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NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-209 (naca63209-il)
Reynolds number: 100,000
Max Cl/Cd: 47.33 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca63209-il-100000.txt
Download as CSV file: xf-naca63209-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4512   0.09996   0.09529  -0.0110   1.0000   0.1147
  -9.500  -0.4675   0.09585   0.09127  -0.0149   1.0000   0.1194
  -9.250  -0.4976   0.09133   0.08686  -0.0213   1.0000   0.1204
  -9.000  -0.4542   0.08739   0.08281  -0.0148   1.0000   0.1287
  -8.750  -0.4792   0.08275   0.07828  -0.0200   1.0000   0.1336
  -8.500  -0.4643   0.07835   0.07388  -0.0181   1.0000   0.1387
  -8.250  -0.4698   0.07430   0.06988  -0.0198   1.0000   0.1456
  -8.000  -0.5116   0.06867   0.06438  -0.0274   1.0000   0.1478
  -7.750  -0.4787   0.06560   0.06129  -0.0220   1.0000   0.1582
  -7.500  -0.5257   0.05930   0.05501  -0.0308   1.0000   0.1618
  -7.250  -0.5749   0.06569   0.06105  -0.0311   1.0000   0.1600
  -7.000  -0.5669   0.06211   0.05750  -0.0306   1.0000   0.1703
  -6.750  -0.5618   0.05866   0.05402  -0.0311   1.0000   0.1843
  -6.500  -0.5618   0.05525   0.05048  -0.0324   1.0000   0.2066
  -6.000  -0.5224   0.03708   0.02982  -0.0378   1.0000   0.0780
  -5.750  -0.5041   0.03341   0.02592  -0.0369   1.0000   0.0757
  -5.500  -0.4842   0.03038   0.02251  -0.0358   1.0000   0.0739
  -5.250  -0.4624   0.02738   0.01893  -0.0343   1.0000   0.0696
  -5.000  -0.4400   0.02517   0.01626  -0.0328   1.0000   0.0681
  -4.750  -0.4182   0.02329   0.01418  -0.0315   1.0000   0.0687
  -4.500  -0.3974   0.02190   0.01273  -0.0303   1.0000   0.0733
  -4.250  -0.3760   0.02072   0.01135  -0.0289   1.0000   0.0775
  -4.000  -0.3551   0.01927   0.00986  -0.0274   1.0000   0.0807
  -3.750  -0.3356   0.01805   0.00878  -0.0260   1.0000   0.0869
  -3.500  -0.3162   0.01708   0.00789  -0.0248   1.0000   0.0993
  -3.250  -0.2960   0.01610   0.00698  -0.0237   1.0000   0.1177
  -3.000  -0.2802   0.01279   0.00617  -0.0227   1.0000   0.5602
  -2.750  -0.2704   0.01288   0.00661  -0.0179   1.0000   0.7022
  -2.500  -0.2599   0.01313   0.00692  -0.0136   1.0000   0.7586
  -2.250  -0.2505   0.01334   0.00714  -0.0093   1.0000   0.7974
  -2.000  -0.2498   0.01359   0.00746  -0.0028   1.0000   0.8459
  -1.750  -0.2539   0.01371   0.00767   0.0049   1.0000   0.8944
  -1.500  -0.2336   0.01382   0.00774   0.0079   1.0000   0.9502
  -1.250  -0.1717   0.01398   0.00764   0.0007   1.0000   0.9752
  -1.000  -0.1022   0.01414   0.00758  -0.0085   0.9971   0.9903
  -0.750  -0.0441   0.01426   0.00752  -0.0160   0.9902   1.0000
  -0.500   0.0012   0.01438   0.00752  -0.0213   0.9796   1.0000
  -0.250   0.0476   0.01451   0.00756  -0.0264   0.9699   1.0000
   0.000   0.0871   0.01460   0.00758  -0.0301   0.9584   1.0000
   0.250   0.1266   0.01472   0.00765  -0.0335   0.9474   1.0000
   0.500   0.1723   0.01484   0.00775  -0.0379   0.9385   1.0000
   0.750   0.2167   0.01493   0.00784  -0.0418   0.9290   1.0000
   1.000   0.2550   0.01504   0.00796  -0.0445   0.9182   1.0000
   1.250   0.2949   0.01513   0.00809  -0.0472   0.9083   1.0000
   1.500   0.3372   0.01517   0.00820  -0.0501   0.8993   1.0000
   1.750   0.3675   0.01531   0.00839  -0.0509   0.8868   1.0000
   2.000   0.3974   0.01546   0.00860  -0.0514   0.8745   1.0000
   2.250   0.4273   0.01559   0.00883  -0.0517   0.8621   1.0000
   2.500   0.4566   0.01569   0.00902  -0.0518   0.8493   1.0000
   2.750   0.4849   0.01575   0.00917  -0.0514   0.8356   1.0000
   3.000   0.5120   0.01573   0.00926  -0.0504   0.8201   1.0000
   3.250   0.5387   0.01547   0.00911  -0.0487   0.8014   1.0000
   3.500   0.5615   0.01488   0.00855  -0.0453   0.7730   1.0000
   3.750   0.5816   0.01409   0.00772  -0.0410   0.7318   1.0000
   4.000   0.6032   0.01370   0.00733  -0.0381   0.6913   1.0000
   4.250   0.6253   0.01350   0.00718  -0.0356   0.6443   1.0000
   4.500   0.6409   0.01354   0.00679  -0.0316   0.5063   1.0000
   4.750   0.6375   0.01737   0.00807  -0.0270   0.1274   1.0000
   5.000   0.6558   0.01899   0.00945  -0.0256   0.0973   1.0000
   5.250   0.6766   0.02046   0.01084  -0.0243   0.0849   1.0000
   5.500   0.6996   0.02195   0.01229  -0.0234   0.0751   1.0000
   5.750   0.7247   0.02393   0.01414  -0.0229   0.0695   1.0000
   6.000   0.7528   0.02605   0.01638  -0.0224   0.0670   1.0000
   6.250   0.7807   0.02814   0.01875  -0.0218   0.0652   1.0000
   6.500   0.8062   0.03009   0.02097  -0.0211   0.0614   1.0000
   6.750   0.8310   0.03269   0.02393  -0.0203   0.0605   1.0000
   7.000   0.8537   0.03610   0.02788  -0.0191   0.0623   1.0000
   7.250   0.8737   0.04013   0.03242  -0.0179   0.0654   1.0000
   7.500   0.8907   0.04518   0.03832  -0.0158   0.0760   1.0000
  10.250   0.8097   0.11192   0.10746  -0.0317   0.1352   1.0000
  10.500   0.7782   0.11863   0.11405  -0.0405   0.1317   1.0000
  10.750   0.6603   0.12065   0.11642  -0.0359   0.1387   1.0000
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