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NACA 63-212 AIRFOIL (n63212-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-212 AIRFOIL (n63212-il)
Reynolds number: 50,000
Max Cl/Cd: 33.46 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63212-il-50000.txt
Download as CSV file: xf-n63212-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-212 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4822   0.10997   0.10290  -0.0018   1.0000   0.3363
  -9.250  -0.4630   0.10475   0.09767  -0.0023   1.0000   0.3392
  -9.000  -0.5882   0.08212   0.07542  -0.0339   1.0000   0.1705
  -8.750  -0.5953   0.07455   0.06785  -0.0372   1.0000   0.1512
  -8.500  -0.6355   0.06726   0.06038  -0.0413   1.0000   0.1385
  -8.250  -0.6627   0.06099   0.05367  -0.0428   1.0000   0.1286
  -8.000  -0.6596   0.05687   0.04928  -0.0424   1.0000   0.1251
  -7.750  -0.6542   0.05285   0.04505  -0.0417   1.0000   0.1230
  -7.500  -0.6492   0.04901   0.04086  -0.0407   1.0000   0.1205
  -7.250  -0.6428   0.04534   0.03674  -0.0393   1.0000   0.1177
  -7.000  -0.6336   0.04209   0.03295  -0.0376   1.0000   0.1156
  -6.750  -0.6204   0.03927   0.02970  -0.0358   1.0000   0.1152
  -6.500  -0.6045   0.03677   0.02693  -0.0342   1.0000   0.1161
  -6.250  -0.5879   0.03469   0.02467  -0.0326   1.0000   0.1199
  -6.000  -0.5712   0.03286   0.02247  -0.0308   1.0000   0.1253
  -5.750  -0.5526   0.03084   0.02041  -0.0291   1.0000   0.1314
  -5.500  -0.5332   0.02927   0.01866  -0.0273   1.0000   0.1407
  -5.250  -0.5148   0.02770   0.01717  -0.0254   1.0000   0.1554
  -5.000  -0.4983   0.02612   0.01585  -0.0233   1.0000   0.1775
  -4.750  -0.4838   0.02451   0.01451  -0.0212   1.0000   0.2126
  -4.500  -0.4750   0.02162   0.01289  -0.0189   1.0000   0.3211
  -4.250  -0.4838   0.02190   0.01482  -0.0085   1.0000   0.6065
  -4.000  -0.4819   0.02333   0.01622  -0.0003   1.0000   0.6696
  -3.750  -0.4787   0.02453   0.01738   0.0076   1.0000   0.7108
  -3.500  -0.4758   0.02543   0.01817   0.0150   1.0000   0.7504
  -3.250  -0.4718   0.02636   0.01903   0.0230   1.0000   0.7880
  -3.000  -0.4638   0.02697   0.01954   0.0297   1.0000   0.8279
  -2.750  -0.4325   0.02768   0.02000   0.0326   1.0000   0.8696
  -2.500  -0.3735   0.02796   0.01988   0.0283   1.0000   0.9024
  -2.250  -0.2948   0.02786   0.01937   0.0186   1.0000   0.9245
  -2.000  -0.2427   0.02751   0.01873   0.0125   1.0000   0.9435
  -1.750  -0.1863   0.02714   0.01812   0.0052   1.0000   0.9603
  -1.500  -0.1303   0.02677   0.01755  -0.0025   1.0000   0.9762
  -1.250  -0.0766   0.02646   0.01707  -0.0100   1.0000   0.9920
  -1.000  -0.0532   0.02628   0.01681  -0.0126   1.0000   1.0000
  -0.750  -0.0627   0.02611   0.01663  -0.0095   1.0000   1.0000
  -0.500  -0.0728   0.02587   0.01635  -0.0063   1.0000   1.0000
  -0.250  -0.0836   0.02555   0.01601  -0.0030   1.0000   1.0000
   0.000  -0.0949   0.02514   0.01558   0.0005   1.0000   1.0000
   0.250  -0.0765   0.02525   0.01562  -0.0012   0.9931   1.0000
