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

NACA 4412 (naca4412-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 4412 (naca4412-il)
Reynolds number: 100,000
Max Cl/Cd: 57.41 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca4412-il-100000-n5.txt
Download as CSV file: xf-naca4412-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 4412                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4048   0.09389   0.08857  -0.0483   1.0000   0.0478
  -9.750  -0.4169   0.08955   0.08431  -0.0489   1.0000   0.0478
  -9.500  -0.4366   0.08474   0.07959  -0.0495   1.0000   0.0479
  -9.250  -0.4631   0.08006   0.07503  -0.0493   1.0000   0.0480
  -8.750  -0.5253   0.06900   0.06415  -0.0511   1.0000   0.0479
  -8.500  -0.5707   0.05119   0.04568  -0.0644   0.9952   0.0481
  -8.250  -0.5467   0.04868   0.04308  -0.0673   0.9903   0.0493
  -8.000  -0.5231   0.04492   0.03903  -0.0712   0.9851   0.0504
  -7.750  -0.5018   0.04055   0.03419  -0.0746   0.9791   0.0518
  -7.500  -0.4754   0.03665   0.02968  -0.0779   0.9741   0.0541
  -7.250  -0.4503   0.03299   0.02525  -0.0800   0.9684   0.0562
  -7.000  -0.4200   0.03096   0.02296  -0.0817   0.9634   0.0575
  -6.750  -0.3850   0.02963   0.02147  -0.0840   0.9600   0.0593
  -6.500  -0.3579   0.02848   0.02010  -0.0846   0.9527   0.0618
  -6.250  -0.3232   0.02697   0.01822  -0.0865   0.9482   0.0647
  -6.000  -0.2905   0.02560   0.01658  -0.0878   0.9431   0.0669
  -5.750  -0.2604   0.02468   0.01563  -0.0886   0.9364   0.0692
  -5.500  -0.2238   0.02383   0.01466  -0.0906   0.9323   0.0733
  -5.250  -0.1930   0.02299   0.01359  -0.0913   0.9258   0.0776
  -5.000  -0.1610   0.02221   0.01284  -0.0923   0.9197   0.0817
  -4.750  -0.1239   0.02143   0.01196  -0.0942   0.9158   0.0879
  -4.500  -0.0963   0.02085   0.01138  -0.0942   0.9078   0.0943
  -4.250  -0.0626   0.02029   0.01069  -0.0953   0.9021   0.1036
  -4.000  -0.0298   0.01972   0.01019  -0.0963   0.8963   0.1137
  -3.750  -0.0012   0.01927   0.00975  -0.0965   0.8880   0.1252
  -3.500   0.0341   0.01876   0.00925  -0.0979   0.8832   0.1405
  -3.250   0.0601   0.01842   0.00895  -0.0975   0.8734   0.1560
  -3.000   0.0943   0.01796   0.00851  -0.0985   0.8678   0.1762
  -2.750   0.1208   0.01768   0.00826  -0.0982   0.8578   0.1966
  -2.500   0.1543   0.01725   0.00791  -0.0991   0.8516   0.2223
  -2.250   0.1807   0.01701   0.00771  -0.0986   0.8410   0.2480
  -2.000   0.2125   0.01664   0.00739  -0.0992   0.8338   0.2786
  -1.750   0.2399   0.01635   0.00720  -0.0989   0.8233   0.3107
  -1.500   0.2689   0.01603   0.00700  -0.0990   0.8139   0.3511
  -1.250   0.2984   0.01563   0.00678  -0.0991   0.8049   0.4075
  -1.000   0.3243   0.01521   0.00672  -0.0985   0.7938   0.5006
  -0.750   0.3496   0.01460   0.00664  -0.0973   0.7848   0.6595
  -0.500   0.3752   0.01412   0.00663  -0.0954   0.7741   0.8453
  -0.250   0.4266   0.01392   0.00639  -0.0997   0.7634   1.0000
   0.000   0.4558   0.01393   0.00621  -0.0998   0.7530   1.0000
   0.250   0.4826   0.01399   0.00614  -0.0994   0.7409   1.0000
   0.500   0.5094   0.01407   0.00609  -0.0991   0.7289   1.0000
   0.750   0.5371   0.01415   0.00604  -0.0988   0.7177   1.0000
   1.000   0.5649   0.01424   0.00599  -0.0986   0.7065   1.0000
   1.250   0.5909   0.01438   0.00605  -0.0982   0.6942   1.0000
   1.500   0.6178   0.01451   0.00608  -0.0978   0.6828   1.0000
   1.750   0.6455   0.01464   0.00609  -0.0976   0.6722   1.0000
   2.000   0.6713   0.01482   0.00622  -0.0972   0.6603   1.0000
   2.250   0.6976   0.01500   0.00633  -0.0968   0.6491   1.0000
   2.500   0.7248   0.01517   0.00641  -0.0965   0.6390   1.0000
   2.750   0.7505   0.01538   0.00659  -0.0960   0.6276   1.0000
