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NACA 63-210 AIRFOIL (n63210-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-210 AIRFOIL (n63210-il)
Reynolds number: 500,000
Max Cl/Cd: 67.69 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63210-il-500000.txt
Download as CSV file: xf-n63210-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-210 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6413   0.06088   0.05855  -0.0411   1.0000   0.0149
  -9.500  -0.6635   0.05575   0.05331  -0.0438   1.0000   0.0150
  -9.250  -0.6833   0.05158   0.04900  -0.0437   1.0000   0.0148
  -9.000  -0.6996   0.04596   0.04312  -0.0435   1.0000   0.0141
  -8.750  -0.7056   0.04060   0.03741  -0.0427   1.0000   0.0145
  -8.500  -0.7083   0.03497   0.03132  -0.0414   1.0000   0.0147
  -8.250  -0.7045   0.03008   0.02589  -0.0395   1.0000   0.0153
  -8.000  -0.6898   0.02839   0.02378  -0.0380   1.0000   0.0162
  -7.750  -0.6830   0.02383   0.01889  -0.0364   1.0000   0.0174
  -7.500  -0.6637   0.02328   0.01833  -0.0355   1.0000   0.0185
  -7.250  -0.6457   0.02222   0.01710  -0.0341   1.0000   0.0201
  -7.000  -0.6268   0.02176   0.01646  -0.0325   1.0000   0.0216
  -6.750  -0.6108   0.01907   0.01352  -0.0314   0.9995   0.0237
  -6.500  -0.5745   0.01857   0.01301  -0.0339   0.9961   0.0259
  -6.250  -0.5383   0.01760   0.01191  -0.0359   0.9926   0.0276
  -6.000  -0.5017   0.01730   0.01147  -0.0379   0.9884   0.0293
  -5.750  -0.4661   0.01569   0.00970  -0.0399   0.9850   0.0303
  -5.500  -0.4303   0.01443   0.00837  -0.0418   0.9816   0.0303
  -5.250  -0.3972   0.01342   0.00731  -0.0431   0.9749   0.0304
  -5.000  -0.3624   0.01253   0.00636  -0.0448   0.9698   0.0305
  -4.750  -0.3335   0.01175   0.00554  -0.0452   0.9590   0.0311
  -4.500  -0.3060   0.01115   0.00488  -0.0453   0.9471   0.0315
  -4.250  -0.2799   0.01067   0.00434  -0.0449   0.9336   0.0318
  -4.000  -0.2545   0.01024   0.00383  -0.0444   0.9193   0.0324
  -3.750  -0.2289   0.00989   0.00341  -0.0439   0.9051   0.0332
  -3.500  -0.2031   0.00960   0.00305  -0.0433   0.8921   0.0347
  -3.250  -0.1768   0.00939   0.00274  -0.0429   0.8804   0.0368
  -3.000  -0.1502   0.00921   0.00247  -0.0425   0.8699   0.0413
  -2.750  -0.1241   0.00863   0.00216  -0.0424   0.8594   0.1161
  -2.500  -0.0998   0.00731   0.00179  -0.0428   0.8494   0.3751
  -2.250  -0.0739   0.00678   0.00171  -0.0428   0.8405   0.5113
  -2.000  -0.0464   0.00671   0.00175  -0.0427   0.8310   0.5724
  -1.750  -0.0186   0.00665   0.00172  -0.0426   0.8221   0.6050
  -1.500   0.0084   0.00654   0.00168  -0.0423   0.8137   0.6377
  -1.250   0.0359   0.00646   0.00171  -0.0421   0.8043   0.6655
  -1.000   0.0636   0.00646   0.00171  -0.0420   0.7957   0.6844
  -0.750   0.0916   0.00645   0.00170  -0.0419   0.7868   0.6990
  -0.500   0.1194   0.00645   0.00171  -0.0418   0.7776   0.7153
  -0.250   0.1469   0.00646   0.00172  -0.0416   0.7693   0.7318
   0.000   0.1751   0.00646   0.00174  -0.0415   0.7597   0.7434
   0.250   0.2032   0.00648   0.00174  -0.0415   0.7510   0.7541
   0.500   0.2309   0.00649   0.00176  -0.0414   0.7420   0.7643
   0.750   0.2588   0.00649   0.00180  -0.0413   0.7319   0.7751
   1.000   0.2863   0.00650   0.00180  -0.0411   0.7178   0.7868
