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GOE 416A AIRFOIL (goe416a-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 416A AIRFOIL (goe416a-il)
Reynolds number: 50,000
Max Cl/Cd: 31.06 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe416a-il-50000.txt
Download as CSV file: xf-goe416a-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 416A 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6126   0.08710   0.08070  -0.0170   1.0000   0.1464
  -8.750  -0.6619   0.07654   0.07022  -0.0297   1.0000   0.1429
  -8.500  -0.6703   0.06962   0.06319  -0.0336   1.0000   0.1327
  -8.250  -0.6888   0.06276   0.05590  -0.0381   1.0000   0.1249
  -8.000  -0.6955   0.05652   0.04903  -0.0405   1.0000   0.1159
  -7.750  -0.6816   0.05201   0.04420  -0.0406   1.0000   0.1093
  -7.500  -0.6732   0.04810   0.03915  -0.0407   1.0000   0.1010
  -7.250  -0.6516   0.04401   0.03494  -0.0401   1.0000   0.0978
  -7.000  -0.6302   0.04057   0.03114  -0.0394   1.0000   0.0943
  -6.750  -0.6072   0.03765   0.02771  -0.0385   1.0000   0.0913
  -6.500  -0.5830   0.03520   0.02495  -0.0375   1.0000   0.0914
  -6.250  -0.5578   0.03306   0.02261  -0.0364   1.0000   0.0932
  -6.000  -0.5319   0.03122   0.02066  -0.0349   1.0000   0.0947
  -5.750  -0.5067   0.02970   0.01908  -0.0329   1.0000   0.0958
  -5.500  -0.4842   0.02842   0.01774  -0.0308   1.0000   0.0978
  -5.250  -0.4638   0.02728   0.01649  -0.0288   1.0000   0.1007
  -5.000  -0.4468   0.02575   0.01508  -0.0272   1.0000   0.1066
  -4.750  -0.4281   0.02426   0.01358  -0.0263   1.0000   0.1183
  -4.500  -0.4082   0.02236   0.01196  -0.0260   1.0000   0.1447
  -4.250  -0.3954   0.02086   0.01245  -0.0238   1.0000   0.4678
  -4.000  -0.3827   0.02282   0.01445  -0.0172   1.0000   0.5587
  -3.750  -0.3758   0.02449   0.01625  -0.0087   1.0000   0.6192
  -3.500  -0.3691   0.02536   0.01716  -0.0008   1.0000   0.6615
  -3.250  -0.3626   0.02577   0.01753   0.0065   1.0000   0.6978
  -3.000  -0.3595   0.02604   0.01782   0.0146   1.0000   0.7382
  -2.750  -0.3550   0.02607   0.01784   0.0225   1.0000   0.7725
  -2.500  -0.3416   0.02553   0.01717   0.0254   1.0000   0.7932
  -2.250  -0.3237   0.02487   0.01635   0.0265   1.0000   0.8052
  -2.000  -0.3052   0.02425   0.01557   0.0273   1.0000   0.8167
  -1.750  -0.2861   0.02367   0.01486   0.0275   1.0000   0.8277
  -1.500  -0.2660   0.02317   0.01423   0.0273   1.0000   0.8382
  -1.250  -0.2453   0.02275   0.01372   0.0273   1.0000   0.8475
  -1.000  -0.2235   0.02240   0.01326   0.0267   1.0000   0.8569
  -0.750  -0.2012   0.02215   0.01292   0.0257   1.0000   0.8665
  -0.500  -0.1792   0.02196   0.01269   0.0250   1.0000   0.8759
  -0.250  -0.1564   0.02186   0.01255   0.0239   1.0000   0.8861
   0.000  -0.1333   0.02186   0.01250   0.0225   1.0000   0.8973
   0.250  -0.1097   0.02194   0.01257   0.0210   1.0000   0.9095
   0.500  -0.0845   0.02212   0.01278   0.0190   1.0000   0.9237
