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NACA 66-209 (naca66209-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 66-209 (naca66209-il)
Reynolds number: 500,000
Max Cl/Cd: 60.65 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca66209-il-500000-n5.txt
Download as CSV file: xf-naca66209-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66-209                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5360   0.08358   0.08133  -0.0360   1.0000   0.0060
  -9.500  -0.5429   0.07815   0.07594  -0.0396   1.0000   0.0056
  -9.250  -0.5570   0.07141   0.06922  -0.0458   1.0000   0.0056
  -9.000  -0.5747   0.06676   0.06456  -0.0478   1.0000   0.0056
  -8.750  -0.5943   0.06255   0.06030  -0.0471   0.9987   0.0054
  -8.500  -0.5902   0.05547   0.05302  -0.0521   0.9831   0.0056
  -8.250  -0.5838   0.04811   0.04537  -0.0555   0.9716   0.0060
  -8.000  -0.5761   0.04109   0.03797  -0.0569   0.9611   0.0060
  -7.750  -0.5760   0.03159   0.02779  -0.0553   0.9487   0.0067
  -7.500  -0.5756   0.02257   0.01778  -0.0519   0.9378   0.0075
  -7.250  -0.5545   0.02157   0.01661  -0.0513   0.9307   0.0078
  -7.000  -0.5315   0.02079   0.01566  -0.0509   0.9252   0.0083
  -6.750  -0.5099   0.01920   0.01381  -0.0501   0.9194   0.0088
  -6.500  -0.4868   0.01789   0.01223  -0.0495   0.9141   0.0096
  -6.250  -0.4633   0.01654   0.01063  -0.0488   0.9095   0.0103
  -6.000  -0.4382   0.01602   0.00997  -0.0485   0.9043   0.0110
  -5.750  -0.4153   0.01461   0.00838  -0.0478   0.8994   0.0121
  -5.500  -0.3905   0.01405   0.00775  -0.0475   0.8951   0.0128
  -5.250  -0.3656   0.01347   0.00709  -0.0472   0.8904   0.0135
  -5.000  -0.3406   0.01292   0.00644  -0.0468   0.8863   0.0143
  -4.750  -0.3153   0.01247   0.00592  -0.0465   0.8827   0.0155
  -4.500  -0.2900   0.01201   0.00540  -0.0461   0.8784   0.0165
  -4.250  -0.2649   0.01154   0.00485  -0.0458   0.8741   0.0171
  -4.000  -0.2400   0.01107   0.00430  -0.0454   0.8704   0.0178
  -3.750  -0.2159   0.01043   0.00357  -0.0449   0.8664   0.0194
  -3.500  -0.1900   0.01010   0.00322  -0.0447   0.8624   0.0211
  -3.250  -0.1636   0.00987   0.00296  -0.0445   0.8590   0.0238
  -3.000  -0.1370   0.00966   0.00270  -0.0444   0.8559   0.0262
  -2.750  -0.1103   0.00946   0.00246  -0.0444   0.8527   0.0282
  -2.500  -0.0837   0.00920   0.00217  -0.0443   0.8490   0.0341
  -2.250  -0.0567   0.00904   0.00199  -0.0442   0.8456   0.0395
  -2.000  -0.0303   0.00878   0.00183  -0.0442   0.8425   0.0705
  -1.750  -0.0076   0.00785   0.00160  -0.0439   0.8393   0.2791
  -1.500   0.0087   0.00625   0.00143  -0.0427   0.8355   0.6728
  -1.250   0.0338   0.00613   0.00153  -0.0420   0.8324   0.7485
  -1.000   0.0603   0.00613   0.00158  -0.0416   0.8296   0.7780
  -0.500   0.1152   0.00616   0.00162  -0.0414   0.8238   0.8023
  -0.250   0.1426   0.00619   0.00166  -0.0414   0.8208   0.8139
   0.000   0.1698   0.00622   0.00171  -0.0412   0.8180   0.8241
