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GOE 602 MOD. AIRFOIL (goe602m-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 602 MOD. AIRFOIL (goe602m-il)
Reynolds number: 50,000
Max Cl/Cd: 39.22 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe602m-il-50000.txt
Download as CSV file: xf-goe602m-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 602 MOD. 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2822   0.11133   0.10491  -0.0303   1.0000   0.2092
  -9.250  -0.2703   0.10700   0.10060  -0.0291   1.0000   0.2165
  -9.000  -0.2845   0.10602   0.09972  -0.0289   1.0000   0.2236
  -8.750  -0.2723   0.10183   0.09556  -0.0274   1.0000   0.2346
  -8.500  -0.2757   0.09916   0.09297  -0.0265   1.0000   0.2420
  -8.250  -0.2843   0.09758   0.09149  -0.0253   1.0000   0.2518
  -8.000  -0.2745   0.09365   0.08759  -0.0237   1.0000   0.2613
  -7.750  -0.3010   0.09362   0.08773  -0.0224   1.0000   0.2673
  -7.500  -0.2850   0.08906   0.08316  -0.0206   1.0000   0.2792
  -7.250  -0.2872   0.08619   0.08037  -0.0188   1.0000   0.2868
  -7.000  -0.3628   0.09288   0.08664  -0.0172   1.0000   0.2868
  -6.750  -0.3845   0.09261   0.08654  -0.0141   1.0000   0.2955
  -6.500  -0.3776   0.08922   0.08319  -0.0118   1.0000   0.3070
  -6.000  -0.4069   0.08634   0.08059  -0.0075   1.0000   0.3269
  -5.750  -0.4168   0.08479   0.07912  -0.0059   1.0000   0.3405
  -5.500  -0.4178   0.08222   0.07662  -0.0035   1.0000   0.3551
  -5.250  -0.4181   0.07951   0.07396  -0.0009   1.0000   0.3705
  -5.000  -0.4066   0.07612   0.07059   0.0036   1.0000   0.3911
  -4.750  -0.4186   0.07480   0.06937   0.0054   1.0000   0.4135
  -4.250  -0.3459   0.04981   0.04314  -0.0448   1.0000   0.1785
  -4.000  -0.3070   0.04180   0.03402  -0.0525   1.0000   0.1516
  -3.750  -0.2808   0.03806   0.02981  -0.0539   1.0000   0.1466
  -3.500  -0.2534   0.03507   0.02623  -0.0550   1.0000   0.1472
  -3.250  -0.2264   0.03277   0.02330  -0.0555   1.0000   0.1510
  -3.000  -0.1998   0.03080   0.02075  -0.0555   1.0000   0.1527
  -2.750  -0.1759   0.02916   0.01892  -0.0551   1.0000   0.1568
  -2.500  -0.1521   0.02808   0.01755  -0.0546   1.0000   0.1672
  -2.250  -0.1298   0.02709   0.01651  -0.0539   1.0000   0.1794
  -2.000  -0.1073   0.02622   0.01559  -0.0530   1.0000   0.1934
  -1.750  -0.0826   0.02554   0.01497  -0.0526   1.0000   0.2212
  -1.500  -0.0556   0.02442   0.01458  -0.0525   1.0000   0.3490
  -1.250  -0.0390   0.02324   0.01464  -0.0494   1.0000   0.6190
  -1.000  -0.0287   0.02184   0.01434  -0.0453   1.0000   1.0000
  -0.750  -0.0020   0.02238   0.01423  -0.0469   1.0000   1.0000
  -0.500   0.0197   0.02297   0.01439  -0.0473   1.0000   1.0000
  -0.250   0.0397   0.02362   0.01469  -0.0475   1.0000   1.0000
   0.000   0.0588   0.02432   0.01509  -0.0475   1.0000   1.0000
   0.250   0.0773   0.02508   0.01560  -0.0475   1.0000   1.0000
   0.500   0.1204   0.02638   0.01661  -0.0521   0.9884   1.0000
   0.750   0.1707   0.02776   0.01771  -0.0578   0.9728   1.0000
   1.000   0.2192   0.02901   0.01874  -0.0629   0.9573   1.0000
   1.250   0.2611   0.03002   0.01959  -0.0668   0.9409   1.0000
