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NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-206 (naca63206-il)
Reynolds number: 50,000
Max Cl/Cd: 31.12 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca63206-il-50000-n5.txt
Download as CSV file: xf-naca63206-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-206                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5836   0.10067   0.09415  -0.0060   1.0000   0.1122
  -8.000  -0.5693   0.09614   0.08963  -0.0035   1.0000   0.1225
  -7.750  -0.5834   0.09306   0.08668  -0.0124   1.0000   0.1261
  -7.500  -0.5681   0.08878   0.08228  -0.0080   1.0000   0.1365
  -7.250  -0.5647   0.08469   0.07826  -0.0104   1.0000   0.1442
  -6.750  -0.5378   0.06959   0.06294  -0.0261   1.0000   0.0553
  -6.500  -0.5276   0.06475   0.05801  -0.0285   1.0000   0.0519
  -6.250  -0.5114   0.05934   0.05209  -0.0327   1.0000   0.0446
  -6.000  -0.4974   0.05489   0.04739  -0.0335   1.0000   0.0430
  -5.750  -0.4809   0.05053   0.04277  -0.0347   1.0000   0.0414
  -5.500  -0.4618   0.04630   0.03819  -0.0358   1.0000   0.0400
  -5.250  -0.4405   0.04225   0.03369  -0.0365   1.0000   0.0390
  -5.000  -0.4174   0.03853   0.02945  -0.0369   1.0000   0.0384
  -4.750  -0.3929   0.03516   0.02557  -0.0370   1.0000   0.0383
  -4.500  -0.3676   0.03219   0.02209  -0.0367   1.0000   0.0393
  -4.250  -0.3410   0.03004   0.01928  -0.0362   1.0000   0.0445
  -4.000  -0.3160   0.02741   0.01635  -0.0357   1.0000   0.0479
  -3.750  -0.2908   0.02529   0.01398  -0.0346   1.0000   0.0499
  -3.500  -0.2663   0.02354   0.01202  -0.0332   1.0000   0.0529
  -3.250  -0.2425   0.02210   0.01032  -0.0317   1.0000   0.0568
  -3.000  -0.2194   0.02079   0.00880  -0.0308   1.0000   0.0669
  -2.750  -0.1956   0.01966   0.00753  -0.0301   1.0000   0.0842
  -2.500  -0.1709   0.01831   0.00621  -0.0297   1.0000   0.1112
  -2.250  -0.1639   0.01503   0.00589  -0.0256   1.0000   0.6750
  -2.000  -0.1184   0.01426   0.00533  -0.0242   1.0000   1.0000
  -1.750  -0.1013   0.01413   0.00486  -0.0230   1.0000   1.0000
  -1.500  -0.0814   0.01405   0.00446  -0.0222   1.0000   1.0000
  -1.250  -0.0601   0.01402   0.00407  -0.0216   1.0000   1.0000
  -1.000  -0.0381   0.01402   0.00383  -0.0211   1.0000   1.0000
  -0.750  -0.0158   0.01404   0.00365  -0.0207   1.0000   1.0000
  -0.500   0.0066   0.01410   0.00355  -0.0203   1.0000   1.0000
  -0.250   0.0291   0.01419   0.00350  -0.0199   1.0000   1.0000
   0.000   0.0514   0.01432   0.00348  -0.0195   1.0000   1.0000
   0.250   0.0738   0.01447   0.00355  -0.0191   1.0000   1.0000
   0.500   0.0959   0.01465   0.00367  -0.0188   1.0000   1.0000
   0.750   0.1180   0.01487   0.00386  -0.0185   1.0000   1.0000
   1.000   0.1397   0.01512   0.00411  -0.0182   1.0000   1.0000
   1.250   0.1611   0.01541   0.00443  -0.0179   1.0000   1.0000
   1.500   0.2025   0.01581   0.00492  -0.0215   0.9871   1.0000
   1.750   0.2434   0.01619   0.00543  -0.0249   0.9733   1.0000
   2.000   0.2843   0.01655   0.00598  -0.0281   0.9594   1.0000
   2.250   0.3254   0.01690   0.00664  -0.0313   0.9451   1.0000
   2.500   0.3674   0.01724   0.00727  -0.0345   0.9308   1.0000
   2.750   0.4106   0.01753   0.00794  -0.0376   0.9157   1.0000
   3.000   0.4493   0.01778   0.00861  -0.0396   0.8964   1.0000
   3.250   0.4992   0.01708   0.00855  -0.0398   0.8312   1.0000
   3.500   0.5160   0.01658   0.00716  -0.0306   0.5574   1.0000
   3.750   0.5205   0.02008   0.00802  -0.0268   0.1254   1.0000
   4.000   0.5424   0.02198   0.00957  -0.0263   0.0771   1.0000
   4.250   0.5660   0.02344   0.01122  -0.0255   0.0660   1.0000
   4.500   0.5896   0.02511   0.01306  -0.0244   0.0602   1.0000
   4.750   0.6160   0.02689   0.01511  -0.0233   0.0559   1.0000
   5.000   0.6422   0.02921   0.01762  -0.0226   0.0499   1.0000
   5.250   0.6693   0.03117   0.02004  -0.0218   0.0425   1.0000
   5.500   0.6959   0.03395   0.02320  -0.0210   0.0404   1.0000
   5.750   0.7206   0.03709   0.02675  -0.0202   0.0390   1.0000
   6.000   0.7431   0.04063   0.03076  -0.0194   0.0382   1.0000
   6.250   0.7628   0.04454   0.03513  -0.0186   0.0376   1.0000
   6.500   0.7784   0.04886   0.03992  -0.0180   0.0361   1.0000
   6.750   0.7934   0.05250   0.04429  -0.0171   0.0344   1.0000
   7.000   0.8045   0.05678   0.04911  -0.0167   0.0330   1.0000
   7.250   0.8126   0.06135   0.05408  -0.0166   0.0328   1.0000
   7.500   0.8176   0.06607   0.05911  -0.0168   0.0332   1.0000
   7.750   0.8195   0.07086   0.06414  -0.0174   0.0336   1.0000
   8.000   0.8187   0.07565   0.06911  -0.0183   0.0341   1.0000
   8.250   0.8157   0.08044   0.07402  -0.0195   0.0346   1.0000
   8.500   0.8111   0.08512   0.07877  -0.0210   0.0351   1.0000
   8.750   0.8052   0.08971   0.08338  -0.0224   0.0355   1.0000
   9.000   0.8045   0.09452   0.08818  -0.0234   0.0362   1.0000
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