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GOE 596 AIRFOIL (goe596-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 596 AIRFOIL (goe596-il)
Reynolds number: 100,000
Max Cl/Cd: 56.55 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe596-il-100000.txt
Download as CSV file: xf-goe596-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 596 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3438   0.10358   0.09848  -0.0341   1.0000   0.0891
  -8.750  -0.3637   0.10305   0.09810  -0.0371   1.0000   0.0900
  -8.500  -0.3839   0.10196   0.09714  -0.0391   1.0000   0.0903
  -8.250  -0.3402   0.09399   0.08907  -0.0337   1.0000   0.0934
  -8.000  -0.3347   0.09133   0.08645  -0.0325   1.0000   0.0960
  -7.750  -0.3376   0.08915   0.08435  -0.0317   1.0000   0.0986
  -7.500  -0.3483   0.08740   0.08271  -0.0305   1.0000   0.1007
  -7.250  -0.3648   0.08588   0.08131  -0.0299   1.0000   0.1027
  -7.000  -0.3894   0.08487   0.08037  -0.0333   1.0000   0.1047
  -6.750  -0.4075   0.08295   0.07840  -0.0368   1.0000   0.1057
  -6.500  -0.3973   0.07869   0.07432  -0.0295   1.0000   0.1076
  -6.250  -0.3949   0.07669   0.07239  -0.0255   1.0000   0.1104
  -6.000  -0.3974   0.07467   0.07040  -0.0241   1.0000   0.1139
  -5.750  -0.4054   0.07239   0.06783  -0.0329   1.0000   0.1213
  -5.500  -0.4031   0.06888   0.06453  -0.0282   1.0000   0.1229
  -5.250  -0.4012   0.06685   0.06258  -0.0250   1.0000   0.1253
  -5.000  -0.3634   0.06221   0.05765  -0.0352   0.9924   0.1381
  -4.750  -0.3305   0.05898   0.05448  -0.0374   0.9850   0.1456
  -4.500  -0.2933   0.05513   0.05050  -0.0434   0.9753   0.1591
  -4.250  -0.2524   0.05182   0.04688  -0.0510   0.9648   0.1848
  -4.000  -0.2150   0.04854   0.04360  -0.0546   0.9573   0.2023
  -3.750  -0.1832   0.04587   0.04090  -0.0570   0.9462   0.2212
  -3.500  -0.1481   0.04329   0.03822  -0.0602   0.9363   0.2510
  -3.250  -0.1120   0.04084   0.03578  -0.0626   0.9281   0.2850
  -2.750   0.0095   0.02963   0.02193  -0.0762   0.9122   0.1188
  -2.500   0.0495   0.02787   0.01947  -0.0773   0.9014   0.1055
  -2.250   0.0969   0.02526   0.01665  -0.0807   0.8963   0.1026
  -2.000   0.1323   0.02409   0.01522  -0.0816   0.8847   0.1035
  -1.750   0.1794   0.02267   0.01354  -0.0844   0.8792   0.1043
  -1.500   0.2113   0.02172   0.01247  -0.0846   0.8666   0.1048
  -1.250   0.2445   0.02073   0.01144  -0.0849   0.8553   0.1063
  -1.000   0.2834   0.01952   0.01033  -0.0863   0.8478   0.1113
  -0.750   0.3108   0.01899   0.00979  -0.0856   0.8344   0.1193
  -0.500   0.3374   0.01835   0.00923  -0.0847   0.8216   0.1284
  -0.250   0.3660   0.01779   0.00870  -0.0842   0.8101   0.1463
   0.000   0.4467   0.01471   0.00784  -0.0933   0.8025   1.0000
   0.250   0.4704   0.01484   0.00776  -0.0921   0.7896   1.0000
   0.500   0.4950   0.01497   0.00770  -0.0911   0.7777   1.0000
   0.750   0.5220   0.01502   0.00757  -0.0904   0.7675   1.0000
   1.000   0.5456   0.01519   0.00762  -0.0893   0.7555   1.0000
   1.250   0.5690   0.01540   0.00772  -0.0882   0.7437   1.0000
   1.500   0.5943   0.01555   0.00776  -0.0874   0.7333   1.0000
   1.750   0.6203   0.01567   0.00776  -0.0866   0.7231   1.0000
   2.000   0.6434   0.01592   0.00797  -0.0856   0.7114   1.0000
   2.250   0.6682   0.01614   0.00811  -0.0847   0.7010   1.0000
   2.500   0.6953   0.01627   0.00813  -0.0841   0.6914   1.0000
   2.750   0.7183   0.01657   0.00842  -0.0831   0.6795   1.0000
