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NACA 64-206 (naca64206-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-206 (naca64206-il)
Reynolds number: 100,000
Max Cl/Cd: 40.99 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64206-il-100000-n5.txt
Download as CSV file: xf-naca64206-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-206                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4657   0.08923   0.08459  -0.0085   1.0000   0.0363
  -8.500  -0.4655   0.08508   0.08047  -0.0097   1.0000   0.0368
  -8.250  -0.4657   0.08086   0.07628  -0.0111   1.0000   0.0373
  -8.000  -0.4671   0.07655   0.07201  -0.0127   1.0000   0.0378
  -7.750  -0.4692   0.07234   0.06784  -0.0146   1.0000   0.0379
  -7.500  -0.4733   0.06797   0.06353  -0.0167   1.0000   0.0381
  -7.250  -0.4787   0.06355   0.05915  -0.0198   1.0000   0.0379
  -7.000  -0.4805   0.05834   0.05393  -0.0240   1.0000   0.0379
  -6.750  -0.4777   0.05269   0.04816  -0.0276   1.0000   0.0303
  -6.500  -0.4739   0.04739   0.04280  -0.0295   1.0000   0.0271
  -6.250  -0.4678   0.04158   0.03682  -0.0320   1.0000   0.0244
  -5.750  -0.4674   0.04647   0.04060  -0.0352   1.0000   0.0194
  -5.500  -0.4505   0.04220   0.03604  -0.0358   1.0000   0.0189
  -5.250  -0.4311   0.03827   0.03176  -0.0361   1.0000   0.0187
  -5.000  -0.4099   0.03458   0.02766  -0.0360   1.0000   0.0185
  -4.750  -0.3871   0.03137   0.02400  -0.0357   1.0000   0.0188
  -4.500  -0.3630   0.02856   0.02062  -0.0352   1.0000   0.0211
  -4.250  -0.3408   0.02577   0.01753  -0.0350   1.0000   0.0233
  -4.000  -0.3160   0.02335   0.01471  -0.0342   1.0000   0.0241
  -3.750  -0.2911   0.02129   0.01232  -0.0333   1.0000   0.0252
  -3.500  -0.2664   0.01952   0.01029  -0.0323   1.0000   0.0270
  -3.250  -0.2418   0.01867   0.00917  -0.0315   1.0000   0.0329
  -3.000  -0.2187   0.01690   0.00730  -0.0305   1.0000   0.0351
  -2.750  -0.1958   0.01576   0.00612  -0.0296   1.0000   0.0379
  -2.500  -0.1722   0.01494   0.00517  -0.0289   1.0000   0.0427
  -2.250  -0.1483   0.01421   0.00434  -0.0283   1.0000   0.0525
  -2.000  -0.1241   0.01326   0.00365  -0.0280   1.0000   0.1094
  -1.750  -0.1133   0.01075   0.00371  -0.0247   1.0000   0.7288
  -1.500  -0.1097   0.01042   0.00382  -0.0177   1.0000   0.8957
  -1.250  -0.0666   0.01022   0.00337  -0.0205   1.0000   1.0000
  -1.000  -0.0443   0.01025   0.00320  -0.0202   1.0000   1.0000
  -0.750  -0.0181   0.01032   0.00309  -0.0206   0.9982   1.0000
  -0.500   0.0211   0.01043   0.00304  -0.0235   0.9894   1.0000
  -0.250   0.0597   0.01053   0.00300  -0.0262   0.9807   1.0000
   0.000   0.0979   0.01062   0.00300  -0.0288   0.9717   1.0000
   0.250   0.1363   0.01071   0.00305  -0.0313   0.9632   1.0000
   0.500   0.1756   0.01080   0.00312  -0.0340   0.9551   1.0000
   0.750   0.2112   0.01088   0.00323  -0.0358   0.9447   1.0000
   1.000   0.2467   0.01096   0.00335  -0.0376   0.9345   1.0000
   1.250   0.2820   0.01104   0.00350  -0.0393   0.9242   1.0000
   1.500   0.3167   0.01112   0.00368  -0.0407   0.9137   1.0000
   1.750   0.3501   0.01121   0.00395  -0.0419   0.9022   1.0000
   2.000   0.3817   0.01131   0.00420  -0.0426   0.8895   1.0000
   2.250   0.4131   0.01140   0.00445  -0.0431   0.8751   1.0000
   2.500   0.4404   0.01132   0.00450  -0.0418   0.8389   1.0000
   2.750   0.4583   0.01118   0.00396  -0.0368   0.7092   1.0000
   3.000   0.4750   0.01194   0.00393  -0.0333   0.5000   1.0000
   3.250   0.4849   0.01502   0.00475  -0.0312   0.0760   1.0000
   3.500   0.5087   0.01604   0.00573  -0.0305   0.0520   1.0000
   3.750   0.5329   0.01700   0.00686  -0.0298   0.0448   1.0000
   4.000   0.5561   0.01813   0.00812  -0.0289   0.0404   1.0000
   4.250   0.5794   0.01933   0.00941  -0.0282   0.0330   1.0000
   4.500   0.6037   0.02082   0.01102  -0.0274   0.0295   1.0000
   4.750   0.6288   0.02271   0.01313  -0.0266   0.0272   1.0000
   5.000   0.6542   0.02546   0.01606  -0.0260   0.0255   1.0000
   5.250   0.6801   0.02752   0.01858  -0.0251   0.0221   1.0000
   5.500   0.7052   0.03017   0.02174  -0.0241   0.0201   1.0000
   5.750   0.7283   0.03349   0.02561  -0.0230   0.0194   1.0000
   6.000   0.7492   0.03720   0.02988  -0.0218   0.0191   1.0000
   6.250   0.7677   0.04128   0.03448  -0.0206   0.0191   1.0000
   6.500   0.7836   0.04565   0.03933  -0.0196   0.0193   1.0000
   6.750   0.7972   0.05007   0.04417  -0.0188   0.0190   1.0000
   7.000   0.8085   0.05424   0.04869  -0.0184   0.0176   1.0000
   7.250   0.8173   0.05844   0.05318  -0.0183   0.0168   1.0000
   7.500   0.8235   0.06233   0.05728  -0.0184   0.0157   1.0000
   7.750   0.8261   0.06695   0.06212  -0.0188   0.0155   1.0000
   8.000   0.8244   0.07208   0.06743  -0.0197   0.0156   1.0000
   8.250   0.8183   0.07761   0.07310  -0.0215   0.0161   1.0000
   8.500   0.8074   0.08294   0.07851  -0.0239   0.0168   1.0000
   8.750   0.7973   0.08913   0.08472  -0.0289   0.0173   1.0000
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