   0.500  -0.0461   0.02567   0.01596  -0.0047   0.9822   1.0000
   0.750  -0.0174   0.02615   0.01635  -0.0076   0.9713   1.0000
   1.000   0.0070   0.02657   0.01670  -0.0096   0.9606   1.0000
   1.250   0.0369   0.02720   0.01726  -0.0123   0.9503   1.0000
   1.500   0.0739   0.02807   0.01807  -0.0160   0.9403   1.0000
   1.750   0.1043   0.02880   0.01876  -0.0185   0.9296   1.0000
   2.000   0.1338   0.02960   0.01952  -0.0207   0.9191   1.0000
   2.250   0.1692   0.03056   0.02047  -0.0237   0.9087   1.0000
   2.500   0.2036   0.03151   0.02144  -0.0264   0.8977   1.0000
   2.750   0.2289   0.03237   0.02231  -0.0276   0.8862   1.0000
   3.000   0.2583   0.03334   0.02332  -0.0294   0.8747   1.0000
   3.250   0.2922   0.03438   0.02443  -0.0317   0.8627   1.0000
   3.500   0.3305   0.03545   0.02559  -0.0346   0.8502   1.0000
   3.750   0.3557   0.03641   0.02662  -0.0354   0.8366   1.0000
   4.000   0.3829   0.03741   0.02774  -0.0364   0.8223   1.0000
   4.250   0.4130   0.03841   0.02886  -0.0376   0.8070   1.0000
   4.500   0.4464   0.03934   0.02995  -0.0391   0.7907   1.0000
   4.750   0.4890   0.04009   0.03093  -0.0412   0.7730   1.0000
   5.000   0.5088   0.04097   0.03195  -0.0405   0.7529   1.0000
   5.250   0.5487   0.04130   0.03253  -0.0414   0.7304   1.0000
   5.500   0.5900   0.04120   0.03275  -0.0417   0.7052   1.0000
   5.750   0.6551   0.03896   0.03096  -0.0416   0.6729   1.0000
   6.000   0.7400   0.03185   0.02440  -0.0368   0.6265   1.0000
   6.250   0.7874   0.02666   0.01947  -0.0303   0.5698   1.0000
   6.500   0.8006   0.02393   0.01651  -0.0221   0.4429   1.0000
   6.750   0.7898   0.02631   0.01691  -0.0153   0.2619   1.0000
   7.000   0.7998   0.02913   0.01891  -0.0128   0.2017   1.0000
   7.250   0.8263   0.03143   0.02091  -0.0121   0.1687   1.0000
   7.500   0.8596   0.03374   0.02314  -0.0121   0.1489   1.0000
   7.750   0.8907   0.03618   0.02562  -0.0121   0.1355   1.0000
   8.000   0.9229   0.03919   0.02859  -0.0124   0.1278   1.0000
   8.250   0.9437   0.04176   0.03167  -0.0114   0.1218   1.0000
   8.500   0.9680   0.04471   0.03470  -0.0111   0.1165   1.0000
   8.750   0.9902   0.04877   0.03897  -0.0108   0.1147   1.0000
   9.000   1.0031   0.05238   0.04309  -0.0095   0.1143   1.0000
   9.250   1.0108   0.05613   0.04733  -0.0080   0.1138   1.0000
   9.500   1.0140   0.06004   0.05170  -0.0065   0.1135   1.0000
   9.750   1.0135   0.06421   0.05626  -0.0051   0.1136   1.0000
  10.000   1.0107   0.06866   0.06102  -0.0040   0.1140   1.0000
  10.250   0.9800   0.07280   0.06572  -0.0020   0.1172   1.0000
  10.500   0.9270   0.07837   0.07161  -0.0012   0.1222   1.0000
  10.750   0.8986   0.08447   0.07782  -0.0030   0.1250   1.0000
  11.000   0.8850   0.09065   0.08404  -0.0050   0.1272   1.0000
  11.250   0.7821   0.11226   0.10556  -0.0242   0.1491   1.0000
  11.500   0.8074   0.11671   0.11008  -0.0225   0.1572   1.0000
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