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NACA 66-206 (naca66206-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 66-206 (naca66206-il)
Reynolds number: 50,000
Max Cl/Cd: 20.93 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca66206-il-50000.txt
Download as CSV file: xf-naca66206-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66-206                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5628   0.11708   0.11007  -0.0062   1.0000   0.1656
  -9.250  -0.5519   0.11244   0.10545  -0.0055   1.0000   0.1755
  -9.000  -0.5673   0.11125   0.10439  -0.0090   1.0000   0.1798
  -8.750  -0.5584   0.10695   0.10012  -0.0083   1.0000   0.1926
  -8.500  -0.5525   0.10312   0.09634  -0.0080   1.0000   0.2052
  -8.250  -0.5509   0.09974   0.09302  -0.0080   1.0000   0.2185
  -8.000  -0.5520   0.09666   0.09003  -0.0081   1.0000   0.2323
  -7.750  -0.5400   0.09258   0.08597  -0.0060   1.0000   0.2551
  -7.500  -0.5369   0.08943   0.08289  -0.0045   1.0000   0.2806
  -7.250  -0.5358   0.08664   0.08017  -0.0024   1.0000   0.3106
  -7.000  -0.5256   0.08334   0.07692   0.0008   1.0000   0.3481
  -6.750  -0.5374   0.08162   0.07534   0.0034   1.0000   0.3807
  -6.500  -0.5069   0.07756   0.07122   0.0091   1.0000   0.4463
  -6.250  -0.4743   0.07360   0.06711   0.0146   1.0000   0.5261
  -6.000  -0.4398   0.07000   0.06345   0.0199   1.0000   0.6219
  -5.250  -0.3397   0.05667   0.04999   0.0184   1.0000   0.7747
  -5.000  -0.4138   0.05732   0.05102   0.0216   1.0000   0.6554
  -4.750  -0.4588   0.05610   0.05010   0.0246   1.0000   0.6119
  -4.250  -0.4134   0.03893   0.03016  -0.0310   1.0000   0.1656
  -4.000  -0.3846   0.03534   0.02595  -0.0305   1.0000   0.1364
  -3.750  -0.3577   0.03241   0.02242  -0.0295   1.0000   0.1207
  -3.500  -0.3305   0.03006   0.01941  -0.0283   1.0000   0.1110
  -3.250  -0.3052   0.02785   0.01680  -0.0271   1.0000   0.1100
  -3.000  -0.2807   0.02584   0.01452  -0.0260   1.0000   0.1169
  -2.750  -0.2547   0.02405   0.01248  -0.0246   1.0000   0.1181
  -2.500  -0.2289   0.02252   0.01078  -0.0228   1.0000   0.1219
  -2.250  -0.2045   0.02120   0.00931  -0.0211   1.0000   0.1293
  -2.000  -0.1826   0.01996   0.00805  -0.0196   1.0000   0.1485
  -1.750  -0.1226   0.01561   0.00650  -0.0206   1.0000   1.0000
  -1.500  -0.1097   0.01555   0.00594  -0.0181   1.0000   1.0000
  -1.250  -0.0951   0.01552   0.00554  -0.0160   1.0000   1.0000
  -1.000  -0.0787   0.01552   0.00523  -0.0143   1.0000   1.0000
  -0.750  -0.0609   0.01555   0.00499  -0.0130   1.0000   1.0000
  -0.500  -0.0420   0.01561   0.00483  -0.0118   1.0000   1.0000
  -0.250  -0.0223   0.01569   0.00472  -0.0108   1.0000   1.0000
   0.000  -0.0021   0.01580   0.00461  -0.0100   1.0000   1.0000
   0.250   0.0186   0.01593   0.00461  -0.0092   1.0000   1.0000
   0.500   0.0395   0.01608   0.00467  -0.0085   1.0000   1.0000
   0.750   0.0606   0.01625   0.00478  -0.0078   1.0000   1.0000
   1.000   0.0819   0.01645   0.00494  -0.0073   1.0000   1.0000
   1.250   0.1032   0.01667   0.00515  -0.0067   1.0000   1.0000
   1.500   0.1246   0.01691   0.00544  -0.0062   1.0000   1.0000
   1.750   0.1459   0.01718   0.00575  -0.0057   1.0000   1.0000
   2.000   0.1672   0.01748   0.00611  -0.0052   1.0000   1.0000
   2.250   0.1884   0.01780   0.00654  -0.0048   1.0000   1.0000
   2.500   0.2094   0.01816   0.00703  -0.0044   1.0000   1.0000
   2.750   0.2303   0.01855   0.00758  -0.0040   1.0000   1.0000
   3.000   0.2510   0.01898   0.00822  -0.0036   1.0000   1.0000
   3.250   0.2714   0.01945   0.00903  -0.0032   1.0000   1.0000
   3.500   0.2915   0.01997   0.00984  -0.0029   1.0000   1.0000
   3.750   0.3114   0.02054   0.01075  -0.0026   1.0000   1.0000
   4.000   0.3309   0.02118   0.01181  -0.0023   1.0000   1.0000
   4.250   0.5587   0.02669   0.01471  -0.0195   0.1049   1.0000
   4.500   0.5931   0.02958   0.01771  -0.0194   0.1025   1.0000
   4.750   0.6238   0.03240   0.02091  -0.0187   0.1031   1.0000
   5.000   0.6528   0.03486   0.02423  -0.0171   0.1089   1.0000
   5.250   0.6795   0.03880   0.02847  -0.0162   0.1154   1.0000
   5.500   0.7046   0.04217   0.03266  -0.0146   0.1277   1.0000
   5.750   0.7274   0.04599   0.03718  -0.0133   0.1405   1.0000
   6.000   0.7507   0.05059   0.04282  -0.0128   0.1761   1.0000
   6.250   0.7569   0.06329   0.05740  -0.0346   0.3880   1.0000
   6.500   0.7132   0.07093   0.06496  -0.0470   0.4549   1.0000
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