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NACA 65(2)-415 (naca652415-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(2)-415 (naca652415-il)
Reynolds number: 100,000
Max Cl/Cd: 46.59 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca652415-il-100000-n5.txt
Download as CSV file: xf-naca652415-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(2)-415                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.4497   0.09622   0.09092  -0.0627   1.0000   0.0367
 -11.750  -0.4717   0.08626   0.08101  -0.0684   1.0000   0.0359
 -11.500  -0.5099   0.07613   0.07085  -0.0746   1.0000   0.0351
 -11.250  -0.5457   0.06961   0.06425  -0.0772   1.0000   0.0347
 -11.000  -0.5793   0.06522   0.05980  -0.0770   1.0000   0.0344
 -10.750  -0.6134   0.06262   0.05716  -0.0739   1.0000   0.0342
 -10.500  -0.6390   0.05946   0.05385  -0.0728   0.9939   0.0340
 -10.250  -0.6457   0.05522   0.04928  -0.0752   0.9803   0.0341
 -10.000  -0.6396   0.05164   0.04540  -0.0772   0.9701   0.0349
  -9.750  -0.6301   0.04812   0.04149  -0.0790   0.9620   0.0358
  -9.500  -0.6208   0.04492   0.03786  -0.0795   0.9526   0.0368
  -9.250  -0.6039   0.04161   0.03404  -0.0807   0.9467   0.0376
  -9.000  -0.5905   0.03902   0.03100  -0.0801   0.9373   0.0381
  -8.750  -0.5671   0.03651   0.02799  -0.0810   0.9321   0.0388
  -8.500  -0.5478   0.03460   0.02587  -0.0807   0.9240   0.0400
  -8.250  -0.5218   0.03309   0.02425  -0.0815   0.9185   0.0415
  -8.000  -0.4942   0.03153   0.02248  -0.0822   0.9136   0.0428
  -7.750  -0.4710   0.03014   0.02091  -0.0818   0.9063   0.0438
  -7.500  -0.4414   0.02871   0.01928  -0.0824   0.9016   0.0451
  -7.250  -0.4143   0.02761   0.01798  -0.0825   0.8960   0.0468
  -7.000  -0.3900   0.02653   0.01685  -0.0822   0.8893   0.0488
  -6.750  -0.3625   0.02552   0.01585  -0.0826   0.8847   0.0508
  -6.500  -0.3400   0.02472   0.01501  -0.0819   0.8783   0.0525
  -6.250  -0.3175   0.02396   0.01418  -0.0812   0.8719   0.0546
  -6.000  -0.2920   0.02324   0.01334  -0.0811   0.8673   0.0573
  -5.750  -0.2761   0.02260   0.01275  -0.0795   0.8595   0.0608
  -5.500  -0.2543   0.02201   0.01211  -0.0788   0.8541   0.0654
  -5.250  -0.2320   0.02138   0.01140  -0.0782   0.8493   0.0704
  -5.000  -0.2145   0.02090   0.01090  -0.0768   0.8419   0.0783
  -4.750  -0.1925   0.02024   0.01028  -0.0762   0.8370   0.0950
  -4.500  -0.1749   0.01932   0.00969  -0.0752   0.8315   0.1489
  -4.250  -0.1667   0.01774   0.00909  -0.0734   0.8246   0.3376
  -4.000  -0.1495   0.01721   0.00945  -0.0712   0.8203   0.5381
  -3.750  -0.1255   0.01739   0.00963  -0.0701   0.8157   0.5928
  -3.500  -0.1053   0.01792   0.01021  -0.0678   0.8096   0.6419
  -3.250  -0.0838   0.01884   0.01117  -0.0647   0.8054   0.6856
  -3.000  -0.0583   0.01939   0.01167  -0.0628   0.8024   0.7055
  -2.750  -0.0368   0.01942   0.01157  -0.0620   0.7963   0.7151
  -2.500  -0.0116   0.01947   0.01153  -0.0613   0.7916   0.7199
  -2.250   0.0164   0.01940   0.01133  -0.0614   0.7881   0.7250
  -2.000   0.0448   0.01924   0.01102  -0.0619   0.7847   0.7314
  -1.750   0.0659   0.01935   0.01109  -0.0610   0.7788   0.7355
  -1.500   0.0920   0.01934   0.01101  -0.0608   0.7747   0.7396
  -1.250   0.1209   0.01924   0.01080  -0.0612   0.7715   0.7446
  -1.000   0.1479   0.01918   0.01065  -0.0615   0.7676   0.7499
  -0.750   0.1692   0.01933   0.01080  -0.0605   0.7622   0.7536
  -0.500   0.1956   0.01934   0.01076  -0.0605   0.7584   0.7579
  -0.250   0.2250   0.01927   0.01062  -0.0611   0.7554   0.7632
   0.000   0.2515   0.01929   0.01061  -0.0611   0.7518   0.7676
   0.250   0.2717   0.01949   0.01084  -0.0600   0.7462   0.7716
   0.500   0.2979   0.01955   0.01088  -0.0600   0.7425   0.7764
   0.750   0.3279   0.01951   0.01081  -0.0608   0.7397   0.7822
   1.000   0.3549   0.01955   0.01085  -0.0606   0.7367   0.7858
