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GOE 587 AIRFOIL (goe587-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 587 AIRFOIL (goe587-il)
Reynolds number: 50,000
Max Cl/Cd: 36.6 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe587-il-50000.txt
Download as CSV file: xf-goe587-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 587 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  -0.4746   0.10402   0.09726  -0.0085   1.0000   0.1318
  -8.000  -0.4828   0.10249   0.09584  -0.0110   1.0000   0.1352
  -7.750  -0.4937   0.10170   0.09516  -0.0156   1.0000   0.1363
  -7.500  -0.4737   0.09488   0.08836  -0.0114   1.0000   0.1462
  -7.250  -0.4816   0.09389   0.08743  -0.0165   1.0000   0.1497
  -7.000  -0.4671   0.08822   0.08181  -0.0133   1.0000   0.1581
  -6.750  -0.4719   0.08685   0.08048  -0.0184   1.0000   0.1640
  -6.500  -0.4610   0.08217   0.07577  -0.0163   1.0000   0.1754
  -6.250  -0.4535   0.07824   0.07189  -0.0157   1.0000   0.1848
  -6.000  -0.4479   0.07488   0.06857  -0.0161   1.0000   0.1967
  -5.750  -0.4415   0.07164   0.06534  -0.0160   1.0000   0.2125
  -5.500  -0.1092   0.04601   0.03882  -0.0137   1.0000   1.0000
  -5.250  -0.0981   0.04369   0.03654  -0.0148   1.0000   1.0000
  -5.000  -0.0870   0.04138   0.03427  -0.0160   1.0000   1.0000
  -4.750  -0.1902   0.04761   0.04092   0.0086   1.0000   0.9049
  -4.250  -0.4248   0.05248   0.04677   0.0045   1.0000   0.4450
  -4.000  -0.4253   0.04942   0.04387   0.0117   1.0000   0.5006
  -3.750  -0.4244   0.04668   0.04124   0.0172   1.0000   0.5446
  -3.500  -0.4196   0.04372   0.03840   0.0228   1.0000   0.5837
  -3.250  -0.4130   0.04079   0.03548   0.0253   1.0000   0.6058
  -3.000  -0.3990   0.03764   0.03231   0.0233   1.0000   0.6080
  -2.750  -0.2384   0.03514   0.02689  -0.0201   1.0000   0.2211
  -2.500  -0.2051   0.03269   0.02369  -0.0201   1.0000   0.1749
  -2.250  -0.1786   0.03021   0.02070  -0.0190   1.0000   0.1542
  -2.000  -0.1537   0.02819   0.01820  -0.0178   1.0000   0.1441
  -1.750  -0.1292   0.02640   0.01596  -0.0165   1.0000   0.1403
  -1.500  -0.1066   0.02511   0.01428  -0.0153   1.0000   0.1508
  -1.250  -0.0827   0.02363   0.01264  -0.0144   1.0000   0.1601
  -1.000  -0.0535   0.02237   0.01106  -0.0140   1.0000   0.1702
  -0.750  -0.0278   0.02143   0.01007  -0.0135   1.0000   0.1994
  -0.500  -0.0067   0.02061   0.00926  -0.0123   1.0000   0.2228
  -0.250   0.0594   0.01701   0.00759  -0.0176   1.0000   1.0000
   0.000   0.0701   0.01741   0.00762  -0.0155   1.0000   1.0000
   0.250   0.0808   0.01788   0.00783  -0.0137   1.0000   1.0000
   0.500   0.0918   0.01840   0.00814  -0.0121   1.0000   1.0000
   0.750   0.1033   0.01898   0.00851  -0.0108   1.0000   1.0000
   1.000   0.1152   0.01962   0.00899  -0.0098   1.0000   1.0000
   1.250   0.1454   0.02046   0.00968  -0.0123   0.9932   1.0000
   1.500   0.1994   0.02141   0.01051  -0.0192   0.9752   1.0000
   1.750   0.2522   0.02228   0.01132  -0.0255   0.9582   1.0000
   2.000   0.3020   0.02302   0.01205  -0.0310   0.9413   1.0000
   2.250   0.3457   0.02367   0.01274  -0.0351   0.9236   1.0000
   2.500   0.3917   0.02428   0.01346  -0.0395   0.9068   1.0000
   2.750   0.4391   0.02484   0.01422  -0.0438   0.8908   1.0000
   3.000   0.4888   0.02531   0.01490  -0.0484   0.8753   1.0000
   3.250   0.5237   0.02590   0.01569  -0.0502   0.8583   1.0000
   3.500   0.5579   0.02649   0.01652  -0.0517   0.8416   1.0000
   3.750   0.6204   0.02560   0.01616  -0.0549   0.8105   1.0000
   4.000   0.6735   0.02374   0.01470  -0.0535   0.7676   1.0000
   4.250   0.7005   0.02312   0.01438  -0.0500   0.7344   1.0000
   4.500   0.7181   0.02078   0.01199  -0.0402   0.6566   1.0000
   4.750   0.7228   0.01975   0.01089  -0.0313   0.5609   1.0000
   5.000   0.7197   0.02048   0.01030  -0.0231   0.2896   1.0000
   5.250   0.7250   0.02359   0.01201  -0.0201   0.1538   1.0000
   5.500   0.7370   0.02574   0.01393  -0.0177   0.1276   1.0000
   5.750   0.7529   0.02773   0.01585  -0.0153   0.1167   1.0000
   6.000   0.7792   0.02953   0.01782  -0.0136   0.1097   1.0000
   6.250   0.8104   0.03209   0.02036  -0.0130   0.1002   1.0000
   6.500   0.8413   0.03465   0.02314  -0.0122   0.0951   1.0000
   6.750   0.8703   0.03762   0.02652  -0.0111   0.0958   1.0000
   7.000   0.8950   0.04091   0.03041  -0.0096   0.0985   1.0000
   7.250   0.9180   0.04488   0.03472  -0.0083   0.1021   1.0000
   7.500   0.9373   0.04882   0.03905  -0.0068   0.1043   1.0000
   7.750   0.9438   0.05164   0.04290  -0.0037   0.1100   1.0000
   8.000   0.9534   0.05605   0.04774  -0.0020   0.1143   1.0000
   8.250   0.9541   0.06037   0.05276  -0.0001   0.1236   1.0000
   8.500   0.9521   0.06547   0.05834   0.0010   0.1345   1.0000
   9.250   0.8931   0.08374   0.07735  -0.0021   0.1717   1.0000
   9.500   0.8528   0.09217   0.08571  -0.0091   0.1851   1.0000
   9.750   0.8169   0.10164   0.09492  -0.0183   0.2014   1.0000
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