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GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 376 AIRFOIL (goe376-il)
Reynolds number: 50,000
Max Cl/Cd: 41.47 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe376-il-50000-n5.txt
Download as CSV file: xf-goe376-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 376 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3192   0.11114   0.10430  -0.0245   1.0000   0.0631
  -8.250  -0.3245   0.11041   0.10373  -0.0254   1.0000   0.0635
  -8.000  -0.3300   0.10980   0.10323  -0.0272   1.0000   0.0639
  -7.750  -0.3146   0.10256   0.09600  -0.0241   1.0000   0.0659
  -7.500  -0.3088   0.09914   0.09263  -0.0230   1.0000   0.0685
  -7.250  -0.3077   0.09675   0.09034  -0.0227   1.0000   0.0710
  -7.000  -0.3069   0.09471   0.08840  -0.0234   1.0000   0.0744
  -6.750  -0.3068   0.09373   0.08751  -0.0265   1.0000   0.0769
  -6.500  -0.3031   0.09375   0.08757  -0.0327   1.0000   0.0780
  -6.250  -0.3003   0.08725   0.08122  -0.0253   1.0000   0.0814
  -6.000  -0.2968   0.08462   0.07865  -0.0245   1.0000   0.0852
  -5.750  -0.2925   0.08273   0.07680  -0.0263   1.0000   0.0901
  -5.500  -0.2802   0.08258   0.07659  -0.0337   1.0000   0.0926
  -5.250  -0.2827   0.07756   0.07173  -0.0280   1.0000   0.0948
  -5.000  -0.2794   0.07481   0.06904  -0.0262   1.0000   0.0986
  -4.750  -0.2659   0.07336   0.06747  -0.0302   1.0000   0.1060
  -4.250  -0.2558   0.06748   0.06170  -0.0279   1.0000   0.1151
  -4.000  -0.2360   0.06459   0.05873  -0.0312   0.9975   0.1250
  -3.750  -0.1980   0.06071   0.05472  -0.0374   0.9882   0.1401
  -3.500  -0.1598   0.05697   0.05084  -0.0430   0.9781   0.1561
  -3.250  -0.1183   0.05376   0.04738  -0.0495   0.9668   0.1826
  -3.000  -0.0895   0.05032   0.04392  -0.0519   0.9557   0.2142
  -2.000   0.0997   0.03880   0.03063  -0.0713   0.9149   0.1188
  -1.750   0.1445   0.03617   0.02759  -0.0744   0.9071   0.1013
  -1.500   0.1838   0.03420   0.02516  -0.0761   0.8963   0.0886
  -1.250   0.2219   0.03232   0.02288  -0.0778   0.8859   0.0825
  -1.000   0.2661   0.03095   0.02091  -0.0798   0.8771   0.0772
  -0.750   0.3003   0.02945   0.01921  -0.0808   0.8653   0.0757
  -0.500   0.3347   0.02835   0.01780  -0.0816   0.8528   0.0761
  -0.250   0.3697   0.02746   0.01657  -0.0823   0.8401   0.0774
   0.000   0.4034   0.02648   0.01537  -0.0829   0.8271   0.0773
   0.250   0.4377   0.02557   0.01426  -0.0834   0.8139   0.0769
   0.500   0.4750   0.02476   0.01320  -0.0844   0.8005   0.0768
   0.750   0.5101   0.02407   0.01233  -0.0849   0.7861   0.0769
   1.000   0.5426   0.02352   0.01163  -0.0851   0.7711   0.0775
   1.250   0.5733   0.02306   0.01106  -0.0850   0.7552   0.0784
   1.500   0.6028   0.02266   0.01060  -0.0848   0.7387   0.0819
   1.750   0.6318   0.02242   0.01026  -0.0845   0.7215   0.0882
   2.000   0.6606   0.02225   0.00999  -0.0841   0.7039   0.0940
   2.250   0.6890   0.02209   0.00974  -0.0836   0.6858   0.1009
   2.500   0.7163   0.02199   0.00960  -0.0829   0.6672   0.1143
