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NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-206 (naca63206-il)
Reynolds number: 100,000
Max Cl/Cd: 43.07 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca63206-il-100000.txt
Download as CSV file: xf-naca63206-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5595   0.08681   0.08215  -0.0092   1.0000   0.0770
  -7.500  -0.5617   0.08245   0.07784  -0.0167   1.0000   0.0795
  -7.250  -0.5652   0.07844   0.07361  -0.0278   1.0000   0.0809
  -7.000  -0.5511   0.07336   0.06869  -0.0216   1.0000   0.0851
  -6.750  -0.5426   0.06941   0.06470  -0.0244   1.0000   0.0908
  -6.500  -0.5361   0.06428   0.05939  -0.0302   1.0000   0.0962
  -6.250  -0.5229   0.06089   0.05603  -0.0295   1.0000   0.1034
  -6.000  -0.5111   0.05659   0.05161  -0.0317   1.0000   0.1121
  -5.750  -0.4971   0.05280   0.04768  -0.0334   1.0000   0.1248
  -5.500  -0.4819   0.04941   0.04422  -0.0339   1.0000   0.1401
  -5.250  -0.4665   0.04613   0.04078  -0.0349   1.0000   0.1641
  -5.000  -0.4513   0.04327   0.03793  -0.0343   1.0000   0.1919
  -4.250  -0.3561   0.03103   0.02355  -0.0384   1.0000   0.1206
  -4.000  -0.3224   0.02582   0.01764  -0.0371   1.0000   0.0733
  -3.750  -0.2939   0.02329   0.01455  -0.0359   1.0000   0.0640
  -3.500  -0.2673   0.02097   0.01181  -0.0349   1.0000   0.0608
  -3.250  -0.2415   0.01919   0.00981  -0.0338   1.0000   0.0616
  -3.000  -0.2164   0.01798   0.00839  -0.0328   1.0000   0.0688
  -2.750  -0.1928   0.01631   0.00684  -0.0317   1.0000   0.0727
  -2.500  -0.1691   0.01520   0.00572  -0.0306   1.0000   0.0798
  -2.250  -0.1451   0.01403   0.00462  -0.0299   1.0000   0.1000
  -2.000  -0.1389   0.01063   0.00424  -0.0250   1.0000   0.7596
  -1.750  -0.1021   0.01022   0.00390  -0.0226   1.0000   1.0000
  -1.500  -0.0853   0.01013   0.00356  -0.0215   1.0000   1.0000
  -1.250  -0.0639   0.01011   0.00331  -0.0210   1.0000   1.0000
  -1.000  -0.0413   0.01013   0.00315  -0.0207   1.0000   1.0000
  -0.750  -0.0182   0.01019   0.00304  -0.0205   1.0000   1.0000
  -0.500   0.0048   0.01028   0.00300  -0.0202   1.0000   1.0000
  -0.250   0.0276   0.01041   0.00299  -0.0199   1.0000   1.0000
   0.000   0.0502   0.01056   0.00306  -0.0197   1.0000   1.0000
   0.250   0.0725   0.01075   0.00318  -0.0194   1.0000   1.0000
   0.500   0.0944   0.01098   0.00336  -0.0191   1.0000   1.0000
   0.750   0.1160   0.01124   0.00360  -0.0188   1.0000   1.0000
   1.000   0.1373   0.01154   0.00389  -0.0186   1.0000   1.0000
   1.250   0.1581   0.01188   0.00426  -0.0184   1.0000   1.0000
   1.500   0.1829   0.01228   0.00469  -0.0191   0.9981   1.0000
   1.750   0.2319   0.01278   0.00530  -0.0242   0.9858   1.0000
   2.000   0.2807   0.01322   0.00589  -0.0292   0.9731   1.0000
   2.250   0.3307   0.01357   0.00651  -0.0342   0.9592   1.0000
   2.500   0.3837   0.01378   0.00699  -0.0393   0.9440   1.0000
   2.750   0.4717   0.01240   0.00613  -0.0464   0.8905   1.0000
   3.000   0.4957   0.01151   0.00525  -0.0406   0.7976   1.0000
   3.250   0.4980   0.01263   0.00462  -0.0316   0.3809   1.0000
   3.500   0.5105   0.01607   0.00628  -0.0295   0.0905   1.0000
   3.750   0.5331   0.01750   0.00773  -0.0283   0.0775   1.0000
   4.000   0.5564   0.01901   0.00916  -0.0273   0.0656   1.0000
   4.250   0.5821   0.02071   0.01084  -0.0265   0.0601   1.0000
   4.500   0.6093   0.02319   0.01331  -0.0259   0.0580   1.0000
   4.750   0.6379   0.02555   0.01593  -0.0251   0.0583   1.0000
   5.000   0.6659   0.02807   0.01884  -0.0241   0.0589   1.0000
   5.250   0.6900   0.03159   0.02286  -0.0233   0.0564   1.0000
   5.500   0.7181   0.03488   0.02699  -0.0214   0.0671   1.0000
   8.250   0.7185   0.08362   0.07965  -0.0285   0.1186   1.0000
   8.500   0.7072   0.08903   0.08502  -0.0316   0.1147   1.0000
   8.750   0.7212   0.09375   0.08975  -0.0290   0.1084   1.0000
   9.000   0.7001   0.09958   0.09551  -0.0346   0.1071   1.0000
   9.250   0.6885   0.10486   0.10076  -0.0383   0.1034   1.0000
   9.500   0.7148   0.10941   0.10534  -0.0334   0.0958   1.0000
   9.750   0.6969   0.11464   0.11052  -0.0386   0.0952   1.0000
  10.000   0.6823   0.11943   0.11526  -0.0432   0.0931   1.0000
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