   1.250   0.3137   0.00653   0.00182  -0.0409   0.7016   0.7990
   1.500   0.3408   0.00655   0.00185  -0.0406   0.6869   0.8107
   1.750   0.3675   0.00659   0.00187  -0.0402   0.6682   0.8225
   2.000   0.3941   0.00663   0.00191  -0.0398   0.6451   0.8346
   2.250   0.4202   0.00671   0.00194  -0.0393   0.6163   0.8467
   2.500   0.4460   0.00684   0.00199  -0.0388   0.5823   0.8591
   2.750   0.4714   0.00700   0.00207  -0.0382   0.5432   0.8717
   3.000   0.4948   0.00731   0.00219  -0.0373   0.4795   0.8841
   3.250   0.5152   0.00803   0.00243  -0.0360   0.3570   0.8974
   3.500   0.5309   0.00948   0.00299  -0.0345   0.1533   0.9124
   3.750   0.5490   0.01046   0.00348  -0.0329   0.0434   0.9285
   4.000   0.5704   0.01072   0.00375  -0.0315   0.0344   0.9460
   4.250   0.5954   0.01094   0.00404  -0.0308   0.0318   0.9672
   4.500   0.6295   0.01126   0.00441  -0.0323   0.0304   1.0000
   4.750   0.6572   0.01167   0.00485  -0.0325   0.0293   1.0000
   5.000   0.6841   0.01214   0.00537  -0.0326   0.0283   1.0000
   5.250   0.7103   0.01267   0.00593  -0.0326   0.0277   1.0000
   5.500   0.7357   0.01328   0.00658  -0.0324   0.0272   1.0000
   5.750   0.7604   0.01395   0.00730  -0.0320   0.0269   1.0000
   6.000   0.7846   0.01471   0.00812  -0.0316   0.0268   1.0000
   6.250   0.8085   0.01550   0.00896  -0.0311   0.0265   1.0000
   6.500   0.8321   0.01637   0.00986  -0.0306   0.0261   1.0000
   6.750   0.8559   0.01733   0.01088  -0.0301   0.0260   1.0000
   7.000   0.8799   0.01840   0.01202  -0.0296   0.0260   1.0000
   7.250   0.9042   0.01961   0.01332  -0.0292   0.0260   1.0000
   7.500   0.9286   0.02095   0.01475  -0.0287   0.0258   1.0000
   7.750   0.9516   0.02325   0.01714  -0.0284   0.0247   1.0000
   8.000   0.9733   0.02522   0.01936  -0.0278   0.0236   1.0000
   8.250   0.9963   0.02626   0.02058  -0.0272   0.0229   1.0000
   8.500   1.0180   0.02761   0.02214  -0.0265   0.0220   1.0000
   8.750   1.0395   0.02843   0.02307  -0.0259   0.0204   1.0000
   9.000   1.0607   0.02898   0.02362  -0.0256   0.0192   1.0000
   9.250   1.0686   0.03425   0.02922  -0.0243   0.0177   1.0000
   9.500   1.0849   0.03457   0.02983  -0.0229   0.0167   1.0000
   9.750   1.0979   0.03656   0.03211  -0.0214   0.0155   1.0000
  10.000   1.1087   0.03849   0.03426  -0.0200   0.0146   1.0000
  10.250   1.1214   0.03969   0.03555  -0.0189   0.0140   1.0000
  10.500   1.1359   0.04038   0.03621  -0.0182   0.0134   1.0000
  10.750   1.1331   0.04376   0.03978  -0.0162   0.0130   1.0000
  11.000   1.1097   0.04858   0.04493  -0.0124   0.0128   1.0000
  11.250   1.0798   0.05343   0.05006  -0.0094   0.0127   1.0000
  11.500   1.0602   0.05744   0.05428  -0.0084   0.0127   1.0000
  11.750   1.0377   0.06231   0.05935  -0.0088   0.0127   1.0000
  12.000   1.0131   0.06813   0.06537  -0.0108   0.0127   1.0000
  12.250   1.0034   0.07239   0.06975  -0.0130   0.0127   1.0000
  12.500   0.9846   0.07874   0.07626  -0.0169   0.0128   1.0000
  12.750   0.9712   0.08503   0.08268  -0.0214   0.0129   1.0000
  13.000   0.8258   0.14073   0.13865  -0.0537   0.0195   1.0000
  13.250   0.8288   0.14514   0.14306  -0.0560   0.0190   1.0000
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