   0.750  -0.0512   0.02250   0.01320   0.0152   0.9974   0.9403
   1.000   0.0218   0.02334   0.01404   0.0041   0.9778   0.9568
   1.250   0.0984   0.02413   0.01487  -0.0075   0.9579   0.9758
   1.500   0.1686   0.02474   0.01555  -0.0178   0.9369   1.0000
   1.750   0.2198   0.02519   0.01605  -0.0247   0.9158   1.0000
   2.000   0.2782   0.02555   0.01650  -0.0321   0.8948   1.0000
   2.250   0.3401   0.02556   0.01661  -0.0389   0.8700   1.0000
   2.500   0.3894   0.02542   0.01658  -0.0430   0.8437   1.0000
   2.750   0.4355   0.02530   0.01654  -0.0463   0.8212   1.0000
   3.000   0.4740   0.02541   0.01670  -0.0485   0.7998   1.0000
   3.250   0.5143   0.02537   0.01675  -0.0502   0.7805   1.0000
   3.500   0.5445   0.02568   0.01712  -0.0507   0.7579   1.0000
   3.750   0.5798   0.02560   0.01710  -0.0508   0.7382   1.0000
   4.000   0.6067   0.02598   0.01754  -0.0503   0.7143   1.0000
   4.250   0.6364   0.02608   0.01774  -0.0493   0.6917   1.0000
   4.500   0.6644   0.02627   0.01799  -0.0480   0.6674   1.0000
   4.750   0.6900   0.02668   0.01848  -0.0466   0.6406   1.0000
   5.000   0.7156   0.02695   0.01882  -0.0448   0.6118   1.0000
   5.250   0.7409   0.02705   0.01893  -0.0426   0.5809   1.0000
   5.500   0.7662   0.02714   0.01900  -0.0404   0.5499   1.0000
   5.750   0.7906   0.02749   0.01938  -0.0387   0.5197   1.0000
   6.000   0.8137   0.02791   0.01991  -0.0370   0.4876   1.0000
   6.250   0.8375   0.02789   0.01982  -0.0347   0.4513   1.0000
   6.500   0.8587   0.02801   0.01984  -0.0323   0.4090   1.0000
   6.750   0.8790   0.02830   0.01993  -0.0298   0.3616   1.0000
   7.000   0.8954   0.02883   0.02026  -0.0272   0.3057   1.0000
   7.250   0.9118   0.03036   0.02130  -0.0248   0.2490   1.0000
   7.500   0.9284   0.03279   0.02351  -0.0230   0.2033   1.0000
   7.750   0.9459   0.03509   0.02584  -0.0214   0.1712   1.0000
   8.000   0.9645   0.03720   0.02789  -0.0200   0.1476   1.0000
   8.250   0.9833   0.03979   0.03064  -0.0187   0.1305   1.0000
   8.500   1.0011   0.04287   0.03392  -0.0174   0.1185   1.0000
   8.750   1.0193   0.04625   0.03738  -0.0165   0.1094   1.0000
   9.000   1.0278   0.05056   0.04238  -0.0147   0.1061   1.0000
   9.250   1.0340   0.05471   0.04703  -0.0132   0.1026   1.0000
   9.500   1.0492   0.05871   0.05094  -0.0126   0.0972   1.0000
   9.750   1.0423   0.06328   0.05607  -0.0109   0.0964   1.0000
  10.000   1.0322   0.06814   0.06134  -0.0096   0.0962   1.0000
  10.250   1.0198   0.07316   0.06665  -0.0088   0.0966   1.0000
  10.500   1.0067   0.07829   0.07198  -0.0083   0.0971   1.0000
  10.750   0.9217   0.08824   0.08230  -0.0140   0.1080   1.0000
  11.000   0.9039   0.09560   0.08967  -0.0178   0.1098   1.0000
  11.250   0.8931   0.10274   0.09680  -0.0209   0.1108   1.0000
  11.500   0.8141   0.12665   0.12046  -0.0420   0.1347   1.0000
  11.750   0.8010   0.13623   0.12995  -0.0474   0.1485   1.0000
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