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

N-11 (n11-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: N-11 (n11-il)
Reynolds number: 100,000
Max Cl/Cd: 56.23 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n11-il-100000-n5.txt
Download as CSV file: xf-n11-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-11                                            
  
 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  -0.3645   0.09531   0.09053  -0.0409   1.0000   0.0498
  -9.750  -0.3732   0.09293   0.08823  -0.0392   1.0000   0.0497
  -9.500  -0.3849   0.09094   0.08633  -0.0369   1.0000   0.0495
  -9.250  -0.3979   0.08907   0.08455  -0.0344   1.0000   0.0493
  -9.000  -0.3930   0.08514   0.08063  -0.0372   0.9965   0.0490
  -8.750  -0.3739   0.07993   0.07538  -0.0433   0.9898   0.0482
  -8.500  -0.3546   0.07393   0.06932  -0.0512   0.9824   0.0474
  -8.250  -0.3337   0.06681   0.06209  -0.0609   0.9744   0.0474
  -8.000  -0.3143   0.05887   0.05392  -0.0702   0.9649   0.0481
  -7.750  -0.2932   0.05139   0.04611  -0.0773   0.9569   0.0480
  -7.500  -0.2699   0.04443   0.03867  -0.0829   0.9499   0.0478
  -7.250  -0.2469   0.03882   0.03246  -0.0862   0.9424   0.0483
  -7.000  -0.2196   0.03424   0.02706  -0.0889   0.9361   0.0497
  -6.750  -0.1861   0.03114   0.02345  -0.0914   0.9325   0.0502
  -6.500  -0.1627   0.02917   0.02116  -0.0914   0.9240   0.0507
  -6.250  -0.1290   0.02733   0.01903  -0.0931   0.9196   0.0514
  -6.000  -0.0985   0.02589   0.01734  -0.0939   0.9139   0.0523
  -5.750  -0.0688   0.02482   0.01609  -0.0944   0.9072   0.0540
  -5.500  -0.0337   0.02370   0.01472  -0.0959   0.9031   0.0564
  -5.250  -0.0063   0.02271   0.01353  -0.0957   0.8952   0.0577
  -5.000   0.0272   0.02167   0.01230  -0.0966   0.8901   0.0589
  -4.750   0.0576   0.02085   0.01132  -0.0970   0.8835   0.0602
  -4.500   0.0883   0.02004   0.01052  -0.0975   0.8770   0.0621
  -4.250   0.1208   0.01939   0.00984  -0.0982   0.8714   0.0647
  -4.000   0.1496   0.01889   0.00928  -0.0982   0.8633   0.0686
  -3.750   0.1835   0.01830   0.00866  -0.0992   0.8582   0.0754
  -3.500   0.2108   0.01790   0.00824  -0.0989   0.8489   0.0844
  -3.250   0.2429   0.01729   0.00769  -0.0995   0.8418   0.1026
  -3.000   0.2720   0.01683   0.00735  -0.0995   0.8319   0.1371
  -2.750   0.3011   0.01649   0.00708  -0.0995   0.8212   0.1791
  -2.500   0.3318   0.01605   0.00680  -0.0998   0.8109   0.2386
  -2.250   0.3602   0.01550   0.00658  -0.0997   0.7989   0.3328
  -2.000   0.3827   0.01461   0.00654  -0.0985   0.7860   0.5732
  -1.750   0.4314   0.01367   0.00635  -0.1013   0.7747   1.0000
  -1.500   0.4590   0.01371   0.00618  -0.1010   0.7639   1.0000
  -1.250   0.4854   0.01377   0.00607  -0.1005   0.7523   1.0000
  -1.000   0.5108   0.01386   0.00602  -0.0999   0.7399   1.0000
  -0.750   0.5368   0.01394   0.00596  -0.0993   0.7277   1.0000
  -0.500   0.5632   0.01402   0.00590  -0.0989   0.7157   1.0000
  -0.250   0.5897   0.01409   0.00584  -0.0984   0.7035   1.0000
   0.000   0.6156   0.01419   0.00582  -0.0979   0.6902   1.0000
   0.250   0.6413   0.01429   0.00582  -0.0973   0.6767   1.0000
   0.500   0.6672   0.01441   0.00584  -0.0968   0.6633   1.0000
   0.750   0.6931   0.01454   0.00587  -0.0963   0.6496   1.0000