   3.000   0.7765   0.01560   0.00677  -0.0956   0.6169   1.0000
   3.250   0.8035   0.01580   0.00689  -0.0953   0.6073   1.0000
   3.500   0.8286   0.01605   0.00715  -0.0948   0.5961   1.0000
   3.750   0.8545   0.01630   0.00737  -0.0943   0.5860   1.0000
   4.000   0.8807   0.01654   0.00757  -0.0939   0.5762   1.0000
   4.250   0.9054   0.01682   0.00787  -0.0933   0.5653   1.0000
   4.500   0.9312   0.01709   0.00812  -0.0929   0.5556   1.0000
   4.750   0.9563   0.01737   0.00842  -0.0923   0.5452   1.0000
   5.000   0.9809   0.01768   0.00875  -0.0917   0.5348   1.0000
   5.250   1.0066   0.01797   0.00902  -0.0913   0.5256   1.0000
   5.500   1.0303   0.01830   0.00943  -0.0905   0.5147   1.0000
   5.750   1.0545   0.01863   0.00979  -0.0899   0.5043   1.0000
   6.000   1.0780   0.01893   0.01009  -0.0890   0.4918   1.0000
   6.250   1.1002   0.01923   0.01038  -0.0879   0.4772   1.0000
   6.500   1.1214   0.01955   0.01077  -0.0867   0.4620   1.0000
   6.750   1.1425   0.01990   0.01117  -0.0855   0.4474   1.0000
   7.000   1.1625   0.02025   0.01154  -0.0841   0.4307   1.0000
   7.250   1.1810   0.02063   0.01193  -0.0825   0.4114   1.0000
   7.500   1.1982   0.02105   0.01238  -0.0807   0.3902   1.0000
   7.750   1.2150   0.02152   0.01285  -0.0788   0.3690   1.0000
   8.000   1.2308   0.02205   0.01337  -0.0769   0.3473   1.0000
   8.250   1.2453   0.02266   0.01398  -0.0748   0.3230   1.0000
   8.500   1.2577   0.02337   0.01464  -0.0725   0.2970   1.0000
   8.750   1.2668   0.02421   0.01539  -0.0697   0.2694   1.0000
   9.000   1.2728   0.02520   0.01626  -0.0665   0.2418   1.0000
   9.250   1.2779   0.02637   0.01732  -0.0635   0.2137   1.0000
   9.500   1.2819   0.02769   0.01856  -0.0605   0.1872   1.0000
   9.750   1.2847   0.02918   0.01994  -0.0577   0.1643   1.0000
  10.000   1.2873   0.03077   0.02147  -0.0550   0.1449   1.0000
  10.250   1.2892   0.03249   0.02314  -0.0525   0.1299   1.0000
  10.500   1.2911   0.03429   0.02493  -0.0502   0.1182   1.0000
  10.750   1.2917   0.03627   0.02689  -0.0480   0.1092   1.0000
  11.000   1.2943   0.03819   0.02889  -0.0462   0.1015   1.0000
  11.250   1.2947   0.04036   0.03108  -0.0444   0.0960   1.0000
  11.500   1.2979   0.04238   0.03321  -0.0429   0.0905   1.0000
  11.750   1.2980   0.04473   0.03559  -0.0415   0.0863   1.0000
  12.000   1.3002   0.04698   0.03791  -0.0403   0.0824   1.0000
  12.250   1.3033   0.04919   0.04024  -0.0392   0.0786   1.0000
  12.500   1.3045   0.05162   0.04273  -0.0383   0.0756   1.0000
  12.750   1.3053   0.05414   0.04526  -0.0373   0.0731   1.0000
  13.000   1.3099   0.05635   0.04763  -0.0365   0.0702   1.0000
  13.250   1.3130   0.05874   0.05013  -0.0358   0.0674   1.0000
  13.500   1.3149   0.06128   0.05274  -0.0352   0.0650   1.0000
  14.000   1.3213   0.06622   0.05785  -0.0341   0.0607   1.0000
  14.250   1.3240   0.06885   0.06063  -0.0337   0.0584   1.0000
  14.500   1.3262   0.07157   0.06345  -0.0335   0.0564   1.0000
  14.750   1.3282   0.07428   0.06621  -0.0333   0.0546   1.0000
  15.000   1.3308   0.07696   0.06893  -0.0330   0.0529   1.0000
  15.250   1.3307   0.08019   0.07241  -0.0332   0.0511   1.0000
  15.500   1.3304   0.08348   0.07587  -0.0334   0.0494   1.0000
  15.750   1.3299   0.08678   0.07930  -0.0338   0.0478   1.0000
  16.000   1.3299   0.09000   0.08258  -0.0343   0.0464   1.0000
  16.250   1.3328   0.09267   0.08521  -0.0343   0.0450   1.0000
  16.500   1.3257   0.09731   0.09017  -0.0356   0.0439   1.0000
  16.750   1.3187   0.10199   0.09511  -0.0370   0.0427   1.0000
<< Back to NACA 4412 (naca4412-il)

Polar data table (+)

Polar graphs


<< Back to NACA 4412 (naca4412-il)