Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-209 (naca64209-il)
Reynolds number: 50,000
Max Cl/Cd: 32 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64209-il-50000-n5.txt
Download as CSV file: xf-naca64209-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-209                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5549   0.09730   0.09025  -0.0187   1.0000   0.0546
  -9.250  -0.5567   0.09226   0.08528  -0.0217   1.0000   0.0531
  -9.000  -0.5630   0.08614   0.07923  -0.0265   1.0000   0.0511
  -8.750  -0.5891   0.07883   0.07188  -0.0343   1.0000   0.0475
  -8.500  -0.5918   0.07457   0.06759  -0.0357   1.0000   0.0471
  -8.250  -0.5956   0.07026   0.06319  -0.0371   1.0000   0.0470
  -8.000  -0.5980   0.06596   0.05873  -0.0382   1.0000   0.0469
  -7.750  -0.5987   0.06170   0.05421  -0.0389   1.0000   0.0471
  -7.500  -0.5964   0.05756   0.04971  -0.0393   1.0000   0.0475
  -7.250  -0.5907   0.05363   0.04532  -0.0391   1.0000   0.0479
  -7.000  -0.5802   0.04972   0.04116  -0.0388   1.0000   0.0484
  -6.750  -0.5675   0.04605   0.03708  -0.0382   1.0000   0.0484
  -6.500  -0.5526   0.04263   0.03331  -0.0375   1.0000   0.0489
  -6.250  -0.5357   0.03957   0.02993  -0.0367   1.0000   0.0496
  -6.000  -0.5174   0.03680   0.02684  -0.0358   1.0000   0.0509
  -5.750  -0.4981   0.03451   0.02418  -0.0348   1.0000   0.0540
  -5.500  -0.4771   0.03232   0.02144  -0.0336   1.0000   0.0582
  -5.250  -0.4566   0.03024   0.01926  -0.0327   1.0000   0.0623
  -5.000  -0.4351   0.02870   0.01748  -0.0315   1.0000   0.0682
  -4.750  -0.4146   0.02727   0.01597  -0.0304   1.0000   0.0765
  -4.500  -0.3930   0.02604   0.01458  -0.0290   1.0000   0.0811
  -4.250  -0.3719   0.02497   0.01333  -0.0273   1.0000   0.0829
  -4.000  -0.3520   0.02410   0.01224  -0.0256   1.0000   0.0845
  -3.750  -0.3333   0.02323   0.01130  -0.0241   1.0000   0.0864
  -3.500  -0.3147   0.02247   0.01046  -0.0228   1.0000   0.0889
  -3.250  -0.2955   0.02182   0.00970  -0.0217   1.0000   0.0919
  -3.000  -0.2762   0.02128   0.00903  -0.0207   1.0000   0.0971
  -2.750  -0.2565   0.02069   0.00838  -0.0199   1.0000   0.1057
  -2.500  -0.2363   0.02011   0.00784  -0.0192   1.0000   0.1200
  -2.250  -0.2168   0.01816   0.00723  -0.0196   1.0000   0.3375
  -2.000  -0.2093   0.01737   0.00777  -0.0150   1.0000   0.6454
  -1.750  -0.1978   0.01740   0.00797  -0.0111   1.0000   0.7268
  -1.500  -0.1753   0.01760   0.00826  -0.0087   0.9896   0.8109
  -1.250  -0.1431   0.01774   0.00827  -0.0092   0.9797   0.8494
  -1.000  -0.1079   0.01786   0.00828  -0.0103   0.9710   0.8882
  -0.750  -0.0652   0.01798   0.00823  -0.0135   0.9632   0.9100
  -0.500  -0.0221   0.01806   0.00815  -0.0169   0.9546   0.9339
  -0.250   0.0551   0.01808   0.00808  -0.0266   0.9531   1.0000
   0.000   0.0879   0.01819   0.00807  -0.0287   0.9417   1.0000
