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NACA 65-206 (naca65206-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-206 (naca65206-il)
Reynolds number: 200,000
Max Cl/Cd: 50.32 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65206-il-200000-n5.txt
Download as CSV file: xf-naca65206-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-206                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5296   0.08236   0.07887  -0.0190   1.0000   0.0103
  -7.500  -0.5268   0.07738   0.07389  -0.0229   1.0000   0.0103
  -7.250  -0.5332   0.07170   0.06823  -0.0247   1.0000   0.0092
  -7.000  -0.5284   0.06700   0.06348  -0.0276   1.0000   0.0089
  -6.750  -0.5210   0.06237   0.05878  -0.0303   1.0000   0.0085
  -6.500  -0.5112   0.05774   0.05404  -0.0325   1.0000   0.0082
  -6.250  -0.4992   0.05304   0.04919  -0.0343   1.0000   0.0080
  -6.000  -0.4851   0.04852   0.04448  -0.0354   1.0000   0.0079
  -5.750  -0.4691   0.04409   0.03982  -0.0360   1.0000   0.0079
  -5.500  -0.4504   0.04017   0.03564  -0.0360   1.0000   0.0085
  -5.000  -0.4093   0.03274   0.02750  -0.0347   1.0000   0.0109
  -4.750  -0.3883   0.02991   0.02435  -0.0338   1.0000   0.0107
  -4.500  -0.3673   0.02712   0.02122  -0.0329   1.0000   0.0106
  -4.250  -0.3460   0.02422   0.01793  -0.0319   1.0000   0.0106
  -4.000  -0.3239   0.02134   0.01462  -0.0309   1.0000   0.0107
  -3.750  -0.3012   0.01840   0.01125  -0.0300   1.0000   0.0114
  -3.500  -0.2784   0.01668   0.00930  -0.0290   1.0000   0.0126
  -3.250  -0.2480   0.01596   0.00843  -0.0299   0.9971   0.0172
  -3.000  -0.2149   0.01439   0.00659  -0.0307   0.9934   0.0194
  -2.750  -0.1819   0.01338   0.00546  -0.0319   0.9892   0.0225
  -2.500  -0.1490   0.01233   0.00437  -0.0333   0.9850   0.0268
  -2.250  -0.1153   0.01164   0.00357  -0.0348   0.9802   0.0301
  -2.000  -0.0809   0.01116   0.00294  -0.0363   0.9757   0.0361
  -1.750  -0.0474   0.01060   0.00244  -0.0378   0.9702   0.0707
  -1.500  -0.0260   0.00808   0.00243  -0.0377   0.9653   0.7271
  -1.250  -0.0035   0.00788   0.00252  -0.0356   0.9576   0.8360
  -1.000   0.0172   0.00780   0.00256  -0.0330   0.9497   0.9058
  -0.750   0.0487   0.00775   0.00246  -0.0334   0.9437   0.9339
  -0.500   0.0834   0.00771   0.00233  -0.0349   0.9374   0.9471
  -0.250   0.1198   0.00766   0.00223  -0.0368   0.9312   0.9592
   0.000   0.1574   0.00763   0.00215  -0.0389   0.9248   0.9709
   0.250   0.1954   0.00759   0.00210  -0.0413   0.9180   0.9829
   0.500   0.2323   0.00756   0.00209  -0.0434   0.9101   0.9990
   0.750   0.2614   0.00757   0.00209  -0.0437   0.9006   1.0000
   1.000   0.2887   0.00760   0.00213  -0.0437   0.8901   1.0000
   1.250   0.3155   0.00764   0.00221  -0.0436   0.8789   1.0000
   1.500   0.3422   0.00768   0.00229  -0.0433   0.8661   1.0000
   1.750   0.3664   0.00768   0.00229  -0.0419   0.8349   1.0000
   2.000   0.3890   0.00773   0.00224  -0.0402   0.7854   1.0000
   2.250   0.4062   0.00817   0.00205  -0.0370   0.6380   1.0000
   2.500   0.4147   0.01039   0.00237  -0.0340   0.2190   1.0000
   2.750   0.4352   0.01176   0.00297  -0.0333   0.0467   1.0000
   3.000   0.4607   0.01232   0.00364  -0.0329   0.0356   1.0000
   3.250   0.4860   0.01289   0.00435  -0.0325   0.0318   1.0000
   3.500   0.5100   0.01373   0.00526  -0.0320   0.0270   1.0000
   3.750   0.5345   0.01448   0.00610  -0.0315   0.0242   1.0000
   4.000   0.5587   0.01548   0.00721  -0.0308   0.0218   1.0000
   4.250   0.5830   0.01682   0.00867  -0.0300   0.0198   1.0000
   4.500   0.6077   0.01776   0.00965  -0.0297   0.0152   1.0000
   4.750   0.6319   0.02045   0.01259  -0.0288   0.0135   1.0000
   5.000   0.6580   0.02244   0.01500  -0.0279   0.0126   1.0000
   5.250   0.6837   0.02449   0.01744  -0.0270   0.0106   1.0000
   5.500   0.7081   0.02625   0.01950  -0.0263   0.0084   1.0000
   5.750   0.7305   0.02917   0.02285  -0.0252   0.0078   1.0000
   6.000   0.7509   0.03267   0.02680  -0.0239   0.0075   1.0000
   6.250   0.7690   0.03674   0.03132  -0.0225   0.0075   1.0000
   6.500   0.7848   0.04158   0.03662  -0.0209   0.0076   1.0000
   6.750   0.7979   0.04676   0.04222  -0.0196   0.0079   1.0000
   7.000   0.8083   0.05206   0.04787  -0.0186   0.0083   1.0000
   7.250   0.8156   0.05741   0.05352  -0.0180   0.0088   1.0000
   7.500   0.8200   0.06260   0.05895  -0.0179   0.0091   1.0000
   7.750   0.8212   0.06771   0.06425  -0.0182   0.0095   1.0000
   8.000   0.8185   0.07287   0.06955  -0.0192   0.0099   1.0000
   8.250   0.8129   0.07778   0.07456  -0.0206   0.0101   1.0000
   8.500   0.8017   0.08249   0.07932  -0.0224   0.0103   1.0000
   8.750   0.7916   0.08817   0.08502  -0.0271   0.0104   1.0000
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