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NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 64A210 (naca64a210-il)
Reynolds number: 100,000
Max Cl/Cd: 49.08 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64a210-il-100000.txt
Download as CSV file: xf-naca64a210-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A210                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5446   0.12864   0.12345  -0.0069   1.0000   0.0863
 -11.000  -0.5536   0.12520   0.12008  -0.0118   1.0000   0.0894
 -10.750  -0.5705   0.12171   0.11671  -0.0187   1.0000   0.0903
 -10.500  -0.5446   0.11636   0.11128  -0.0132   1.0000   0.0935
 -10.250  -0.5366   0.11292   0.10784  -0.0131   1.0000   0.0973
 -10.000  -0.5400   0.10904   0.10401  -0.0162   1.0000   0.1018
  -9.750  -0.5644   0.10456   0.09966  -0.0253   1.0000   0.1040
  -9.500  -0.5429   0.10031   0.09538  -0.0204   1.0000   0.1075
  -9.250  -0.5366   0.09710   0.09219  -0.0206   1.0000   0.1139
  -9.000  -0.5566   0.09197   0.08717  -0.0284   1.0000   0.1173
  -8.750  -0.4327   0.07992   0.07533  -0.0289   1.0000   0.1411
  -8.500  -0.4667   0.07465   0.07020  -0.0347   1.0000   0.1457
  -8.250  -0.4483   0.07105   0.06658  -0.0314   1.0000   0.1518
  -8.000  -0.5590   0.07564   0.07102  -0.0334   1.0000   0.1395
  -7.750  -0.5874   0.07115   0.06635  -0.0393   1.0000   0.1459
  -7.500  -0.5676   0.06775   0.06311  -0.0361   1.0000   0.1545
  -7.250  -0.5779   0.06383   0.05912  -0.0370   1.0000   0.1641
  -7.000  -0.5861   0.06093   0.05609  -0.0365   1.0000   0.1767
  -6.750  -0.5858   0.05831   0.05341  -0.0348   1.0000   0.1906
  -6.500  -0.5802   0.05551   0.05064  -0.0326   1.0000   0.2054
  -6.250  -0.5724   0.05290   0.04810  -0.0300   1.0000   0.2213
  -5.750  -0.5431   0.03626   0.02861  -0.0295   1.0000   0.0757
  -5.500  -0.5268   0.03283   0.02496  -0.0281   1.0000   0.0732
  -5.250  -0.5086   0.03051   0.02222  -0.0265   1.0000   0.0735
  -5.000  -0.4883   0.02819   0.01953  -0.0251   1.0000   0.0728
  -4.750  -0.4661   0.02607   0.01706  -0.0238   1.0000   0.0719
  -4.500  -0.4429   0.02432   0.01502  -0.0227   1.0000   0.0725
  -4.250  -0.4194   0.02299   0.01345  -0.0217   1.0000   0.0750
  -4.000  -0.3960   0.02147   0.01187  -0.0210   1.0000   0.0802
  -3.750  -0.3724   0.02033   0.01074  -0.0203   1.0000   0.0853
  -3.500  -0.3487   0.01924   0.00963  -0.0195   1.0000   0.0921
  -3.250  -0.3264   0.01825   0.00878  -0.0189   1.0000   0.1074
  -3.000  -0.3030   0.01714   0.00786  -0.0185   1.0000   0.1383
  -2.750  -0.2876   0.01424   0.00773  -0.0158   1.0000   0.6884
  -2.500  -0.2747   0.01441   0.00802  -0.0118   1.0000   0.7677
  -2.250  -0.2623   0.01452   0.00817  -0.0078   1.0000   0.8177
  -2.000  -0.2522   0.01461   0.00831  -0.0033   1.0000   0.8663
  -1.750  -0.2386   0.01483   0.00860   0.0014   1.0000   0.9340
  -1.250  -0.1254   0.01540   0.00873  -0.0114   1.0000   1.0000
  -1.000  -0.0848   0.01547   0.00864  -0.0162   0.9910   1.0000
  -0.750  -0.0417   0.01565   0.00864  -0.0211   0.9824   1.0000
  -0.500  -0.0019   0.01582   0.00867  -0.0251   0.9728   1.0000
  -0.250   0.0375   0.01604   0.00877  -0.0288   0.9637   1.0000
   0.000   0.0826   0.01631   0.00893  -0.0332   0.9565   1.0000
   0.250   0.1173   0.01654   0.00910  -0.0356   0.9464   1.0000
   0.500   0.1598   0.01680   0.00931  -0.0393   0.9392   1.0000
   0.750   0.1960   0.01704   0.00952  -0.0417   0.9299   1.0000
   1.000   0.2311   0.01731   0.00977  -0.0438   0.9209   1.0000
   1.250   0.2743   0.01751   0.01000  -0.0474   0.9139   1.0000
   1.500   0.3046   0.01780   0.01030  -0.0484   0.9038   1.0000
   1.750   0.3518   0.01792   0.01049  -0.0525   0.8983   1.0000
   2.000   0.3781   0.01823   0.01086  -0.0526   0.8872   1.0000
   2.250   0.4096   0.01847   0.01118  -0.0536   0.8777   1.0000
   2.500   0.4498   0.01851   0.01132  -0.0559   0.8703   1.0000
   2.750   0.4768   0.01872   0.01163  -0.0558   0.8586   1.0000
   3.000   0.5072   0.01881   0.01186  -0.0560   0.8472   1.0000
   3.250   0.5408   0.01865   0.01184  -0.0563   0.8355   1.0000
   3.500   0.5762   0.01777   0.01111  -0.0554   0.8162   1.0000
   3.750   0.6085   0.01628   0.00972  -0.0524   0.7871   1.0000
   4.000   0.6350   0.01531   0.00881  -0.0493   0.7569   1.0000
   4.250   0.6580   0.01471   0.00826  -0.0464   0.7219   1.0000
   4.500   0.6787   0.01429   0.00785  -0.0431   0.6733   1.0000
   4.750   0.6935   0.01413   0.00743  -0.0386   0.5645   1.0000
   5.000   0.6796   0.01751   0.00821  -0.0312   0.1621   1.0000
   5.250   0.6903   0.01950   0.00972  -0.0284   0.1104   1.0000
   5.500   0.7070   0.02091   0.01102  -0.0265   0.0923   1.0000
   5.750   0.7267   0.02253   0.01253  -0.0249   0.0832   1.0000
   6.000   0.7498   0.02432   0.01414  -0.0242   0.0745   1.0000
   6.250   0.7767   0.02590   0.01589  -0.0236   0.0698   1.0000
   6.500   0.8048   0.02783   0.01796  -0.0231   0.0669   1.0000
   6.750   0.8325   0.03006   0.02036  -0.0226   0.0653   1.0000
   7.000   0.8574   0.03254   0.02296  -0.0222   0.0626   1.0000
   7.250   0.8794   0.03604   0.02674  -0.0214   0.0607   1.0000
   7.500   0.9008   0.03984   0.03090  -0.0204   0.0611   1.0000
   7.750   0.9191   0.04139   0.03325  -0.0176   0.0641   1.0000
   8.000   0.9311   0.04647   0.03903  -0.0151   0.0706   1.0000
  10.250   0.8873   0.09965   0.09503  -0.0080   0.1418   1.0000
  10.500   0.6299   0.10643   0.10187  -0.0161   0.1639   1.0000
  10.750   0.6393   0.10974   0.10520  -0.0151   0.1582   1.0000
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