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NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-206 (naca63206-il)
Reynolds number: 500,000
Max Cl/Cd: 58.7 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca63206-il-500000-n5.txt
Download as CSV file: xf-naca63206-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5487   0.08243   0.08020  -0.0075   1.0000   0.0033
  -7.750  -0.5516   0.07818   0.07599  -0.0100   1.0000   0.0032
  -7.500  -0.5520   0.07360   0.07143  -0.0145   1.0000   0.0032
  -7.250  -0.5481   0.06762   0.06543  -0.0212   1.0000   0.0031
  -7.000  -0.5411   0.06199   0.05974  -0.0262   1.0000   0.0030
  -6.750  -0.5317   0.05651   0.05415  -0.0300   1.0000   0.0030
  -6.500  -0.5196   0.05123   0.04873  -0.0328   1.0000   0.0029
  -6.250  -0.5052   0.04608   0.04340  -0.0349   1.0000   0.0028
  -6.000  -0.4886   0.04087   0.03796  -0.0363   1.0000   0.0027
  -5.750  -0.4700   0.03590   0.03271  -0.0370   1.0000   0.0026
  -5.500  -0.4497   0.03095   0.02741  -0.0371   1.0000   0.0026
  -5.250  -0.4279   0.02590   0.02194  -0.0368   1.0000   0.0025
  -5.000  -0.4047   0.02042   0.01588  -0.0359   1.0000   0.0024
  -4.750  -0.3803   0.01531   0.01007  -0.0348   1.0000   0.0024
  -4.500  -0.3560   0.01242   0.00663  -0.0339   1.0000   0.0026
  -4.250  -0.3316   0.01095   0.00491  -0.0332   1.0000   0.0029
  -4.000  -0.2993   0.01014   0.00402  -0.0343   0.9963   0.0042
  -3.750  -0.2663   0.01001   0.00388  -0.0356   0.9914   0.0072
  -3.500  -0.2330   0.01008   0.00398  -0.0371   0.9863   0.0103
  -3.250  -0.2004   0.01002   0.00396  -0.0384   0.9799   0.0149
  -3.000  -0.1674   0.00927   0.00309  -0.0396   0.9735   0.0148
  -2.750  -0.1342   0.00873   0.00243  -0.0409   0.9660   0.0152
  -2.500  -0.1017   0.00831   0.00185  -0.0419   0.9567   0.0163
  -2.250  -0.0697   0.00808   0.00155  -0.0428   0.9465   0.0191
  -2.000  -0.0391   0.00786   0.00132  -0.0433   0.9348   0.0301
  -1.750  -0.0102   0.00761   0.00115  -0.0436   0.9218   0.0644
  -1.500   0.0174   0.00718   0.00100  -0.0438   0.9081   0.1609
  -1.250   0.0426   0.00584   0.00087  -0.0443   0.8940   0.5274
  -1.000   0.0662   0.00525   0.00097  -0.0434   0.8797   0.7265
  -0.750   0.0918   0.00515   0.00095  -0.0426   0.8654   0.7710
  -0.500   0.1179   0.00513   0.00093  -0.0421   0.8512   0.7953
  -0.250   0.1441   0.00512   0.00092  -0.0416   0.8372   0.8149
   0.000   0.1705   0.00513   0.00091  -0.0412   0.8233   0.8313
   0.500   0.2227   0.00516   0.00094  -0.0401   0.7954   0.8635
   0.750   0.2483   0.00518   0.00096  -0.0395   0.7787   0.8805
   1.000   0.2734   0.00522   0.00099  -0.0387   0.7589   0.8987
   1.250   0.2977   0.00528   0.00101  -0.0377   0.7304   0.9181
   1.500   0.3211   0.00547   0.00100  -0.0366   0.6733   0.9401
   1.750   0.3462   0.00596   0.00100  -0.0360   0.5473   0.9660
   2.000   0.3730   0.00693   0.00123  -0.0365   0.3485   1.0000
   2.250   0.3975   0.00776   0.00150  -0.0364   0.2040   1.0000
   2.500   0.4225   0.00855   0.00181  -0.0364   0.0800   1.0000
   2.750   0.4488   0.00906   0.00210  -0.0363   0.0294   1.0000
   3.000   0.4760   0.00939   0.00245  -0.0362   0.0210   1.0000
   3.250   0.5032   0.00970   0.00281  -0.0362   0.0184   1.0000
   3.500   0.5301   0.01005   0.00319  -0.0361   0.0162   1.0000
   3.750   0.5566   0.01049   0.00370  -0.0359   0.0150   1.0000
   4.000   0.5822   0.01123   0.00462  -0.0356   0.0133   1.0000
   4.250   0.6075   0.01199   0.00547  -0.0352   0.0120   1.0000
   4.500   0.6336   0.01256   0.00612  -0.0350   0.0111   1.0000
   4.750   0.6585   0.01361   0.00730  -0.0344   0.0104   1.0000
   5.000   0.6843   0.01434   0.00813  -0.0341   0.0091   1.0000
   5.250   0.7103   0.01490   0.00878  -0.0339   0.0075   1.0000
   5.500   0.7366   0.01525   0.00916  -0.0338   0.0059   1.0000
   5.750   0.7583   0.01827   0.01255  -0.0326   0.0048   1.0000
   6.000   0.7818   0.02074   0.01538  -0.0316   0.0045   1.0000
   6.250   0.8057   0.02257   0.01749  -0.0310   0.0038   1.0000
   6.500   0.8296   0.02391   0.01903  -0.0305   0.0029   1.0000
   6.750   0.8547   0.02396   0.01923  -0.0305   0.0023   1.0000
   7.000   0.8769   0.02570   0.02123  -0.0300   0.0020   1.0000
   7.250   0.8879   0.03331   0.02957  -0.0277   0.0018   1.0000
   7.500   0.8866   0.04432   0.04132  -0.0252   0.0016   1.0000
   7.750   0.8932   0.05033   0.04765  -0.0244   0.0015   1.0000
   8.000   0.8958   0.05644   0.05402  -0.0242   0.0015   1.0000
   8.250   0.8934   0.06254   0.06033  -0.0245   0.0015   1.0000
   8.500   0.8860   0.06859   0.06655  -0.0257   0.0015   1.0000
   8.750   0.8740   0.07407   0.07213  -0.0272   0.0015   1.0000
   9.000   0.8555   0.07974   0.07786  -0.0306   0.0015   1.0000
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