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GOE 504 AIRFOIL (goe504-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 504 AIRFOIL (goe504-il)
Reynolds number: 200,000
Max Cl/Cd: 66.15 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe504-il-200000.txt
Download as CSV file: xf-goe504-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 504 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.0314   0.05505   0.05184  -0.1300   0.9270   0.0816
  -9.750  -0.3253   0.04185   0.03676  -0.1359   0.9094   0.0491
  -9.500  -0.3194   0.03895   0.03370  -0.1339   0.8985   0.0483
  -9.250  -0.3040   0.03528   0.02966  -0.1341   0.8938   0.0478
  -9.000  -0.3008   0.03359   0.02766  -0.1308   0.8823   0.0481
  -8.750  -0.2846   0.03165   0.02534  -0.1297   0.8758   0.0486
  -8.500  -0.2717   0.03020   0.02357  -0.1275   0.8667   0.0488
  -8.250  -0.2464   0.02773   0.02080  -0.1278   0.8619   0.0491
  -8.000  -0.2313   0.02593   0.01884  -0.1258   0.8524   0.0496
  -7.750  -0.2010   0.02429   0.01712  -0.1267   0.8475   0.0511
  -7.500  -0.1833   0.02350   0.01625  -0.1250   0.8382   0.0525
  -7.250  -0.1542   0.02238   0.01499  -0.1252   0.8325   0.0537
  -7.000  -0.1341   0.02157   0.01408  -0.1238   0.8240   0.0547
  -6.750  -0.1069   0.02067   0.01306  -0.1236   0.8176   0.0559
  -6.500  -0.0853   0.02014   0.01242  -0.1224   0.8097   0.0574
  -6.250  -0.0627   0.01920   0.01145  -0.1215   0.8027   0.0592
  -6.000  -0.0417   0.01860   0.01084  -0.1203   0.7955   0.0610
  -5.750  -0.0205   0.01812   0.01030  -0.1191   0.7879   0.0630
  -5.500   0.0035   0.01766   0.00975  -0.1183   0.7814   0.0655
  -5.250   0.0224   0.01729   0.00933  -0.1166   0.7732   0.0689
  -5.000   0.0490   0.01681   0.00876  -0.1163   0.7677   0.0745
  -4.750   0.0660   0.01653   0.00847  -0.1142   0.7591   0.0812
  -4.500   0.0902   0.01590   0.00785  -0.1136   0.7530   0.1056
  -4.250   0.1037   0.01515   0.00771  -0.1113   0.7453   0.2296
  -4.000   0.1301   0.01515   0.00765  -0.1109   0.7387   0.2712
  -3.750   0.1544   0.01520   0.00765  -0.1101   0.7320   0.2936
  -3.500   0.1780   0.01522   0.00761  -0.1092   0.7246   0.3116
  -3.250   0.2076   0.01519   0.00745  -0.1095   0.7192   0.3262
  -3.000   0.2273   0.01521   0.00746  -0.1079   0.7111   0.3374
  -2.750   0.2552   0.01514   0.00732  -0.1078   0.7052   0.3530
  -2.500   0.2771   0.01512   0.00731  -0.1067   0.6981   0.3653
  -2.250   0.3027   0.01505   0.00719  -0.1062   0.6915   0.3779
  -2.000   0.3297   0.01502   0.00708  -0.1061   0.6857   0.3920
  -1.750   0.3507   0.01496   0.00707  -0.1048   0.6783   0.4076
  -1.500   0.3787   0.01483   0.00693  -0.1048   0.6728   0.4273
  -1.250   0.3985   0.01477   0.00697  -0.1033   0.6657   0.4471
  -1.000   0.4229   0.01462   0.00689  -0.1026   0.6594   0.4718
  -0.750   0.4477   0.01446   0.00681  -0.1020   0.6539   0.5026
  -0.500   0.4649   0.01425   0.00685  -0.1000   0.6467   0.5500
  -0.250   0.4855   0.01384   0.00682  -0.0983   0.6414   0.6553
   0.000   0.5155   0.01359   0.00711  -0.0981   0.6348   0.8200
   0.250   0.5888   0.01378   0.00730  -0.1068   0.6277   0.9102
   0.500   0.6440   0.01403   0.00742  -0.1121   0.6215   0.9415
   0.750   0.6925   0.01426   0.00757  -0.1163   0.6139   0.9610
   1.000   0.7471   0.01441   0.00752  -0.1217   0.6081   0.9746
   1.250   0.7970   0.01457   0.00766  -0.1265   0.6000   0.9880
   1.500   0.8539   0.01461   0.00754  -0.1328   0.5936   0.9980
   1.750   0.8764   0.01472   0.00764  -0.1322   0.5868   1.0000
   2.000   0.8934   0.01480   0.00765  -0.1304   0.5806   1.0000
   2.250   0.9135   0.01491   0.00765  -0.1292   0.5751   1.0000
