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NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-209 (naca63209-il)
Reynolds number: 200,000
Max Cl/Cd: 55.52 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca63209-il-200000-n5.txt
Download as CSV file: xf-naca63209-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-209                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4683   0.11179   0.10837  -0.0057   1.0000   0.0165
 -11.000  -0.4766   0.10488   0.10149  -0.0085   1.0000   0.0153
 -10.500  -0.5788   0.10057   0.09696  -0.0094   1.0000   0.0142
 -10.250  -0.5802   0.09577   0.09218  -0.0117   1.0000   0.0140
 -10.000  -0.5828   0.09050   0.08695  -0.0145   1.0000   0.0139
  -9.750  -0.5879   0.08450   0.08099  -0.0180   1.0000   0.0138
  -9.500  -0.5938   0.07812   0.07466  -0.0223   1.0000   0.0137
  -9.250  -0.6028   0.07032   0.06689  -0.0290   1.0000   0.0134
  -9.000  -0.6192   0.06346   0.05998  -0.0348   1.0000   0.0133
  -8.750  -0.6351   0.05841   0.05482  -0.0372   1.0000   0.0132
  -8.500  -0.6438   0.05315   0.04936  -0.0387   1.0000   0.0131
  -8.250  -0.6477   0.04788   0.04382  -0.0394   1.0000   0.0131
  -8.000  -0.6470   0.04263   0.03820  -0.0394   1.0000   0.0132
  -7.750  -0.6421   0.03745   0.03254  -0.0390   1.0000   0.0135
  -7.500  -0.6313   0.03322   0.02775  -0.0381   1.0000   0.0140
  -7.250  -0.6178   0.03001   0.02416  -0.0375   1.0000   0.0150
  -7.000  -0.5990   0.02858   0.02254  -0.0371   1.0000   0.0159
  -6.750  -0.5801   0.02663   0.02033  -0.0363   1.0000   0.0167
  -6.500  -0.5606   0.02452   0.01790  -0.0353   1.0000   0.0173
  -6.250  -0.5405   0.02268   0.01576  -0.0342   1.0000   0.0181
  -6.000  -0.5198   0.02115   0.01398  -0.0331   1.0000   0.0191
  -5.750  -0.4987   0.02032   0.01294  -0.0320   1.0000   0.0207
  -5.500  -0.4758   0.01886   0.01131  -0.0314   0.9986   0.0218
  -5.250  -0.4434   0.01722   0.00955  -0.0328   0.9922   0.0232
  -5.000  -0.4096   0.01619   0.00845  -0.0345   0.9861   0.0248
  -4.750  -0.3762   0.01542   0.00762  -0.0360   0.9789   0.0274
  -4.500  -0.3428   0.01471   0.00681  -0.0374   0.9715   0.0301
  -4.250  -0.3092   0.01385   0.00584  -0.0389   0.9642   0.0322
  -4.000  -0.2772   0.01310   0.00505  -0.0402   0.9552   0.0365
  -3.750  -0.2440   0.01265   0.00450  -0.0415   0.9469   0.0428
  -3.500  -0.2116   0.01212   0.00398  -0.0426   0.9381   0.0566
  -3.250  -0.1818   0.01141   0.00350  -0.0435   0.9280   0.1124
  -3.000  -0.1547   0.01012   0.00306  -0.0444   0.9179   0.3176
  -2.750  -0.1277   0.00939   0.00292  -0.0446   0.9080   0.4809
  -2.500  -0.1013   0.00911   0.00289  -0.0442   0.8971   0.5649
  -2.250  -0.0756   0.00894   0.00292  -0.0435   0.8864   0.6360
  -2.000  -0.0503   0.00888   0.00298  -0.0425   0.8762   0.6871
  -1.750  -0.0238   0.00886   0.00294  -0.0419   0.8661   0.7114
  -1.500   0.0028   0.00883   0.00287  -0.0414   0.8553   0.7269
  -1.250   0.0297   0.00881   0.00281  -0.0410   0.8450   0.7399
  -1.000   0.0566   0.00880   0.00275  -0.0406   0.8351   0.7522
  -0.750   0.0832   0.00879   0.00271  -0.0401   0.8248   0.7634
