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NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-208 (naca64208-il)
Reynolds number: 200,000
Max Cl/Cd: 58.86 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64208-il-200000.txt
Download as CSV file: xf-naca64208-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-208                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5448   0.08768   0.08419  -0.0164   1.0000   0.0375
  -8.500  -0.5473   0.08303   0.07958  -0.0199   1.0000   0.0388
  -8.250  -0.5521   0.07812   0.07473  -0.0241   1.0000   0.0392
  -8.000  -0.5606   0.07271   0.06933  -0.0299   1.0000   0.0396
  -7.750  -0.5640   0.06761   0.06410  -0.0345   1.0000   0.0408
  -7.500  -0.5639   0.06440   0.06054  -0.0374   1.0000   0.0420
  -7.250  -0.5585   0.06143   0.05727  -0.0380   1.0000   0.0423
  -7.000  -0.5582   0.05319   0.04911  -0.0392   1.0000   0.0439
  -6.750  -0.5454   0.05076   0.04681  -0.0386   1.0000   0.0473
  -6.500  -0.5333   0.04753   0.04337  -0.0388   1.0000   0.0512
  -6.250  -0.5233   0.04395   0.03910  -0.0386   1.0000   0.0564
  -6.000  -0.5090   0.04016   0.03545  -0.0383   1.0000   0.0587
  -4.750  -0.4154   0.02420   0.01734  -0.0311   1.0000   0.0437
  -4.500  -0.3945   0.02270   0.01556  -0.0295   1.0000   0.0430
  -4.250  -0.3734   0.02031   0.01300  -0.0281   1.0000   0.0408
  -4.000  -0.3519   0.01846   0.01092  -0.0268   1.0000   0.0405
  -3.750  -0.3304   0.01715   0.00944  -0.0255   1.0000   0.0410
  -3.500  -0.3091   0.01603   0.00816  -0.0243   1.0000   0.0431
  -3.250  -0.2882   0.01472   0.00691  -0.0234   1.0000   0.0472
  -3.000  -0.2643   0.01391   0.00608  -0.0230   0.9994   0.0505
  -2.750  -0.2245   0.01293   0.00507  -0.0258   0.9947   0.0576
  -2.500  -0.1853   0.01213   0.00431  -0.0285   0.9888   0.0796
  -2.250  -0.1560   0.00933   0.00394  -0.0302   0.9848   0.6525
  -2.000  -0.1222   0.00925   0.00407  -0.0310   0.9775   0.7397
  -1.750  -0.0876   0.00930   0.00423  -0.0317   0.9708   0.7970
  -1.500  -0.0616   0.00943   0.00448  -0.0300   0.9622   0.8509
  -1.250  -0.0304   0.00951   0.00456  -0.0296   0.9561   0.8845
  -1.000   0.0013   0.00946   0.00447  -0.0301   0.9477   0.9009
  -0.750   0.0384   0.00938   0.00434  -0.0318   0.9421   0.9139
  -0.500   0.0693   0.00931   0.00422  -0.0322   0.9330   0.9286
  -0.250   0.1077   0.00921   0.00409  -0.0341   0.9274   0.9410
   0.000   0.1433   0.00913   0.00399  -0.0355   0.9181   0.9544
   0.250   0.1866   0.00903   0.00388  -0.0386   0.9120   0.9641
   0.500   0.2291   0.00895   0.00380  -0.0417   0.9031   0.9742
   0.750   0.2727   0.00888   0.00373  -0.0450   0.8948   0.9838
   1.000   0.3176   0.00878   0.00365  -0.0487   0.8865   0.9923
   1.250   0.3522   0.00875   0.00366  -0.0504   0.8748   1.0000
   1.500   0.3701   0.00880   0.00371  -0.0487   0.8615   1.0000
   1.750   0.3889   0.00885   0.00376  -0.0470   0.8478   1.0000
   2.000   0.4099   0.00892   0.00382  -0.0456   0.8340   1.0000
   2.250   0.4322   0.00891   0.00379  -0.0441   0.8166   1.0000
   2.500   0.4514   0.00873   0.00355  -0.0413   0.7795   1.0000
   2.750   0.4727   0.00866   0.00333  -0.0391   0.7358   1.0000
   3.000   0.4976   0.00874   0.00339  -0.0382   0.7072   1.0000
   3.250   0.5215   0.00886   0.00342  -0.0370   0.6630   1.0000
   3.500   0.5420   0.00923   0.00345  -0.0351   0.5574   1.0000
   3.750   0.5440   0.01253   0.00435  -0.0317   0.0917   1.0000
   4.000   0.5667   0.01362   0.00532  -0.0310   0.0620   1.0000
   4.250   0.5897   0.01463   0.00636  -0.0302   0.0527   1.0000
   4.500   0.6112   0.01597   0.00764  -0.0293   0.0454   1.0000
   4.750   0.6357   0.01701   0.00874  -0.0286   0.0426   1.0000
   5.000   0.6606   0.01832   0.01014  -0.0279   0.0404   1.0000
   5.250   0.6865   0.01989   0.01180  -0.0272   0.0391   1.0000
   5.500   0.7125   0.02143   0.01343  -0.0268   0.0370   1.0000
   5.750   0.7376   0.02405   0.01616  -0.0265   0.0346   1.0000
   6.000   0.7635   0.02635   0.01873  -0.0258   0.0348   1.0000
   6.250   0.7896   0.03028   0.02348  -0.0236   0.0414   1.0000
  15.000   0.6745   0.18174   0.17882  -0.0702   0.0278   1.0000
  15.250   0.6786   0.18498   0.18207  -0.0719   0.0273   1.0000
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