   3.000   0.7425   0.01686   0.00868  -0.0822   0.6686   1.0000
   3.250   0.7694   0.01707   0.00880  -0.0817   0.6589   1.0000
   3.500   0.7932   0.01739   0.00913  -0.0807   0.6471   1.0000
   3.750   0.8166   0.01777   0.00951  -0.0798   0.6354   1.0000
   4.000   0.8418   0.01811   0.00983  -0.0791   0.6246   1.0000
   4.250   0.8683   0.01838   0.01002  -0.0784   0.6133   1.0000
   4.500   0.8910   0.01872   0.01040  -0.0773   0.5995   1.0000
   4.750   0.9141   0.01903   0.01072  -0.0761   0.5855   1.0000
   5.000   0.9374   0.01936   0.01106  -0.0751   0.5721   1.0000
   5.250   0.9615   0.01972   0.01145  -0.0742   0.5601   1.0000
   5.500   0.9883   0.02002   0.01171  -0.0736   0.5495   1.0000
   5.750   1.0100   0.02039   0.01218  -0.0724   0.5361   1.0000
   6.000   1.0326   0.02060   0.01242  -0.0711   0.5214   1.0000
   6.250   1.0555   0.02063   0.01247  -0.0698   0.5053   1.0000
   6.500   1.0781   0.02059   0.01241  -0.0684   0.4884   1.0000
   6.750   1.1001   0.02064   0.01249  -0.0669   0.4722   1.0000
   7.000   1.1217   0.02068   0.01258  -0.0655   0.4558   1.0000
   7.250   1.1407   0.02079   0.01279  -0.0637   0.4380   1.0000
   7.500   1.1592   0.02088   0.01299  -0.0618   0.4188   1.0000
   7.750   1.1774   0.02095   0.01311  -0.0599   0.3983   1.0000
   8.000   1.1927   0.02109   0.01333  -0.0575   0.3728   1.0000
   8.250   1.2059   0.02139   0.01362  -0.0548   0.3429   1.0000
   8.500   1.2144   0.02194   0.01409  -0.0516   0.3019   1.0000
   8.750   1.2132   0.02312   0.01495  -0.0471   0.2252   1.0000
   9.000   1.2009   0.02537   0.01652  -0.0418   0.1553   1.0000
   9.250   1.1944   0.02728   0.01815  -0.0372   0.1265   1.0000
   9.500   1.1932   0.02895   0.01971  -0.0335   0.1124   1.0000
   9.750   1.1924   0.03067   0.02136  -0.0303   0.1046   1.0000
  10.000   1.1957   0.03227   0.02300  -0.0277   0.0978   1.0000
  10.250   1.1972   0.03414   0.02478  -0.0252   0.0927   1.0000
  10.500   1.2054   0.03572   0.02644  -0.0233   0.0879   1.0000
  10.750   1.2155   0.03741   0.02808  -0.0216   0.0838   1.0000
  11.000   1.2343   0.03914   0.02976  -0.0204   0.0796   1.0000
  11.250   1.2514   0.04078   0.03152  -0.0193   0.0755   1.0000
  11.500   1.2827   0.04271   0.03336  -0.0193   0.0718   1.0000
  11.750   1.3143   0.04539   0.03616  -0.0197   0.0684   1.0000
  12.000   1.3278   0.04760   0.03864  -0.0184   0.0662   1.0000
  12.250   1.3446   0.05026   0.04157  -0.0175   0.0645   1.0000
  12.500   1.3581   0.05302   0.04453  -0.0165   0.0629   1.0000
  12.750   1.3694   0.05598   0.04763  -0.0157   0.0610   1.0000
  13.000   1.3892   0.06180   0.05360  -0.0165   0.0591   1.0000
  13.250   1.3776   0.06463   0.05675  -0.0137   0.0589   1.0000
  13.500   1.3655   0.06798   0.06040  -0.0115   0.0589   1.0000
  13.750   1.3528   0.07180   0.06449  -0.0099   0.0589   1.0000
  14.000   1.3387   0.07604   0.06899  -0.0088   0.0590   1.0000
  14.250   1.3222   0.08055   0.07378  -0.0083   0.0592   1.0000
  14.500   1.3004   0.08436   0.07784  -0.0082   0.0594   1.0000
  14.750   1.2746   0.08884   0.08259  -0.0091   0.0598   1.0000
  15.000   1.2374   0.09494   0.08902  -0.0119   0.0606   1.0000
  15.250   1.1550   0.10870   0.10326  -0.0216   0.0631   1.0000
  15.500   1.0842   0.12674   0.12153  -0.0338   0.0671   1.0000
  15.750   1.0545   0.13892   0.13376  -0.0408   0.0690   1.0000
  16.000   1.0394   0.14869   0.14356  -0.0457   0.0705   1.0000
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