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NACA 64-206 (naca64206-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-206 (naca64206-il)
Reynolds number: 500,000
Max Cl/Cd: 60.06 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64206-il-500000-n5.txt
Download as CSV file: xf-naca64206-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-206                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5532   0.08545   0.08323  -0.0074   1.0000   0.0038
  -8.000  -0.5539   0.08134   0.07916  -0.0097   1.0000   0.0037
  -7.750  -0.5555   0.07763   0.07548  -0.0121   1.0000   0.0036
  -7.500  -0.5547   0.07242   0.07029  -0.0180   1.0000   0.0035
  -7.250  -0.5487   0.06739   0.06523  -0.0232   1.0000   0.0034
  -7.000  -0.5418   0.06170   0.05947  -0.0278   1.0000   0.0033
  -6.750  -0.5319   0.05638   0.05405  -0.0313   1.0000   0.0033
  -6.500  -0.5197   0.05117   0.04869  -0.0338   1.0000   0.0032
  -6.250  -0.5054   0.04582   0.04315  -0.0356   1.0000   0.0031
  -6.000  -0.4891   0.04048   0.03756  -0.0366   1.0000   0.0031
  -5.750  -0.4710   0.03542   0.03222  -0.0369   1.0000   0.0031
  -5.500  -0.4515   0.03024   0.02661  -0.0366   1.0000   0.0032
  -5.250  -0.4304   0.02497   0.02090  -0.0357   1.0000   0.0035
  -5.000  -0.4079   0.02047   0.01593  -0.0346   1.0000   0.0040
  -4.750  -0.3851   0.01738   0.01239  -0.0337   1.0000   0.0047
  -4.500  -0.3566   0.01625   0.01108  -0.0345   0.9981   0.0055
  -4.250  -0.3239   0.01398   0.00846  -0.0354   0.9947   0.0057
  -4.000  -0.2921   0.01241   0.00666  -0.0362   0.9904   0.0064
  -3.750  -0.2593   0.01123   0.00532  -0.0373   0.9867   0.0078
  -3.500  -0.2276   0.01067   0.00467  -0.0382   0.9810   0.0094
  -3.250  -0.1956   0.00961   0.00350  -0.0394   0.9756   0.0125
  -3.000  -0.1633   0.00911   0.00289  -0.0405   0.9689   0.0147
  -2.750  -0.1312   0.00876   0.00249  -0.0415   0.9612   0.0171
  -2.500  -0.0987   0.00838   0.00201  -0.0425   0.9532   0.0189
  -2.250  -0.0679   0.00808   0.00162  -0.0432   0.9430   0.0229
  -2.000  -0.0382   0.00784   0.00138  -0.0436   0.9320   0.0380
  -1.750  -0.0097   0.00751   0.00118  -0.0439   0.9201   0.0909
  -1.500   0.0162   0.00623   0.00095  -0.0445   0.9078   0.4145
  -1.250   0.0418   0.00558   0.00092  -0.0443   0.8954   0.6096
  -1.000   0.0666   0.00526   0.00095  -0.0435   0.8829   0.7247
  -0.500   0.1172   0.00508   0.00095  -0.0420   0.8579   0.8128
  -0.250   0.1436   0.00507   0.00093  -0.0416   0.8455   0.8293
   0.000   0.1700   0.00508   0.00093  -0.0412   0.8330   0.8434
   0.250   0.1963   0.00509   0.00093  -0.0407   0.8207   0.8581
   0.500   0.2224   0.00510   0.00096  -0.0402   0.8083   0.8729
   1.000   0.2734   0.00515   0.00101  -0.0389   0.7780   0.9042
   1.250   0.2982   0.00520   0.00103  -0.0381   0.7551   0.9211
   1.500   0.3219   0.00536   0.00103  -0.0369   0.7033   0.9398
   1.750   0.3457   0.00583   0.00105  -0.0360   0.5835   0.9608
   2.000   0.3725   0.00695   0.00122  -0.0365   0.3461   1.0000
   2.250   0.3962   0.00788   0.00152  -0.0363   0.1835   1.0000
   2.500   0.4213   0.00859   0.00182  -0.0363   0.0741   1.0000
   2.750   0.4478   0.00901   0.00209  -0.0362   0.0351   1.0000
   3.000   0.4747   0.00936   0.00246  -0.0361   0.0242   1.0000
   3.250   0.5018   0.00963   0.00277  -0.0361   0.0203   1.0000
   3.500   0.5287   0.00998   0.00318  -0.0360   0.0179   1.0000
   3.750   0.5550   0.01049   0.00375  -0.0358   0.0152   1.0000
   4.000   0.5796   0.01143   0.00483  -0.0352   0.0130   1.0000
   4.250   0.6067   0.01161   0.00504  -0.0352   0.0115   1.0000
   4.500   0.6322   0.01229   0.00586  -0.0348   0.0099   1.0000
   4.750   0.6576   0.01303   0.00669  -0.0344   0.0083   1.0000
   5.000   0.6815   0.01417   0.00790  -0.0339   0.0058   1.0000
   5.250   0.7075   0.01473   0.00856  -0.0337   0.0052   1.0000
   5.500   0.7321   0.01602   0.01004  -0.0330   0.0044   1.0000
   5.750   0.7563   0.01782   0.01209  -0.0323   0.0038   1.0000
   6.000   0.7799   0.02024   0.01486  -0.0313   0.0035   1.0000
   6.250   0.8008   0.02436   0.01951  -0.0298   0.0033   1.0000
   6.500   0.8172   0.03089   0.02671  -0.0275   0.0034   1.0000
   6.750   0.8304   0.03780   0.03417  -0.0254   0.0036   1.0000
   7.000   0.8417   0.04401   0.04080  -0.0239   0.0037   1.0000
   7.250   0.8507   0.04981   0.04692  -0.0230   0.0039   1.0000
   7.500   0.8567   0.05549   0.05286  -0.0225   0.0040   1.0000
   7.750   0.8596   0.06103   0.05861  -0.0226   0.0042   1.0000
   8.000   0.8585   0.06659   0.06435  -0.0232   0.0043   1.0000
   8.250   0.8539   0.07197   0.06986  -0.0244   0.0044   1.0000
   8.500   0.8442   0.07704   0.07501  -0.0260   0.0045   1.0000
   8.750   0.8292   0.08224   0.08026  -0.0291   0.0045   1.0000
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