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NACA 64-012A AIRFOIL (n64012a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-012A AIRFOIL (n64012a-il)
Reynolds number: 50,000
Max Cl/Cd: 27.23 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64012a-il-50000-n5.txt
Download as CSV file: xf-n64012a-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-012A 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7891   0.07868   0.07096  -0.0314   1.0000   0.0480
 -10.750  -0.8055   0.07444   0.06657  -0.0317   1.0000   0.0479
 -10.500  -0.8210   0.07066   0.06261  -0.0307   1.0000   0.0478
 -10.250  -0.8336   0.06707   0.05879  -0.0292   1.0000   0.0478
 -10.000  -0.8424   0.06345   0.05487  -0.0276   1.0000   0.0479
  -9.750  -0.8458   0.05986   0.05104  -0.0261   1.0000   0.0484
  -9.500  -0.8413   0.05674   0.04774  -0.0250   1.0000   0.0496
  -9.250  -0.8334   0.05409   0.04495  -0.0238   1.0000   0.0510
  -9.000  -0.8262   0.05132   0.04191  -0.0224   1.0000   0.0525
  -8.750  -0.8173   0.04843   0.03867  -0.0208   1.0000   0.0537
  -8.500  -0.8051   0.04552   0.03537  -0.0193   1.0000   0.0546
  -8.250  -0.7893   0.04277   0.03223  -0.0180   1.0000   0.0558
  -8.000  -0.7701   0.04025   0.02930  -0.0169   1.0000   0.0573
  -7.750  -0.7492   0.03811   0.02673  -0.0159   1.0000   0.0600
  -7.500  -0.7265   0.03617   0.02483  -0.0155   1.0000   0.0637
  -7.250  -0.7013   0.03445   0.02295  -0.0149   1.0000   0.0677
  -7.000  -0.6731   0.03286   0.02108  -0.0144   1.0000   0.0718
  -6.750  -0.6507   0.03140   0.01973  -0.0136   1.0000   0.0781
  -6.500  -0.6286   0.03021   0.01833  -0.0124   1.0000   0.0858
  -6.250  -0.6123   0.02886   0.01707  -0.0108   1.0000   0.0936
  -6.000  -0.5979   0.02764   0.01587  -0.0089   1.0000   0.1057
  -5.750  -0.5858   0.02635   0.01466  -0.0066   1.0000   0.1211
  -5.500  -0.5763   0.02493   0.01347  -0.0042   1.0000   0.1481
  -5.250  -0.5711   0.02314   0.01221  -0.0013   1.0000   0.2090
  -5.000  -0.5734   0.02109   0.01152   0.0030   1.0000   0.3808
  -4.750  -0.5653   0.02076   0.01182   0.0076   1.0000   0.5401
  -4.500  -0.5530   0.02090   0.01205   0.0116   1.0000   0.6071
  -4.250  -0.5398   0.02118   0.01232   0.0155   1.0000   0.6553
  -4.000  -0.5274   0.02175   0.01290   0.0202   1.0000   0.7022
  -3.750  -0.5113   0.02249   0.01361   0.0247   1.0000   0.7408
  -3.500  -0.4948   0.02281   0.01383   0.0281   1.0000   0.7678
  -3.250  -0.4752   0.02286   0.01373   0.0300   1.0000   0.7847
  -3.000  -0.4570   0.02274   0.01347   0.0317   1.0000   0.7991
  -2.750  -0.4392   0.02257   0.01314   0.0331   1.0000   0.8128
  -2.500  -0.4210   0.02242   0.01286   0.0344   1.0000   0.8257
  -2.250  -0.3838   0.02243   0.01269   0.0321   0.9940   0.8355
  -2.000  -0.3426   0.02241   0.01247   0.0287   0.9850   0.8456
  -1.750  -0.3029   0.02236   0.01226   0.0256   0.9754   0.8560
  -1.250  -0.2194   0.02235   0.01200   0.0188   0.9578   0.8740
  -1.000  -0.1748   0.02238   0.01194   0.0150   0.9498   0.8823
  -0.750  -0.1330   0.02238   0.01186   0.0116   0.9409   0.8912