  -0.500   0.1099   0.00878   0.00268  -0.0397   0.8144   0.7745
  -0.250   0.1365   0.00878   0.00266  -0.0393   0.8045   0.7858
   0.000   0.1632   0.00879   0.00264  -0.0388   0.7948   0.7973
   0.250   0.1898   0.00880   0.00266  -0.0384   0.7842   0.8090
   0.500   0.2160   0.00881   0.00268  -0.0379   0.7743   0.8203
   0.750   0.2421   0.00883   0.00270  -0.0373   0.7646   0.8319
   1.000   0.2682   0.00885   0.00274  -0.0368   0.7541   0.8439
   1.250   0.2941   0.00888   0.00280  -0.0362   0.7437   0.8562
   1.500   0.3199   0.00890   0.00286  -0.0355   0.7334   0.8689
   1.750   0.3453   0.00894   0.00291  -0.0348   0.7230   0.8822
   2.000   0.3708   0.00896   0.00298  -0.0341   0.7110   0.8960
   2.250   0.3965   0.00898   0.00306  -0.0334   0.6979   0.9107
   2.500   0.4227   0.00901   0.00311  -0.0328   0.6823   0.9263
   2.750   0.4503   0.00903   0.00313  -0.0326   0.6586   0.9433
   3.000   0.4796   0.00911   0.00311  -0.0326   0.6127   0.9624
   3.250   0.5112   0.00934   0.00309  -0.0334   0.5429   0.9913
   3.500   0.5369   0.00967   0.00322  -0.0331   0.4863   1.0000
   3.750   0.5599   0.01025   0.00343  -0.0325   0.3967   1.0000
   4.000   0.5784   0.01158   0.00395  -0.0317   0.2253   1.0000
   4.250   0.5988   0.01287   0.00459  -0.0313   0.1007   1.0000
   4.500   0.6224   0.01372   0.00518  -0.0310   0.0543   1.0000
   4.750   0.6473   0.01434   0.00576  -0.0308   0.0408   1.0000
   5.000   0.6721   0.01499   0.00644  -0.0305   0.0342   1.0000
   5.250   0.6968   0.01562   0.00719  -0.0301   0.0304   1.0000
   5.500   0.7205   0.01641   0.00804  -0.0297   0.0275   1.0000
   5.750   0.7415   0.01768   0.00935  -0.0289   0.0253   1.0000
   6.000   0.7650   0.01858   0.01034  -0.0283   0.0245   1.0000
   6.250   0.7885   0.01955   0.01140  -0.0277   0.0234   1.0000
   6.500   0.8124   0.02045   0.01243  -0.0273   0.0217   1.0000
   6.750   0.8359   0.02150   0.01357  -0.0268   0.0204   1.0000
   7.000   0.8593   0.02273   0.01491  -0.0262   0.0195   1.0000
   7.250   0.8824   0.02408   0.01637  -0.0257   0.0187   1.0000
   7.500   0.9050   0.02571   0.01814  -0.0252   0.0180   1.0000
   7.750   0.9250   0.02855   0.02119  -0.0245   0.0169   1.0000
   8.000   0.9472   0.02967   0.02263  -0.0238   0.0160   1.0000
   8.250   0.9667   0.03190   0.02525  -0.0229   0.0153   1.0000
   8.500   0.9832   0.03467   0.02843  -0.0217   0.0147   1.0000
   8.750   0.9961   0.03784   0.03203  -0.0204   0.0142   1.0000
   9.000   1.0048   0.04143   0.03605  -0.0188   0.0138   1.0000
   9.250   1.0109   0.04475   0.03974  -0.0173   0.0134   1.0000
   9.500   1.0198   0.04670   0.04186  -0.0163   0.0127   1.0000
   9.750   1.0232   0.04915   0.04453  -0.0150   0.0123   1.0000
  10.000   1.0244   0.05134   0.04688  -0.0137   0.0119   1.0000
  10.250   1.0159   0.05396   0.04965  -0.0118   0.0116   1.0000
  10.500   0.9993   0.05767   0.05359  -0.0102   0.0116   1.0000
  10.750   0.9801   0.06196   0.05806  -0.0102   0.0115   1.0000
  11.000   0.9605   0.06710   0.06340  -0.0119   0.0115   1.0000
  11.250   0.9398   0.07344   0.06993  -0.0153   0.0116   1.0000
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