   2.500   0.9258   0.01506   0.00781  -0.1265   0.5682   1.0000
   2.750   0.9463   0.01517   0.00782  -0.1253   0.5626   1.0000
   3.000   0.9615   0.01535   0.00799  -0.1230   0.5564   1.0000
   3.250   0.9776   0.01550   0.00810  -0.1210   0.5500   1.0000
   3.500   1.0016   0.01564   0.00812  -0.1204   0.5446   1.0000
   3.750   1.0113   0.01585   0.00838  -0.1171   0.5377   1.0000
   4.000   1.0311   0.01599   0.00846  -0.1157   0.5319   1.0000
   4.250   1.0484   0.01621   0.00864  -0.1139   0.5259   1.0000
   4.500   1.0627   0.01639   0.00883  -0.1114   0.5192   1.0000
   4.750   1.0875   0.01657   0.00889  -0.1110   0.5138   1.0000
   5.000   1.0967   0.01681   0.00920  -0.1076   0.5071   1.0000
   5.250   1.1151   0.01700   0.00934  -0.1060   0.5011   1.0000
   5.500   1.1346   0.01724   0.00955  -0.1046   0.4953   1.0000
   5.750   1.1460   0.01748   0.00983  -0.1016   0.4887   1.0000
   6.000   1.1689   0.01767   0.00994  -0.1009   0.4830   1.0000
   6.250   1.1784   0.01796   0.01028  -0.0976   0.4765   1.0000
   6.500   1.1938   0.01818   0.01050  -0.0955   0.4703   1.0000
   6.750   1.2155   0.01846   0.01072  -0.0946   0.4648   1.0000
   7.000   1.2217   0.01876   0.01110  -0.0907   0.4584   1.0000
   7.250   1.2399   0.01899   0.01128  -0.0891   0.4527   1.0000
   7.500   1.2502   0.01932   0.01164  -0.0861   0.4467   1.0000
   7.750   1.2588   0.01960   0.01195  -0.0828   0.4404   1.0000
   8.000   1.2845   0.01988   0.01214  -0.0828   0.4348   1.0000
   8.250   1.2846   0.02030   0.01267  -0.0781   0.4284   1.0000
   8.500   1.2992   0.02058   0.01295  -0.0760   0.4221   1.0000
   8.750   1.3083   0.02100   0.01339  -0.0731   0.4153   1.0000
   9.000   1.3155   0.02137   0.01378  -0.0700   0.4080   1.0000
   9.250   1.3239   0.02180   0.01420  -0.0672   0.4003   1.0000
   9.500   1.3295   0.02230   0.01473  -0.0640   0.3927   1.0000
   9.750   1.3398   0.02281   0.01524  -0.0617   0.3855   1.0000
  10.000   1.3457   0.02345   0.01595  -0.0589   0.3785   1.0000
  10.250   1.3549   0.02403   0.01651  -0.0566   0.3709   1.0000
  10.500   1.3573   0.02486   0.01741  -0.0536   0.3630   1.0000
  10.750   1.3677   0.02554   0.01806  -0.0517   0.3561   1.0000
  11.000   1.3717   0.02649   0.01913  -0.0492   0.3491   1.0000
  11.250   1.3821   0.02724   0.01982  -0.0475   0.3420   1.0000
  11.500   1.3822   0.02847   0.02119  -0.0449   0.3343   1.0000
  11.750   1.3868   0.02955   0.02223  -0.0428   0.3260   1.0000
  12.000   1.3865   0.03099   0.02377  -0.0406   0.3174   1.0000
  12.250   1.3895   0.03235   0.02516  -0.0387   0.3093   1.0000
  12.500   1.3903   0.03393   0.02680  -0.0369   0.3007   1.0000
  12.750   1.3909   0.03566   0.02859  -0.0352   0.2919   1.0000
  13.000   1.3889   0.03762   0.03053  -0.0334   0.2820   1.0000
  13.250   1.3864   0.03983   0.03282  -0.0320   0.2717   1.0000
  13.500   1.3823   0.04227   0.03531  -0.0306   0.2602   1.0000
  13.750   1.3760   0.04503   0.03808  -0.0293   0.2475   1.0000
  14.000   1.3682   0.04806   0.04111  -0.0282   0.2341   1.0000
  14.250   1.3568   0.05159   0.04463  -0.0271   0.2175   1.0000
  14.500   1.3484   0.05496   0.04799  -0.0263   0.2035   1.0000
  14.750   1.3350   0.05897   0.05196  -0.0256   0.1859   1.0000
  15.000   1.3192   0.06336   0.05629  -0.0251   0.1662   1.0000
  15.250   1.2959   0.06875   0.06155  -0.0247   0.1405   1.0000
  15.500   1.2700   0.07462   0.06729  -0.0246   0.1158   1.0000
  15.750   1.2423   0.08088   0.07343  -0.0247   0.0897   1.0000
  16.000   1.2140   0.08747   0.07992  -0.0251   0.0600   1.0000
  16.250   1.1904   0.09364   0.08604  -0.0257   0.0445   1.0000
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