   1.000   0.7189   0.01469   0.00591  -0.0958   0.6354   1.0000
   1.250   0.7445   0.01485   0.00598  -0.0952   0.6210   1.0000
   1.500   0.7699   0.01503   0.00607  -0.0947   0.6065   1.0000
   1.750   0.7951   0.01524   0.00619  -0.0941   0.5917   1.0000
   2.000   0.8200   0.01546   0.00635  -0.0935   0.5762   1.0000
   2.250   0.8446   0.01570   0.00652  -0.0928   0.5601   1.0000
   2.500   0.8687   0.01596   0.00670  -0.0921   0.5430   1.0000
   2.750   0.8923   0.01624   0.00691  -0.0913   0.5246   1.0000
   3.000   0.9155   0.01654   0.00711  -0.0904   0.5050   1.0000
   3.250   0.9381   0.01685   0.00735  -0.0895   0.4850   1.0000
   3.500   0.9608   0.01719   0.00763  -0.0887   0.4662   1.0000
   3.750   0.9837   0.01754   0.00794  -0.0879   0.4496   1.0000
   4.000   1.0066   0.01792   0.00826  -0.0871   0.4345   1.0000
   4.250   1.0295   0.01831   0.00863  -0.0863   0.4210   1.0000
   4.500   1.0522   0.01872   0.00901  -0.0856   0.4088   1.0000
   4.750   1.0748   0.01916   0.00941  -0.0848   0.3972   1.0000
   5.000   1.0973   0.01960   0.00987  -0.0841   0.3859   1.0000
   5.250   1.1194   0.02007   0.01035  -0.0833   0.3749   1.0000
   5.500   1.1410   0.02057   0.01081  -0.0825   0.3644   1.0000
   5.750   1.1625   0.02107   0.01134  -0.0816   0.3536   1.0000
   6.000   1.1839   0.02158   0.01191  -0.0808   0.3438   1.0000
   6.500   1.2255   0.02267   0.01308  -0.0790   0.3246   1.0000
   6.750   1.2460   0.02325   0.01369  -0.0781   0.3160   1.0000
   7.000   1.2658   0.02381   0.01437  -0.0770   0.3068   1.0000
   7.250   1.2854   0.02440   0.01504  -0.0760   0.2982   1.0000
   7.500   1.3034   0.02500   0.01570  -0.0747   0.2886   1.0000
   7.750   1.3187   0.02557   0.01639  -0.0731   0.2760   1.0000
   8.000   1.3320   0.02617   0.01708  -0.0712   0.2620   1.0000
   8.250   1.3435   0.02679   0.01780  -0.0690   0.2481   1.0000
   8.500   1.3547   0.02747   0.01856  -0.0668   0.2351   1.0000
   8.750   1.3650   0.02824   0.01940  -0.0646   0.2213   1.0000
   9.000   1.3744   0.02912   0.02033  -0.0625   0.2072   1.0000
   9.250   1.3837   0.03009   0.02137  -0.0605   0.1950   1.0000
   9.500   1.3915   0.03121   0.02253  -0.0584   0.1830   1.0000
   9.750   1.3967   0.03254   0.02390  -0.0563   0.1684   1.0000
  10.000   1.4008   0.03406   0.02544  -0.0543   0.1529   1.0000
  10.250   1.4053   0.03566   0.02710  -0.0525   0.1368   1.0000
  10.500   1.4064   0.03760   0.02904  -0.0507   0.1137   1.0000
  10.750   1.3998   0.04031   0.03159  -0.0487   0.0921   1.0000
  11.000   1.3914   0.04339   0.03459  -0.0470   0.0779   1.0000
  11.250   1.3851   0.04645   0.03769  -0.0457   0.0646   1.0000
  11.500   1.3783   0.04973   0.04103  -0.0447   0.0493   1.0000
  11.750   1.3671   0.05364   0.04495  -0.0441   0.0394   1.0000
  12.000   1.3557   0.05781   0.04916  -0.0438   0.0345   1.0000
  12.250   1.3440   0.06225   0.05370  -0.0440   0.0318   1.0000
  12.500   1.3327   0.06690   0.05849  -0.0445   0.0302   1.0000
  12.750   1.3200   0.07196   0.06373  -0.0454   0.0290   1.0000
  13.000   1.3061   0.07743   0.06937  -0.0467   0.0282   1.0000
  13.250   1.2913   0.08330   0.07540  -0.0483   0.0277   1.0000
  13.500   1.2760   0.08946   0.08172  -0.0502   0.0272   1.0000
<< Back to N-11 (n11-il)

Polar data table (+)

Polar graphs


<< Back to N-11 (n11-il)