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GOE 590 AIRFOIL (goe590-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 590 AIRFOIL (goe590-il)
Reynolds number: 500,000
Max Cl/Cd: 93.91 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe590-il-500000-n5.txt
Download as CSV file: xf-goe590-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 590 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3809   0.08934   0.08724  -0.0139   1.0000   0.0064
  -7.250  -0.3803   0.08653   0.08447  -0.0147   1.0000   0.0064
  -7.000  -0.3783   0.08349   0.08146  -0.0161   1.0000   0.0061
  -6.500  -0.3315   0.07322   0.07111  -0.0302   0.9454   0.0033
  -6.250  -0.2964   0.06692   0.06462  -0.0400   0.8918   0.0031
  -6.000  -0.2828   0.06322   0.06071  -0.0424   0.8420   0.0030
  -5.750  -0.2699   0.05980   0.05709  -0.0439   0.8019   0.0030
  -5.500  -0.2548   0.05610   0.05321  -0.0456   0.7738   0.0029
  -5.250  -0.2373   0.05237   0.04930  -0.0472   0.7536   0.0029
  -5.000  -0.2180   0.04852   0.04524  -0.0487   0.7382   0.0028
  -4.750  -0.1969   0.04405   0.04058  -0.0501   0.7249   0.0028
  -4.500  -0.1748   0.03999   0.03632  -0.0510   0.7129   0.0028
  -4.250  -0.1517   0.03484   0.03089  -0.0515   0.7027   0.0029
  -4.000  -0.1286   0.02923   0.02491  -0.0512   0.6936   0.0031
  -3.750  -0.1066   0.02241   0.01751  -0.0497   0.6849   0.0034
  -3.500  -0.0806   0.02324   0.01836  -0.0500   0.6712   0.0041
  -3.250  -0.0562   0.01960   0.01430  -0.0488   0.6596   0.0082
  -2.750  -0.0045   0.02098   0.01560  -0.0492   0.6274   0.0166
  -2.500   0.0202   0.01843   0.01266  -0.0481   0.6133   0.0170
  -2.250   0.0446   0.01573   0.00947  -0.0469   0.5992   0.0159
  -2.000   0.0699   0.01373   0.00700  -0.0460   0.5849   0.0151
  -1.750   0.0959   0.01236   0.00527  -0.0453   0.5720   0.0145
  -1.500   0.1218   0.01136   0.00399  -0.0447   0.5606   0.0142
  -1.250   0.1474   0.01062   0.00307  -0.0440   0.5514   0.0141
  -1.000   0.1726   0.01008   0.00233  -0.0434   0.5435   0.0142
  -0.750   0.1982   0.00972   0.00187  -0.0428   0.5359   0.0150
  -0.500   0.2241   0.00954   0.00160  -0.0424   0.5291   0.0174
  -0.250   0.2506   0.00948   0.00150  -0.0422   0.5225   0.0188
   0.000   0.2765   0.00934   0.00129  -0.0418   0.5171   0.0216
   0.250   0.3030   0.00925   0.00119  -0.0416   0.5120   0.0242
   0.500   0.3292   0.00917   0.00112  -0.0413   0.5071   0.0332
   0.750   0.3551   0.00904   0.00110  -0.0410   0.5027   0.0747
   1.000   0.3813   0.00895   0.00111  -0.0408   0.4979   0.1133
   1.250   0.4075   0.00889   0.00114  -0.0405   0.4933   0.1525
   1.500   0.4332   0.00879   0.00118  -0.0403   0.4895   0.2242
   1.750   0.4888   0.00708   0.00137  -0.0469   0.4849   0.9792
   2.000   0.5521   0.00717   0.00141  -0.0551   0.4797   1.0000
   2.250   0.5769   0.00726   0.00147  -0.0546   0.4760   1.0000
   2.500   0.6021   0.00732   0.00153  -0.0541   0.4723   1.0000
   2.750   0.6271   0.00739   0.00161  -0.0536   0.4686   1.0000
   3.000   0.6518   0.00749   0.00175  -0.0530   0.4596   1.0000
   3.250   0.6764   0.00759   0.00183  -0.0525   0.4492   1.0000
   3.500   0.7014   0.00766   0.00193  -0.0520   0.4400   1.0000
   3.750   0.7258   0.00778   0.00203  -0.0514   0.4244   1.0000
   4.000   0.7494   0.00798   0.00213  -0.0507   0.3902   1.0000
   4.250   0.7524   0.01080   0.00328  -0.0474   0.0370   1.0000
   4.500   0.7750   0.01118   0.00359  -0.0466   0.0190   1.0000
   4.750   0.7971   0.01164   0.00403  -0.0456   0.0047   1.0000
   5.000   0.8199   0.01201   0.00447  -0.0447   0.0042   1.0000
   5.250   0.8421   0.01246   0.00514  -0.0436   0.0040   1.0000
   5.500   0.8635   0.01298   0.00577  -0.0425   0.0039   1.0000
   5.750   0.8837   0.01365   0.00655  -0.0412   0.0039   1.0000
   6.000   0.9023   0.01447   0.00751  -0.0396   0.0039   1.0000
   6.250   0.9193   0.01544   0.00860  -0.0377   0.0039   1.0000
   6.500   0.9346   0.01657   0.00986  -0.0356   0.0039   1.0000
   6.750   0.9499   0.01775   0.01116  -0.0335   0.0039   1.0000
   7.000   0.9662   0.01890   0.01242  -0.0316   0.0035   1.0000
   7.250   0.9851   0.01966   0.01326  -0.0303   0.0028   1.0000
   7.500   1.0022   0.02079   0.01452  -0.0288   0.0024   1.0000
   7.750   1.0185   0.02233   0.01621  -0.0270   0.0023   1.0000
   8.000   1.0343   0.02405   0.01811  -0.0253   0.0019   1.0000
   8.250   1.0416   0.02995   0.02461  -0.0220   0.0015   1.0000
   8.500   1.0496   0.03455   0.02966  -0.0191   0.0014   1.0000
   8.750   1.0589   0.03795   0.03335  -0.0167   0.0014   1.0000
   9.000   1.0643   0.04169   0.03738  -0.0142   0.0013   1.0000
   9.250   1.0642   0.04577   0.04174  -0.0113   0.0013   1.0000
   9.500   1.0584   0.04965   0.04588  -0.0084   0.0014   1.0000
   9.750   1.0501   0.05312   0.04955  -0.0052   0.0013   1.0000
  10.000   1.0242   0.05661   0.05325  -0.0016   0.0014   1.0000
  10.250   1.0188   0.05959   0.05635  -0.0001   0.0014   1.0000
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