   0.250   0.1979   0.00624   0.00172  -0.0413   0.8152   0.8283
   0.500   0.2258   0.00624   0.00173  -0.0414   0.8114   0.8311
   0.750   0.2531   0.00623   0.00172  -0.0413   0.8026   0.8344
   1.000   0.2801   0.00622   0.00168  -0.0411   0.7898   0.8377
   1.250   0.3073   0.00622   0.00166  -0.0410   0.7761   0.8410
   1.500   0.3340   0.00623   0.00167  -0.0407   0.7618   0.8436
   1.750   0.3600   0.00625   0.00166  -0.0402   0.7378   0.8469
   2.000   0.3851   0.00635   0.00164  -0.0396   0.6978   0.8507
   2.250   0.4017   0.00703   0.00170  -0.0374   0.5429   0.8551
   2.500   0.4119   0.00853   0.00218  -0.0346   0.2982   0.8592
   2.750   0.4281   0.00969   0.00259  -0.0331   0.1123   0.8637
   3.000   0.4506   0.01027   0.00288  -0.0324   0.0422   0.8680
   3.250   0.4757   0.01050   0.00311  -0.0320   0.0337   0.8717
   3.500   0.5010   0.01071   0.00338  -0.0316   0.0298   0.8759
   3.750   0.5258   0.01101   0.00369  -0.0312   0.0253   0.8806
   4.000   0.5500   0.01135   0.00409  -0.0306   0.0224   0.8848
   4.250   0.5743   0.01163   0.00443  -0.0300   0.0207   0.8892
   4.500   0.5987   0.01194   0.00480  -0.0295   0.0187   0.8941
   4.750   0.6225   0.01227   0.00517  -0.0289   0.0172   0.8989
   5.000   0.6451   0.01268   0.00564  -0.0280   0.0162   0.9044
   5.250   0.6668   0.01329   0.00631  -0.0270   0.0152   0.9106
   5.500   0.6852   0.01419   0.00732  -0.0254   0.0144   0.9168
   5.750   0.7076   0.01471   0.00792  -0.0245   0.0141   0.9234
   6.000   0.7289   0.01534   0.00866  -0.0234   0.0137   0.9299
   6.250   0.7508   0.01597   0.00939  -0.0224   0.0131   0.9374
   6.500   0.7729   0.01653   0.01005  -0.0215   0.0123   0.9452
   6.750   0.7955   0.01730   0.01092  -0.0207   0.0117   0.9546
   7.000   0.8204   0.01811   0.01184  -0.0205   0.0111   0.9649
   7.500   0.8766   0.01958   0.01350  -0.0218   0.0099   1.0000
   7.750   0.8976   0.02157   0.01571  -0.0211   0.0091   1.0000
   8.000   0.9208   0.02244   0.01675  -0.0207   0.0087   1.0000
   8.250   0.9421   0.02407   0.01863  -0.0199   0.0082   1.0000
   8.500   0.9616   0.02600   0.02084  -0.0190   0.0075   1.0000
   8.750   0.9779   0.02847   0.02364  -0.0175   0.0071   1.0000
   9.000   0.9930   0.03058   0.02603  -0.0161   0.0066   1.0000
   9.250   1.0077   0.03227   0.02796  -0.0148   0.0063   1.0000
   9.500   1.0256   0.03273   0.02850  -0.0140   0.0061   1.0000
   9.750   1.0437   0.03288   0.02868  -0.0132   0.0059   1.0000
  10.000   1.0325   0.03911   0.03554  -0.0090   0.0055   1.0000
  10.250   0.9652   0.05400   0.05124   0.0001   0.0051   1.0000
  10.500   0.9403   0.05860   0.05604   0.0038   0.0051   1.0000
  10.750   0.9115   0.06405   0.06166   0.0058   0.0051   1.0000
  11.000   0.8881   0.06914   0.06689   0.0057   0.0052   1.0000
  11.250   0.8657   0.07504   0.07290   0.0036   0.0053   1.0000
  11.500   0.8452   0.08223   0.08018  -0.0011   0.0054   1.0000
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