   0.250   0.1228   0.01833   0.00812  -0.0311   0.9316   1.0000
   0.500   0.1597   0.01848   0.00821  -0.0337   0.9223   1.0000
   0.750   0.1905   0.01866   0.00835  -0.0351   0.9112   1.0000
   1.000   0.2220   0.01886   0.00855  -0.0366   0.9011   1.0000
   1.250   0.2581   0.01906   0.00875  -0.0386   0.8928   1.0000
   1.500   0.2853   0.01931   0.00903  -0.0392   0.8816   1.0000
   1.750   0.3142   0.01958   0.00936  -0.0399   0.8712   1.0000
   2.000   0.3471   0.01982   0.00968  -0.0412   0.8627   1.0000
   2.250   0.3745   0.02013   0.01007  -0.0415   0.8520   1.0000
   2.500   0.4016   0.02046   0.01055  -0.0418   0.8413   1.0000
   2.750   0.4317   0.02074   0.01098  -0.0424   0.8313   1.0000
   3.000   0.4631   0.02098   0.01140  -0.0430   0.8210   1.0000
   3.250   0.4898   0.02127   0.01188  -0.0428   0.8082   1.0000
   3.500   0.5171   0.02154   0.01242  -0.0426   0.7950   1.0000
   3.750   0.5463   0.02162   0.01276  -0.0422   0.7794   1.0000
   4.000   0.5751   0.02054   0.01186  -0.0385   0.7359   1.0000
   4.250   0.5914   0.01909   0.01017  -0.0314   0.6361   1.0000
   4.500   0.6076   0.01899   0.00980  -0.0273   0.5129   1.0000
   4.750   0.6121   0.02111   0.01011  -0.0231   0.2130   1.0000
   5.000   0.6233   0.02359   0.01177  -0.0216   0.1201   1.0000
   5.250   0.6407   0.02518   0.01320  -0.0204   0.0942   1.0000
   5.500   0.6597   0.02665   0.01473  -0.0192   0.0837   1.0000
   5.750   0.6798   0.02819   0.01624  -0.0181   0.0749   1.0000
   6.000   0.7036   0.02949   0.01777  -0.0173   0.0658   1.0000
   6.250   0.7305   0.03134   0.01961  -0.0168   0.0616   1.0000
   6.500   0.7611   0.03329   0.02186  -0.0163   0.0584   1.0000
   6.750   0.7880   0.03528   0.02413  -0.0160   0.0539   1.0000
   7.000   0.8118   0.03768   0.02656  -0.0158   0.0499   1.0000
   7.250   0.8358   0.04050   0.02981  -0.0151   0.0484   1.0000
   7.500   0.8567   0.04357   0.03341  -0.0142   0.0476   1.0000
   7.750   0.8739   0.04695   0.03731  -0.0131   0.0470   1.0000
   8.000   0.8873   0.05058   0.04146  -0.0119   0.0466   1.0000
   8.250   0.8966   0.05437   0.04578  -0.0106   0.0461   1.0000
   8.500   0.9013   0.05823   0.05011  -0.0094   0.0451   1.0000
   8.750   0.9021   0.06214   0.05442  -0.0083   0.0441   1.0000
   9.000   0.8989   0.06612   0.05874  -0.0074   0.0433   1.0000
   9.250   0.8915   0.07021   0.06310  -0.0067   0.0428   1.0000
   9.500   0.8787   0.07434   0.06744  -0.0061   0.0428   1.0000
   9.750   0.8610   0.07871   0.07195  -0.0063   0.0431   1.0000
  10.000   0.8423   0.08378   0.07713  -0.0081   0.0437   1.0000
  10.250   0.8240   0.08978   0.08320  -0.0116   0.0443   1.0000
  10.500   0.8086   0.09658   0.09002  -0.0161   0.0451   1.0000
<< Back to NACA 64-209 (naca64209-il)

Polar data table (+)

Polar graphs


<< Back to NACA 64-209 (naca64209-il)