  -0.500  -0.0869   0.02238   0.01181   0.0074   0.9336   0.8999
  -0.250  -0.0440   0.02239   0.01179   0.0038   0.9247   0.9079
   0.000   0.0000   0.02237   0.01175   0.0000   0.9173   0.9173
   0.250   0.0440   0.02239   0.01179  -0.0038   0.9079   0.9247
   0.500   0.0869   0.02238   0.01181  -0.0074   0.8999   0.9336
   0.750   0.1330   0.02237   0.01186  -0.0116   0.8912   0.9409
   1.000   0.1748   0.02238   0.01194  -0.0150   0.8824   0.9498
   1.250   0.2194   0.02235   0.01200  -0.0188   0.8740   0.9579
   1.500   0.2601   0.02238   0.01216  -0.0221   0.8642   0.9668
   1.750   0.3030   0.02235   0.01226  -0.0256   0.8560   0.9754
   2.000   0.3426   0.02240   0.01247  -0.0287   0.8456   0.9850
   2.250   0.3838   0.02243   0.01269  -0.0321   0.8355   0.9940
   2.500   0.4210   0.02242   0.01285  -0.0344   0.8257   1.0000
   2.750   0.4391   0.02257   0.01314  -0.0331   0.8128   1.0000
   3.000   0.4569   0.02274   0.01344  -0.0317   0.7991   1.0000
   3.250   0.4751   0.02286   0.01373  -0.0300   0.7846   1.0000
   3.500   0.4947   0.02281   0.01383  -0.0281   0.7678   1.0000
   3.750   0.5113   0.02249   0.01361  -0.0247   0.7408   1.0000
   4.000   0.5273   0.02175   0.01289  -0.0202   0.7022   1.0000
   4.250   0.5398   0.02118   0.01232  -0.0155   0.6553   1.0000
   4.500   0.5530   0.02090   0.01205  -0.0116   0.6071   1.0000
   4.750   0.5653   0.02076   0.01182  -0.0076   0.5401   1.0000
   5.000   0.5734   0.02109   0.01152  -0.0030   0.3807   1.0000
   5.250   0.5711   0.02314   0.01220   0.0013   0.2090   1.0000
   5.500   0.5763   0.02493   0.01346   0.0042   0.1481   1.0000
   5.750   0.5858   0.02635   0.01466   0.0066   0.1211   1.0000
   6.000   0.5979   0.02764   0.01587   0.0089   0.1057   1.0000
   6.250   0.6123   0.02886   0.01707   0.0108   0.0936   1.0000
   6.500   0.6286   0.03021   0.01833   0.0124   0.0858   1.0000
   7.000   0.6732   0.03286   0.02108   0.0144   0.0718   1.0000
   7.250   0.7013   0.03445   0.02295   0.0149   0.0677   1.0000
   7.500   0.7266   0.03617   0.02483   0.0155   0.0637   1.0000
   7.750   0.7492   0.03811   0.02673   0.0159   0.0600   1.0000
   8.000   0.7701   0.04025   0.02930   0.0169   0.0573   1.0000
   8.250   0.7894   0.04278   0.03223   0.0180   0.0558   1.0000
   8.500   0.8052   0.04552   0.03537   0.0193   0.0546   1.0000
   8.750   0.8174   0.04843   0.03867   0.0208   0.0537   1.0000
   9.000   0.8263   0.05132   0.04191   0.0223   0.0525   1.0000
   9.250   0.8336   0.05410   0.04496   0.0238   0.0510   1.0000
   9.500   0.8415   0.05674   0.04775   0.0249   0.0495   1.0000
   9.750   0.8460   0.05987   0.05105   0.0260   0.0484   1.0000
  10.000   0.8426   0.06346   0.05488   0.0276   0.0479   1.0000
  10.250   0.8338   0.06709   0.05881   0.0292   0.0478   1.0000
  10.500   0.8212   0.07069   0.06264   0.0307   0.0478   1.0000
  10.750   0.8058   0.07448   0.06661   0.0316   0.0479   1.0000
  11.000   0.7895   0.07872   0.07100   0.0313   0.0480   1.0000
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