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NACA 65-206 (naca65206-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-206 (naca65206-il)
Reynolds number: 100,000
Max Cl/Cd: 39.43 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65206-il-100000-n5.txt
Download as CSV file: xf-naca65206-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-206                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4721   0.08704   0.08243  -0.0201   1.0000   0.0345
  -8.250  -0.4746   0.08273   0.07815  -0.0228   1.0000   0.0346
  -8.000  -0.4795   0.07847   0.07392  -0.0258   1.0000   0.0346
  -7.750  -0.4822   0.07424   0.06966  -0.0280   1.0000   0.0346
  -7.250  -0.5344   0.07749   0.07242  -0.0305   1.0000   0.0345
  -7.000  -0.5262   0.07338   0.06820  -0.0322   1.0000   0.0346
  -6.750  -0.5217   0.06692   0.06180  -0.0333   1.0000   0.0353
  -6.500  -0.5131   0.06222   0.05708  -0.0339   1.0000   0.0359
  -6.250  -0.5023   0.05798   0.05276  -0.0346   1.0000   0.0366
  -6.000  -0.4891   0.05390   0.04852  -0.0355   1.0000   0.0371
  -5.750  -0.4635   0.04925   0.04343  -0.0353   1.0000   0.0209
  -5.500  -0.4503   0.04471   0.03869  -0.0357   1.0000   0.0200
  -5.250  -0.4331   0.04076   0.03445  -0.0358   1.0000   0.0195
  -5.000  -0.4140   0.03709   0.03044  -0.0355   1.0000   0.0191
  -4.750  -0.3933   0.03371   0.02668  -0.0350   1.0000   0.0189
  -4.500  -0.3713   0.03060   0.02314  -0.0343   1.0000   0.0189
  -4.250  -0.3475   0.02825   0.02031  -0.0334   1.0000   0.0204
  -4.000  -0.3245   0.02560   0.01717  -0.0326   1.0000   0.0228
  -3.750  -0.3015   0.02317   0.01442  -0.0319   1.0000   0.0243
  -3.500  -0.2775   0.02119   0.01213  -0.0308   1.0000   0.0254
  -3.250  -0.2536   0.01949   0.01020  -0.0298   1.0000   0.0272
  -3.000  -0.2301   0.01849   0.00888  -0.0287   1.0000   0.0333
  -2.750  -0.2074   0.01706   0.00737  -0.0276   1.0000   0.0359
  -2.500  -0.1852   0.01587   0.00616  -0.0267   1.0000   0.0385
  -2.250  -0.1625   0.01509   0.00526  -0.0259   1.0000   0.0428
  -2.000  -0.1393   0.01446   0.00449  -0.0251   1.0000   0.0499
  -1.750  -0.1159   0.01388   0.00393  -0.0246   1.0000   0.0747
  -1.500  -0.1054   0.01100   0.00391  -0.0213   1.0000   0.7556
  -1.250  -0.0975   0.01078   0.00391  -0.0154   1.0000   0.9144
  -1.000  -0.0555   0.01065   0.00357  -0.0185   0.9990   1.0000
  -0.750  -0.0180   0.01075   0.00344  -0.0211   0.9918   1.0000
  -0.500   0.0194   0.01086   0.00337  -0.0236   0.9850   1.0000
  -0.250   0.0567   0.01097   0.00333  -0.0261   0.9783   1.0000
   0.000   0.0925   0.01106   0.00333  -0.0282   0.9707   1.0000
   0.250   0.1290   0.01117   0.00339  -0.0304   0.9638   1.0000
   0.500   0.1659   0.01127   0.00347  -0.0327   0.9568   1.0000
   0.750   0.2011   0.01137   0.00360  -0.0346   0.9491   1.0000
   1.000   0.2382   0.01147   0.00374  -0.0368   0.9424   1.0000
   1.250   0.2710   0.01157   0.00391  -0.0381   0.9333   1.0000
   1.500   0.3056   0.01167   0.00411  -0.0396   0.9251   1.0000
   1.750   0.3401   0.01176   0.00441  -0.0411   0.9166   1.0000
   2.000   0.3715   0.01187   0.00469  -0.0419   0.9060   1.0000
   2.250   0.4062   0.01171   0.00472  -0.0423   0.8813   1.0000
   2.500   0.4343   0.01125   0.00426  -0.0397   0.8093   1.0000
   2.750   0.4511   0.01144   0.00376  -0.0347   0.6115   1.0000
   3.000   0.4550   0.01489   0.00438  -0.0311   0.0705   1.0000
   3.250   0.4784   0.01583   0.00537  -0.0303   0.0514   1.0000
   3.500   0.5026   0.01664   0.00638  -0.0295   0.0453   1.0000
   3.750   0.5255   0.01769   0.00757  -0.0286   0.0416   1.0000
   4.000   0.5480   0.01894   0.00890  -0.0277   0.0357   1.0000
   4.250   0.5722   0.02022   0.01030  -0.0269   0.0308   1.0000
   4.500   0.5970   0.02205   0.01220  -0.0262   0.0282   1.0000
   4.750   0.6226   0.02492   0.01524  -0.0256   0.0265   1.0000
   5.000   0.6492   0.02664   0.01752  -0.0247   0.0231   1.0000
   5.250   0.6748   0.02912   0.02049  -0.0236   0.0206   1.0000
   5.500   0.6986   0.03225   0.02414  -0.0224   0.0199   1.0000
   5.750   0.7203   0.03576   0.02819  -0.0211   0.0195   1.0000
   6.000   0.7398   0.03958   0.03253  -0.0198   0.0195   1.0000
   6.250   0.7570   0.04362   0.03704  -0.0185   0.0194   1.0000
   6.500   0.7723   0.04735   0.04116  -0.0176   0.0181   1.0000
   6.750   0.7850   0.05009   0.04409  -0.0173   0.0157   1.0000
   7.000   0.7918   0.05427   0.04849  -0.0171   0.0146   1.0000
   7.250   0.7972   0.05914   0.05365  -0.0166   0.0143   1.0000
   7.500   0.8059   0.06314   0.05794  -0.0161   0.0147   1.0000
   7.750   0.8110   0.06826   0.06340  -0.0160   0.0157   1.0000
   8.000   0.8081   0.07401   0.06936  -0.0170   0.0167   1.0000
   8.250   0.8023   0.07921   0.07469  -0.0186   0.0173   1.0000
   8.500   0.7919   0.08424   0.07977  -0.0206   0.0179   1.0000
   8.750   0.7830   0.08991   0.08546  -0.0250   0.0184   1.0000
   9.000   0.7775   0.09613   0.09163  -0.0302   0.0191   1.0000
   9.250   0.7744   0.10178   0.09725  -0.0340   0.0199   1.0000
   9.500   0.7723   0.10723   0.10266  -0.0372   0.0207   1.0000
   9.750   0.7715   0.11239   0.10778  -0.0398   0.0220   1.0000
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