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NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-206 (naca63206-il)
Reynolds number: 200,000
Max Cl/Cd: 52.38 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca63206-il-200000-n5.txt
Download as CSV file: xf-naca63206-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5518   0.08452   0.08109  -0.0077   1.0000   0.0090
  -7.750  -0.5544   0.08021   0.07684  -0.0102   1.0000   0.0086
  -7.500  -0.5534   0.07518   0.07184  -0.0152   1.0000   0.0085
  -7.250  -0.5486   0.06984   0.06648  -0.0205   1.0000   0.0083
  -7.000  -0.5415   0.06445   0.06103  -0.0250   1.0000   0.0082
  -6.750  -0.5319   0.05923   0.05571  -0.0285   1.0000   0.0081
  -6.500  -0.5197   0.05409   0.05041  -0.0314   1.0000   0.0081
  -6.000  -0.4882   0.04342   0.03923  -0.0355   1.0000   0.0106
  -5.750  -0.4725   0.04166   0.03731  -0.0363   1.0000   0.0128
  -5.500  -0.4507   0.03560   0.03077  -0.0369   1.0000   0.0113
  -5.250  -0.4272   0.03083   0.02550  -0.0367   1.0000   0.0106
  -5.000  -0.4036   0.02731   0.02154  -0.0364   1.0000   0.0103
  -4.750  -0.3796   0.02418   0.01798  -0.0360   1.0000   0.0103
  -4.500  -0.3552   0.02132   0.01468  -0.0355   1.0000   0.0105
  -4.250  -0.3305   0.01901   0.01202  -0.0350   1.0000   0.0111
  -4.000  -0.3058   0.01733   0.01007  -0.0344   1.0000   0.0122
  -3.750  -0.2812   0.01659   0.00919  -0.0338   1.0000   0.0161
  -3.500  -0.2565   0.01511   0.00749  -0.0329   1.0000   0.0176
  -3.250  -0.2322   0.01399   0.00625  -0.0321   1.0000   0.0191
  -3.000  -0.2085   0.01282   0.00502  -0.0316   1.0000   0.0230
  -2.750  -0.1844   0.01211   0.00421  -0.0310   1.0000   0.0261
  -2.500  -0.1600   0.01152   0.00351  -0.0305   1.0000   0.0292
  -2.250  -0.1276   0.01098   0.00284  -0.0317   0.9958   0.0361
  -2.000  -0.0926   0.01016   0.00236  -0.0337   0.9896   0.1196
  -1.750  -0.0613   0.00839   0.00215  -0.0359   0.9842   0.5353
  -1.500  -0.0348   0.00773   0.00230  -0.0351   0.9770   0.7613
  -1.250  -0.0109   0.00755   0.00236  -0.0333   0.9672   0.8532
  -1.000   0.0188   0.00748   0.00227  -0.0333   0.9573   0.8831
  -0.750   0.0506   0.00743   0.00217  -0.0340   0.9476   0.9049
  -0.500   0.0842   0.00737   0.00206  -0.0350   0.9384   0.9261
  -0.250   0.1201   0.00732   0.00196  -0.0366   0.9289   0.9468
   0.000   0.1580   0.00726   0.00188  -0.0387   0.9185   0.9687
   0.250   0.1964   0.00721   0.00181  -0.0410   0.9071   1.0000
   0.500   0.2262   0.00724   0.00181  -0.0414   0.8934   1.0000
   0.750   0.2547   0.00728   0.00182  -0.0415   0.8792   1.0000
   1.000   0.2825   0.00733   0.00186  -0.0415   0.8646   1.0000
   1.250   0.3098   0.00740   0.00192  -0.0413   0.8497   1.0000
   1.500   0.3367   0.00747   0.00200  -0.0409   0.8333   1.0000
   1.750   0.3632   0.00756   0.00213  -0.0405   0.8136   1.0000
   2.000   0.3891   0.00766   0.00223  -0.0398   0.7892   1.0000
   2.250   0.4117   0.00786   0.00220  -0.0381   0.7237   1.0000
   2.500   0.4299   0.00852   0.00212  -0.0356   0.5590   1.0000
   2.750   0.4464   0.01012   0.00240  -0.0340   0.2727   1.0000
   3.000   0.4676   0.01157   0.00305  -0.0337   0.0747   1.0000
   3.250   0.4927   0.01235   0.00367  -0.0334   0.0374   1.0000
   3.500   0.5188   0.01291   0.00437  -0.0330   0.0319   1.0000
   3.750   0.5444   0.01357   0.00514  -0.0327   0.0280   1.0000
   4.000   0.5686   0.01454   0.00617  -0.0322   0.0235   1.0000
   4.250   0.5935   0.01545   0.00722  -0.0317   0.0215   1.0000
   4.500   0.6178   0.01675   0.00871  -0.0309   0.0195   1.0000
   4.750   0.6430   0.01761   0.00966  -0.0305   0.0157   1.0000
   5.000   0.6666   0.01974   0.01194  -0.0298   0.0133   1.0000
   5.250   0.6912   0.02249   0.01503  -0.0289   0.0123   1.0000
   5.500   0.7163   0.02479   0.01773  -0.0280   0.0116   1.0000
   5.750   0.7415   0.02649   0.01979  -0.0272   0.0094   1.0000
   6.000   0.7644   0.02916   0.02287  -0.0263   0.0081   1.0000
   6.250   0.7849   0.03280   0.02700  -0.0251   0.0077   1.0000
   6.500   0.8028   0.03706   0.03175  -0.0239   0.0075   1.0000
   6.750   0.8179   0.04193   0.03708  -0.0227   0.0075   1.0000
   7.000   0.8299   0.04715   0.04272  -0.0218   0.0077   1.0000
   7.250   0.8389   0.05256   0.04850  -0.0212   0.0079   1.0000
   7.500   0.8443   0.05806   0.05429  -0.0210   0.0081   1.0000
   7.750   0.8461   0.06357   0.06004  -0.0214   0.0084   1.0000
   8.000   0.8442   0.06902   0.06567  -0.0224   0.0086   1.0000
   8.250   0.8383   0.07444   0.07123  -0.0241   0.0088   1.0000
   8.500   0.8273   0.07946   0.07633  -0.0262   0.0089   1.0000
   8.750   0.8156   0.08566   0.08255  -0.0316   0.0090   1.0000
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