   1.250   0.3725   0.01987   0.01124  -0.0593   0.7305   0.7906
   1.500   0.3987   0.01997   0.01135  -0.0594   0.7268   0.7964
   1.750   0.4270   0.01999   0.01139  -0.0596   0.7239   0.8011
   2.000   0.4566   0.01997   0.01140  -0.0599   0.7216   0.8055
   2.250   0.4710   0.02046   0.01197  -0.0583   0.7147   0.8119
   2.500   0.4958   0.02059   0.01216  -0.0580   0.7107   0.8172
   2.750   0.5234   0.02062   0.01225  -0.0579   0.7078   0.8223
   3.000   0.5542   0.02062   0.01228  -0.0585   0.7054   0.8284
   3.250   0.5644   0.02122   0.01302  -0.0562   0.6977   0.8349
   3.500   0.5901   0.02132   0.01320  -0.0559   0.6938   0.8409
   3.750   0.6214   0.02128   0.01323  -0.0566   0.6909   0.8474
   4.000   0.6347   0.02172   0.01380  -0.0544   0.6839   0.8544
   4.250   0.6592   0.02184   0.01402  -0.0540   0.6786   0.8623
   4.500   0.6898   0.02166   0.01394  -0.0541   0.6751   0.8682
   4.750   0.7034   0.02209   0.01451  -0.0521   0.6671   0.8774
   5.000   0.7290   0.02200   0.01455  -0.0515   0.6616   0.8849
   5.250   0.7591   0.02177   0.01443  -0.0515   0.6561   0.8935
   5.500   0.7751   0.02182   0.01464  -0.0494   0.6463   0.9040
   5.750   0.7992   0.02156   0.01453  -0.0483   0.6369   0.9142
   6.000   0.8275   0.02084   0.01391  -0.0475   0.6226   0.9251
   6.250   0.8529   0.01974   0.01282  -0.0456   0.5954   0.9377
   6.500   0.8673   0.01941   0.01257  -0.0431   0.5601   0.9567
   6.750   0.8894   0.01929   0.01250  -0.0424   0.5199   0.9912
   7.000   0.9039   0.01940   0.01245  -0.0404   0.4669   1.0000
   7.250   0.9102   0.02006   0.01248  -0.0371   0.3715   1.0000
   7.500   0.9036   0.02173   0.01356  -0.0332   0.2891   1.0000
   7.750   0.8976   0.02369   0.01505  -0.0299   0.2158   1.0000
   8.000   0.8946   0.02570   0.01660  -0.0273   0.1502   1.0000
   8.250   0.8964   0.02756   0.01810  -0.0253   0.1035   1.0000
   9.000   0.9214   0.03212   0.02238  -0.0212   0.0602   1.0000
   9.250   0.9304   0.03364   0.02392  -0.0200   0.0554   1.0000
   9.500   0.9408   0.03509   0.02543  -0.0190   0.0516   1.0000
   9.750   0.9501   0.03664   0.02700  -0.0180   0.0488   1.0000
  10.000   0.9604   0.03816   0.02858  -0.0170   0.0460   1.0000
  10.250   0.9722   0.03961   0.03011  -0.0161   0.0434   1.0000
  10.500   0.9838   0.04112   0.03167  -0.0152   0.0415   1.0000
  10.750   0.9959   0.04269   0.03322  -0.0144   0.0400   1.0000
  11.000   1.0120   0.04411   0.03468  -0.0137   0.0387   1.0000
  11.250   1.0298   0.04545   0.03616  -0.0131   0.0371   1.0000
  11.500   1.0466   0.04688   0.03769  -0.0125   0.0354   1.0000
  11.750   1.0628   0.04839   0.03927  -0.0121   0.0340   1.0000
  12.000   1.0816   0.04994   0.04084  -0.0117   0.0330   1.0000
  12.250   1.1050   0.05166   0.04259  -0.0115   0.0322   1.0000
  12.500   1.1222   0.05365   0.04485  -0.0110   0.0315   1.0000
  12.750   1.1367   0.05593   0.04741  -0.0104   0.0310   1.0000
  13.000   1.1469   0.05848   0.05023  -0.0098   0.0304   1.0000
  13.250   1.1521   0.06126   0.05328  -0.0092   0.0298   1.0000
  13.500   1.1539   0.06420   0.05648  -0.0086   0.0293   1.0000
  13.750   1.1533   0.06732   0.05983  -0.0082   0.0287   1.0000
  14.000   1.1511   0.07053   0.06326  -0.0079   0.0282   1.0000
  14.250   1.1472   0.07396   0.06689  -0.0079   0.0278   1.0000
  14.500   1.1403   0.07779   0.07094  -0.0081   0.0275   1.0000
  14.750   1.1311   0.08196   0.07534  -0.0086   0.0273   1.0000
  15.000   1.1181   0.08678   0.08040  -0.0095   0.0272   1.0000
  15.250   1.1026   0.09212   0.08600  -0.0110   0.0272   1.0000
  15.500   1.0833   0.09829   0.09242  -0.0133   0.0272   1.0000
  15.750   1.0596   0.10561   0.10002  -0.0166   0.0273   1.0000
  16.000   1.0263   0.11537   0.11009  -0.0220   0.0275   1.0000
  16.250   0.9691   0.13228   0.12737  -0.0330   0.0282   1.0000
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