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NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-208 (naca64208-il)
Reynolds number: 200,000
Max Cl/Cd: 53.3 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64208-il-200000-n5.txt
Download as CSV file: xf-naca64208-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-208                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5613   0.08516   0.08164  -0.0162   1.0000   0.0117
  -8.750  -0.5645   0.08001   0.07654  -0.0197   1.0000   0.0116
  -8.500  -0.5703   0.07420   0.07078  -0.0245   1.0000   0.0116
  -8.250  -0.5797   0.06857   0.06516  -0.0299   1.0000   0.0114
  -8.000  -0.5845   0.06294   0.05944  -0.0335   1.0000   0.0113
  -7.750  -0.5856   0.05763   0.05399  -0.0359   1.0000   0.0114
  -7.500  -0.5828   0.05251   0.04868  -0.0373   1.0000   0.0115
  -7.250  -0.5751   0.04715   0.04301  -0.0379   1.0000   0.0125
  -7.000  -0.5642   0.04250   0.03801  -0.0378   1.0000   0.0130
  -6.750  -0.5532   0.03805   0.03319  -0.0374   1.0000   0.0131
  -6.500  -0.5400   0.03393   0.02865  -0.0366   1.0000   0.0131
  -6.000  -0.5097   0.02602   0.01976  -0.0347   1.0000   0.0138
  -5.750  -0.4908   0.02367   0.01712  -0.0338   1.0000   0.0145
  -5.500  -0.4703   0.02244   0.01570  -0.0329   1.0000   0.0157
  -5.250  -0.4494   0.02150   0.01460  -0.0320   1.0000   0.0177
  -5.000  -0.4283   0.01987   0.01269  -0.0308   1.0000   0.0189
  -4.750  -0.4004   0.01826   0.01078  -0.0309   0.9974   0.0200
  -4.500  -0.3665   0.01706   0.00936  -0.0322   0.9920   0.0213
  -4.250  -0.3337   0.01553   0.00774  -0.0337   0.9868   0.0241
  -4.000  -0.3008   0.01451   0.00666  -0.0350   0.9806   0.0258
  -3.750  -0.2667   0.01365   0.00574  -0.0366   0.9751   0.0282
  -3.500  -0.2339   0.01297   0.00493  -0.0379   0.9676   0.0314
  -3.250  -0.2009   0.01234   0.00423  -0.0393   0.9602   0.0373
  -3.000  -0.1670   0.01188   0.00370  -0.0407   0.9531   0.0461
  -2.750  -0.1353   0.01133   0.00323  -0.0418   0.9442   0.0696
  -2.500  -0.1054   0.00993   0.00272  -0.0434   0.9360   0.2974
  -2.250  -0.0782   0.00895   0.00261  -0.0438   0.9264   0.5372
  -2.000  -0.0519   0.00861   0.00268  -0.0432   0.9163   0.6520
  -1.750  -0.0272   0.00848   0.00281  -0.0419   0.9062   0.7341
  -1.500  -0.0007   0.00844   0.00279  -0.0411   0.8964   0.7709
  -1.000   0.0534   0.00838   0.00265  -0.0404   0.8750   0.7969
  -0.750   0.0802   0.00836   0.00259  -0.0399   0.8647   0.8082
  -0.500   0.1068   0.00834   0.00253  -0.0395   0.8547   0.8200
  -0.250   0.1331   0.00833   0.00250  -0.0390   0.8440   0.8319
   0.000   0.1591   0.00833   0.00248  -0.0384   0.8334   0.8442
   0.250   0.1851   0.00833   0.00248  -0.0378   0.8232   0.8568
   0.750   0.2364   0.00835   0.00250  -0.0364   0.8028   0.8828
   1.000   0.2622   0.00835   0.00253  -0.0358   0.7924   0.8966
   1.250   0.2884   0.00837   0.00256  -0.0353   0.7827   0.9113
   1.500   0.3155   0.00838   0.00262  -0.0349   0.7728   0.9264
   1.750   0.3446   0.00839   0.00267  -0.0351   0.7620   0.9421
   2.000   0.3762   0.00841   0.00273  -0.0358   0.7494   0.9584
   2.500   0.4383   0.00852   0.00266  -0.0367   0.6740   1.0000
   2.750   0.4606   0.00880   0.00263  -0.0354   0.5985   1.0000
   3.000   0.4850   0.00910   0.00274  -0.0347   0.5419   1.0000
   3.250   0.5058   0.00980   0.00291  -0.0336   0.4096   1.0000
   3.500   0.5206   0.01167   0.00357  -0.0324   0.1527   1.0000
   3.750   0.5425   0.01275   0.00416  -0.0319   0.0598   1.0000
   4.000   0.5674   0.01335   0.00470  -0.0316   0.0428   1.0000
   4.250   0.5925   0.01395   0.00537  -0.0313   0.0361   1.0000
   4.500   0.6173   0.01459   0.00609  -0.0309   0.0319   1.0000
   4.750   0.6399   0.01558   0.00715  -0.0303   0.0274   1.0000
   5.000   0.6644   0.01627   0.00792  -0.0298   0.0253   1.0000
   5.250   0.6881   0.01717   0.00892  -0.0292   0.0237   1.0000
   5.500   0.7118   0.01823   0.01007  -0.0286   0.0223   1.0000
   5.750   0.7357   0.01944   0.01137  -0.0280   0.0211   1.0000
   6.000   0.7599   0.02076   0.01281  -0.0274   0.0201   1.0000
   6.250   0.7839   0.02189   0.01406  -0.0270   0.0184   1.0000
   6.500   0.8060   0.02446   0.01682  -0.0264   0.0167   1.0000
   6.750   0.8299   0.02613   0.01879  -0.0257   0.0162   1.0000
   7.000   0.8524   0.02839   0.02143  -0.0249   0.0155   1.0000
   7.250   0.8731   0.03091   0.02438  -0.0238   0.0145   1.0000
   7.500   0.8930   0.03290   0.02671  -0.0230   0.0129   1.0000
   7.750   0.9104   0.03530   0.02943  -0.0220   0.0120   1.0000
   8.000   0.9244   0.03834   0.03284  -0.0208   0.0115   1.0000
   8.250   0.9356   0.04149   0.03638  -0.0196   0.0111   1.0000
   8.500   0.9421   0.04520   0.04045  -0.0182   0.0108   1.0000
   8.750   0.9433   0.04942   0.04501  -0.0168   0.0106   1.0000
   9.000   0.9386   0.05407   0.04999  -0.0153   0.0105   1.0000
   9.250   0.9296   0.05875   0.05495  -0.0139   0.0105   1.0000
   9.500   0.9144   0.06311   0.05952  -0.0123   0.0106   1.0000
   9.750   0.8959   0.06780   0.06438  -0.0121   0.0107   1.0000
  10.000   0.8744   0.07406   0.07080  -0.0144   0.0108   1.0000
  10.250   0.8437   0.08548   0.08232  -0.0220   0.0114   1.0000
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