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NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-206 (naca63206-il)
Reynolds number: 1,000,000
Max Cl/Cd: 69.01 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca63206-il-1000000-n5.txt
Download as CSV file: xf-naca63206-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5708   0.09012   0.08852  -0.0019   1.0000   0.0019
  -8.500  -0.5675   0.08645   0.08487  -0.0039   1.0000   0.0019
  -8.250  -0.5657   0.08274   0.08118  -0.0060   1.0000   0.0019
  -8.000  -0.5660   0.07882   0.07729  -0.0083   1.0000   0.0019
  -7.750  -0.5712   0.07428   0.07277  -0.0120   1.0000   0.0018
  -7.500  -0.5687   0.06780   0.06628  -0.0200   1.0000   0.0017
  -7.250  -0.5624   0.06181   0.06022  -0.0256   1.0000   0.0017
  -7.000  -0.5540   0.05561   0.05392  -0.0301   1.0000   0.0017
  -6.750  -0.5427   0.04954   0.04770  -0.0333   1.0000   0.0016
  -6.500  -0.5289   0.04325   0.04120  -0.0356   1.0000   0.0016
  -6.250  -0.5129   0.03646   0.03410  -0.0370   1.0000   0.0016
  -6.000  -0.4949   0.02886   0.02606  -0.0374   1.0000   0.0017
  -5.750  -0.4790   0.01379   0.00950  -0.0361   1.0000   0.0022
  -5.500  -0.4541   0.01301   0.00859  -0.0357   1.0000   0.0024
  -5.250  -0.4272   0.01222   0.00768  -0.0358   0.9991   0.0026
  -4.750  -0.3642   0.01042   0.00555  -0.0379   0.9904   0.0032
  -4.500  -0.3320   0.00991   0.00497  -0.0390   0.9849   0.0037
  -4.250  -0.2998   0.00928   0.00425  -0.0402   0.9784   0.0041
  -4.000  -0.2679   0.00819   0.00298  -0.0412   0.9698   0.0053
  -3.750  -0.2362   0.00797   0.00276  -0.0421   0.9594   0.0069
  -3.500  -0.2062   0.00775   0.00249  -0.0427   0.9465   0.0086
  -3.250  -0.1781   0.00782   0.00256  -0.0427   0.9321   0.0094
  -3.000  -0.1511   0.00730   0.00185  -0.0425   0.9172   0.0112
  -2.750  -0.1242   0.00706   0.00149  -0.0423   0.9028   0.0126
  -2.500  -0.0972   0.00689   0.00126  -0.0421   0.8886   0.0152
  -2.250  -0.0701   0.00678   0.00108  -0.0419   0.8740   0.0189
  -2.000  -0.0430   0.00667   0.00094  -0.0417   0.8593   0.0273
  -1.750  -0.0157   0.00655   0.00080  -0.0416   0.8448   0.0451
  -1.500   0.0115   0.00630   0.00068  -0.0416   0.8305   0.1068
  -1.250   0.0384   0.00566   0.00055  -0.0419   0.8168   0.2856
  -1.000   0.0653   0.00506   0.00046  -0.0422   0.8039   0.4657
  -0.750   0.0922   0.00468   0.00045  -0.0422   0.7909   0.5964
  -0.500   0.1192   0.00448   0.00046  -0.0421   0.7781   0.6791
  -0.250   0.1464   0.00441   0.00047  -0.0420   0.7648   0.7207
   0.000   0.1737   0.00440   0.00047  -0.0418   0.7486   0.7451
   0.250   0.2009   0.00442   0.00049  -0.0417   0.7287   0.7666
   0.500   0.2281   0.00446   0.00051  -0.0415   0.7084   0.7824
   0.750   0.2551   0.00453   0.00054  -0.0413   0.6840   0.7971
   1.000   0.2819   0.00464   0.00058  -0.0411   0.6478   0.8118
   1.250   0.3072   0.00497   0.00063  -0.0407   0.5637   0.8269
   1.500   0.3302   0.00584   0.00080  -0.0401   0.3655   0.8427
   1.750   0.3540   0.00666   0.00106  -0.0398   0.1948   0.8591
   2.000   0.3792   0.00708   0.00125  -0.0395   0.1143   0.8762
   2.250   0.4043   0.00740   0.00143  -0.0390   0.0575   0.8949
   2.750   0.4541   0.00775   0.00175  -0.0377   0.0212   0.9361
   3.000   0.4798   0.00792   0.00197  -0.0372   0.0155   0.9627
   3.250   0.5103   0.00818   0.00233  -0.0378   0.0138   1.0000
   3.500   0.5371   0.00861   0.00286  -0.0376   0.0127   1.0000
   3.750   0.5646   0.00877   0.00302  -0.0377   0.0124   1.0000
   4.000   0.5922   0.00887   0.00310  -0.0378   0.0113   1.0000
   4.250   0.6194   0.00911   0.00339  -0.0377   0.0094   1.0000
   4.500   0.6464   0.00940   0.00369  -0.0377   0.0076   1.0000
   4.750   0.6725   0.00991   0.00424  -0.0375   0.0055   1.0000
   5.000   0.6994   0.01017   0.00453  -0.0374   0.0049   1.0000
   5.250   0.7258   0.01053   0.00492  -0.0373   0.0040   1.0000
   5.500   0.7522   0.01090   0.00529  -0.0372   0.0031   1.0000
   5.750   0.7760   0.01211   0.00668  -0.0365   0.0024   1.0000
   6.000   0.8008   0.01303   0.00775  -0.0360   0.0022   1.0000
   6.250   0.8245   0.01438   0.00931  -0.0353   0.0021   1.0000
   6.500   0.8475   0.01628   0.01154  -0.0345   0.0020   1.0000
   6.750   0.8683   0.01954   0.01528  -0.0332   0.0020   1.0000
   7.000   0.8746   0.03074   0.02756  -0.0294   0.0021   1.0000
   7.250   0.8841   0.03834   0.03566  -0.0274   0.0020   1.0000
   7.500   0.8935   0.04454   0.04220  -0.0261   0.0019   1.0000
   7.750   0.8999   0.05069   0.04863  -0.0253   0.0018   1.0000
   8.000   0.9022   0.05688   0.05505  -0.0250   0.0018   1.0000
   8.250   0.9009   0.06289   0.06125  -0.0254   0.0017   1.0000
   8.500   0.8945   0.06888   0.06738  -0.0264   0.0017   1.0000
   8.750   0.8829   0.07455   0.07316  -0.0280   0.0017   1.0000
   9.000   0.8642   0.07965   0.07831  -0.0305   0.0018   1.0000
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