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S6063 7.05% (s6063-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S6063 7.05% (s6063-il)
Reynolds number: 200,000
Max Cl/Cd: 53.43 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s6063-il-200000-n5.txt
Download as CSV file: xf-s6063-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6063 7.05%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.5425   0.06315   0.05978  -0.0260   1.0000   0.0182
  -7.000  -0.5360   0.05801   0.05455  -0.0291   1.0000   0.0169
  -6.750  -0.5290   0.05046   0.04677  -0.0329   1.0000   0.0150
  -6.500  -0.5163   0.04247   0.03833  -0.0348   1.0000   0.0125
  -6.250  -0.5030   0.03788   0.03342  -0.0355   1.0000   0.0122
  -6.000  -0.4873   0.03359   0.02874  -0.0356   1.0000   0.0118
  -5.750  -0.4695   0.02975   0.02447  -0.0353   1.0000   0.0115
  -5.500  -0.4501   0.02648   0.02074  -0.0346   1.0000   0.0113
  -5.250  -0.4296   0.02366   0.01742  -0.0336   1.0000   0.0111
  -5.000  -0.4083   0.02135   0.01470  -0.0325   1.0000   0.0110
  -4.750  -0.3866   0.01945   0.01245  -0.0313   1.0000   0.0110
  -4.500  -0.3647   0.01788   0.01062  -0.0301   1.0000   0.0112
  -4.250  -0.3429   0.01658   0.00912  -0.0289   1.0000   0.0114
  -4.000  -0.3214   0.01551   0.00791  -0.0276   1.0000   0.0118
  -3.750  -0.2938   0.01476   0.00704  -0.0277   0.9974   0.0129
  -3.500  -0.2604   0.01355   0.00571  -0.0292   0.9916   0.0145
  -3.250  -0.2252   0.01282   0.00486  -0.0308   0.9861   0.0154
  -3.000  -0.1902   0.01227   0.00418  -0.0323   0.9801   0.0167
  -2.750  -0.1552   0.01183   0.00362  -0.0338   0.9736   0.0193
  -2.500  -0.1218   0.01121   0.00313  -0.0351   0.9660   0.0512
  -2.250  -0.0897   0.01019   0.00284  -0.0367   0.9585   0.2153
  -2.000  -0.0596   0.00957   0.00266  -0.0375   0.9490   0.3373
  -1.750  -0.0335   0.00858   0.00262  -0.0375   0.9396   0.5742
  -1.500  -0.0082   0.00806   0.00260  -0.0364   0.9300   0.7213
  -1.250   0.0166   0.00784   0.00257  -0.0350   0.9185   0.8035
  -1.000   0.0441   0.00770   0.00252  -0.0342   0.9073   0.8716
  -0.750   0.0794   0.00762   0.00242  -0.0351   0.8968   0.9255
  -0.500   0.1205   0.00755   0.00227  -0.0375   0.8858   0.9655
  -0.250   0.1614   0.00749   0.00212  -0.0401   0.8732   0.9941
   0.000   0.1893   0.00750   0.00204  -0.0400   0.8573   1.0000
   0.250   0.2133   0.00753   0.00199  -0.0390   0.8402   1.0000
   0.500   0.2376   0.00757   0.00194  -0.0381   0.8223   1.0000
   0.750   0.2621   0.00762   0.00191  -0.0372   0.8040   1.0000
   1.000   0.2870   0.00769   0.00190  -0.0364   0.7838   1.0000
   1.250   0.3120   0.00777   0.00190  -0.0356   0.7629   1.0000
   1.500   0.3372   0.00786   0.00193  -0.0348   0.7394   1.0000
   1.750   0.3625   0.00797   0.00195  -0.0341   0.7138   1.0000
   2.000   0.3878   0.00811   0.00200  -0.0334   0.6861   1.0000
   2.250   0.4132   0.00827   0.00207  -0.0327   0.6564   1.0000
   2.500   0.4385   0.00846   0.00218  -0.0321   0.6245   1.0000
   2.750   0.4638   0.00868   0.00229  -0.0314   0.5881   1.0000
   3.000   0.4866   0.00914   0.00238  -0.0304   0.5094   1.0000
   3.250   0.5095   0.00970   0.00254  -0.0295   0.4226   1.0000
   3.500   0.5342   0.01012   0.00280  -0.0291   0.3701   1.0000
   3.750   0.5584   0.01066   0.00308  -0.0286   0.3043   1.0000
   4.000   0.5811   0.01150   0.00345  -0.0281   0.2056   1.0000
   4.250   0.6044   0.01233   0.00391  -0.0277   0.1252   1.0000
   4.500   0.6257   0.01363   0.00465  -0.0272   0.0281   1.0000
   4.750   0.6506   0.01425   0.00525  -0.0267   0.0192   1.0000
   5.000   0.6759   0.01477   0.00588  -0.0263   0.0174   1.0000
   5.250   0.7008   0.01537   0.00661  -0.0258   0.0163   1.0000
   5.500   0.7254   0.01605   0.00742  -0.0253   0.0155   1.0000
   5.750   0.7493   0.01684   0.00833  -0.0247   0.0149   1.0000
   6.000   0.7724   0.01776   0.00941  -0.0240   0.0145   1.0000
   6.250   0.7948   0.01882   0.01058  -0.0232   0.0142   1.0000
   6.500   0.8168   0.02004   0.01190  -0.0224   0.0140   1.0000
   6.750   0.8376   0.02168   0.01364  -0.0215   0.0132   1.0000
   7.000   0.8592   0.02338   0.01550  -0.0207   0.0126   1.0000
   7.250   0.8818   0.02480   0.01712  -0.0199   0.0122   1.0000
   7.500   0.9034   0.02661   0.01919  -0.0191   0.0120   1.0000
   7.750   0.9239   0.02870   0.02158  -0.0181   0.0119   1.0000
   8.000   0.9427   0.03110   0.02439  -0.0171   0.0117   1.0000
   8.250   0.9589   0.03386   0.02756  -0.0159   0.0116   1.0000
   8.500   0.9721   0.03694   0.03106  -0.0146   0.0116   1.0000
   8.750   0.9814   0.04038   0.03493  -0.0132   0.0117   1.0000
   9.000   0.9863   0.04413   0.03910  -0.0117   0.0117   1.0000
   9.250   0.9864   0.04807   0.04341  -0.0103   0.0118   1.0000
   9.500   0.9810   0.05211   0.04778  -0.0089   0.0119   1.0000
   9.750   0.9692   0.05597   0.05190  -0.0074   0.0120   1.0000
  10.000   0.9524   0.05974   0.05586  -0.0065   0.0120   1.0000
  10.250   0.9343   0.06427   0.06056  -0.0077   0.0121   1.0000
  10.500   0.9156   0.07005   0.06649  -0.0114   0.0121   1.0000
  10.750   0.8966   0.07764   0.07421  -0.0176   0.0122   1.0000
  11.000   0.8776   0.08760   0.08427  -0.0257   0.0123   1.0000
  11.250   0.8593   0.09916   0.09586  -0.0333   0.0125   1.0000
  11.500   0.8479   0.10798   0.10465  -0.0379   0.0127   1.0000
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