   1.500   0.3003   0.03094   0.02039  -0.0700   0.9243   1.0000
   1.750   0.3394   0.03184   0.02119  -0.0730   0.9079   1.0000
   2.000   0.3779   0.03267   0.02196  -0.0757   0.8918   1.0000
   2.250   0.4166   0.03346   0.02270  -0.0784   0.8757   1.0000
   2.500   0.4552   0.03417   0.02339  -0.0808   0.8600   1.0000
   2.750   0.4940   0.03480   0.02403  -0.0830   0.8445   1.0000
   3.000   0.5331   0.03535   0.02461  -0.0852   0.8292   1.0000
   3.250   0.5636   0.03598   0.02527  -0.0860   0.8129   1.0000
   3.500   0.5922   0.03661   0.02595  -0.0864   0.7960   1.0000
   3.750   0.6242   0.03713   0.02657  -0.0872   0.7798   1.0000
   4.000   0.6579   0.03756   0.02708  -0.0880   0.7641   1.0000
   4.250   0.6931   0.03785   0.02749  -0.0888   0.7486   1.0000
   4.500   0.7295   0.03802   0.02779  -0.0895   0.7333   1.0000
   4.750   0.7667   0.03806   0.02802  -0.0902   0.7183   1.0000
   5.000   0.8062   0.03792   0.02806  -0.0909   0.7034   1.0000
   5.250   0.8452   0.03772   0.02806  -0.0914   0.6884   1.0000
   5.500   0.8851   0.03734   0.02793  -0.0917   0.6732   1.0000
   5.750   0.9274   0.03676   0.02758  -0.0920   0.6577   1.0000
   6.000   0.9510   0.03725   0.02826  -0.0906   0.6392   1.0000
   6.250   0.9868   0.03668   0.02795  -0.0897   0.6188   1.0000
   6.500   1.0347   0.03480   0.02630  -0.0890   0.5943   1.0000
   6.750   1.0786   0.03326   0.02493  -0.0881   0.5681   1.0000
   7.000   1.1098   0.03233   0.02415  -0.0860   0.5379   1.0000
   7.250   1.1408   0.03046   0.02218  -0.0829   0.4977   1.0000
   7.500   1.1553   0.03023   0.02202  -0.0793   0.4634   1.0000
   7.750   1.1702   0.03003   0.02184  -0.0758   0.4296   1.0000
   8.000   1.1782   0.03004   0.02188  -0.0716   0.3937   1.0000
   8.250   1.1797   0.03030   0.02217  -0.0667   0.3534   1.0000
   8.500   1.1702   0.03105   0.02279  -0.0607   0.3001   1.0000
   8.750   1.1558   0.03264   0.02398  -0.0546   0.2351   1.0000
   9.000   1.1377   0.03551   0.02615  -0.0491   0.1725   1.0000
   9.250   1.1280   0.03872   0.02884  -0.0451   0.1354   1.0000
   9.500   1.1294   0.04155   0.03135  -0.0423   0.1171   1.0000
   9.750   1.1469   0.04405   0.03378  -0.0405   0.1024   1.0000
  10.000   1.1771   0.04661   0.03625  -0.0400   0.0902   1.0000
  10.250   1.2156   0.04954   0.03944  -0.0405   0.0826   1.0000
  10.500   1.2696   0.05461   0.04469  -0.0435   0.0783   1.0000
  10.750   1.2816   0.05830   0.04888  -0.0417   0.0774   1.0000
  11.000   1.2842   0.06193   0.05297  -0.0392   0.0767   1.0000
  11.250   1.2782   0.06542   0.05686  -0.0362   0.0761   1.0000
  11.500   1.2681   0.06901   0.06080  -0.0333   0.0759   1.0000
  11.750   1.2538   0.07281   0.06491  -0.0307   0.0759   1.0000
  12.000   1.2366   0.07692   0.06931  -0.0287   0.0761   1.0000
  12.250   1.2166   0.08136   0.07401  -0.0276   0.0764   1.0000
  12.500   1.1967   0.08635   0.07923  -0.0274   0.0770   1.0000
  12.750   1.1752   0.09184   0.08491  -0.0281   0.0775   1.0000
  13.000   1.1546   0.09787   0.09110  -0.0297   0.0781   1.0000
  13.250   1.1359   0.10436   0.09771  -0.0319   0.0786   1.0000
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