   2.750   0.7531   0.02042   0.00964  -0.0847   0.6464   1.0000
   3.000   0.7782   0.02067   0.00962  -0.0836   0.6276   1.0000
   3.250   0.8033   0.02093   0.00967  -0.0826   0.6098   1.0000
   3.500   0.8281   0.02122   0.00978  -0.0817   0.5926   1.0000
   3.750   0.8518   0.02156   0.01004  -0.0806   0.5749   1.0000
   4.000   0.8757   0.02191   0.01030  -0.0797   0.5578   1.0000
   4.250   0.8995   0.02228   0.01059  -0.0787   0.5411   1.0000
   4.500   0.9233   0.02267   0.01094  -0.0777   0.5246   1.0000
   4.750   0.9468   0.02308   0.01130  -0.0768   0.5083   1.0000
   5.000   0.9702   0.02353   0.01170  -0.0758   0.4923   1.0000
   5.250   0.9934   0.02400   0.01214  -0.0748   0.4762   1.0000
   5.500   1.0163   0.02451   0.01267  -0.0738   0.4603   1.0000
   5.750   1.0389   0.02505   0.01320  -0.0727   0.4444   1.0000
   6.000   1.0612   0.02563   0.01379  -0.0717   0.4286   1.0000
   6.250   1.0831   0.02625   0.01444  -0.0706   0.4131   1.0000
   6.500   1.1044   0.02690   0.01518  -0.0695   0.3978   1.0000
   6.750   1.1254   0.02759   0.01597  -0.0684   0.3830   1.0000
   7.000   1.1458   0.02831   0.01679  -0.0672   0.3685   1.0000
   7.250   1.1659   0.02906   0.01769  -0.0660   0.3547   1.0000
   7.500   1.1857   0.02986   0.01868  -0.0648   0.3418   1.0000
   7.750   1.2055   0.03069   0.01968  -0.0636   0.3297   1.0000
   8.000   1.2258   0.03154   0.02068  -0.0625   0.3190   1.0000
   8.250   1.2465   0.03236   0.02165  -0.0614   0.3091   1.0000
   8.500   1.2636   0.03329   0.02286  -0.0599   0.2972   1.0000
   8.750   1.2759   0.03375   0.02334  -0.0575   0.2799   1.0000
   9.000   1.2843   0.03442   0.02411  -0.0549   0.2612   1.0000
   9.250   1.2959   0.03526   0.02508  -0.0528   0.2475   1.0000
   9.500   1.3080   0.03623   0.02626  -0.0508   0.2358   1.0000
   9.750   1.3162   0.03728   0.02754  -0.0484   0.2226   1.0000
  10.000   1.3189   0.03838   0.02882  -0.0455   0.2065   1.0000
  10.250   1.3184   0.03964   0.03024  -0.0424   0.1912   1.0000
  10.500   1.3120   0.04129   0.03203  -0.0392   0.1691   1.0000
  10.750   1.3034   0.04347   0.03421  -0.0367   0.1411   1.0000
  11.000   1.2956   0.04616   0.03688  -0.0350   0.1139   1.0000
  11.250   1.2861   0.04946   0.04014  -0.0338   0.0846   1.0000
  11.500   1.2718   0.05363   0.04416  -0.0334   0.0675   1.0000
  11.750   1.2578   0.05822   0.04870  -0.0337   0.0599   1.0000
  12.000   1.2445   0.06308   0.05361  -0.0344   0.0552   1.0000
  12.250   1.2319   0.06813   0.05881  -0.0354   0.0515   1.0000
  12.500   1.2190   0.07349   0.06429  -0.0369   0.0489   1.0000
  12.750   1.2064   0.07898   0.06991  -0.0386   0.0472   1.0000
  13.000   1.1933   0.08471   0.07573  -0.0404   0.0458   1.0000
  13.250   1.1825   0.09014   0.08125  -0.0422   0.0445   1.0000
  13.500   1.1737   0.09537   0.08664  -0.0438   0.0429   1.0000
  13.750   1.1663   0.10041   0.09183  -0.0454   0.0416   1.0000
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