14.250   1.0241   0.12818   0.12136  -0.0380   0.1047   1.0000
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