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NACA 2421 (naca2421-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 2421 (naca2421-il)
Reynolds number: 50,000
Max Cl/Cd: 6.86 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2421-il-50000.txt
Download as CSV file: xf-naca2421-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2421                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6101   0.07993   0.07184  -0.0247   1.0000   0.2984
  -8.500  -0.6835   0.07396   0.06592  -0.0189   1.0000   0.2970
  -8.250  -0.7624   0.06698   0.05883  -0.0128   1.0000   0.2960
  -8.000  -0.8246   0.06065   0.05220  -0.0070   1.0000   0.2972
  -7.750  -0.8258   0.05864   0.05018  -0.0043   1.0000   0.3022
  -7.500  -0.8101   0.05850   0.05015  -0.0023   1.0000   0.3090
  -7.250  -0.8321   0.05474   0.04609   0.0013   1.0000   0.3148
  -7.000  -0.8440   0.05148   0.04252   0.0041   1.0000   0.3210
  -6.750  -0.8244   0.05160   0.04285   0.0057   1.0000   0.3284
  -6.500  -0.8278   0.04917   0.04011   0.0080   1.0000   0.3370
  -6.250  -0.8184   0.04798   0.03889   0.0097   1.0000   0.3447
  -6.000  -0.8065   0.04730   0.03822   0.0114   1.0000   0.3537
  -5.750  -0.8006   0.04555   0.03624   0.0129   1.0000   0.3634
  -5.500  -0.7853   0.04535   0.03616   0.0144   1.0000   0.3725
  -5.250  -0.7768   0.04389   0.03445   0.0155   1.0000   0.3838
  -5.000  -0.7609   0.04380   0.03452   0.0170   1.0000   0.3935
  -4.750  -0.7494   0.04274   0.03328   0.0179   1.0000   0.4058
  -4.500  -0.7271   0.04272   0.03337   0.0180   0.9976   0.4181
  -4.250  -0.6815   0.04293   0.03359   0.0138   0.9855   0.4360
  -4.000  -0.6401   0.04304   0.03367   0.0103   0.9736   0.4542
  -3.750  -0.5992   0.04322   0.03382   0.0070   0.9623   0.4736
  -3.500  -0.5675   0.04313   0.03369   0.0052   0.9504   0.4925
  -3.250  -0.5363   0.04334   0.03394   0.0040   0.9386   0.5105
  -3.000  -0.4979   0.04379   0.03447   0.0019   0.9276   0.5300
  -2.750  -0.4702   0.04395   0.03470   0.0014   0.9158   0.5479
  -2.500  -0.4423   0.04414   0.03492   0.0009   0.9044   0.5671
  -2.250  -0.4056   0.04450   0.03532  -0.0009   0.8937   0.5891
  -2.000  -0.3872   0.04459   0.03542   0.0000   0.8820   0.6088
  -1.750  -0.3428   0.04520   0.03611  -0.0023   0.8718   0.6341
  -1.500  -0.3348   0.04527   0.03621   0.0003   0.8602   0.6541
  -1.250  -0.2939   0.04594   0.03698  -0.0010   0.8502   0.6808
  -1.000  -0.2862   0.04620   0.03732   0.0019   0.8387   0.7028
  -0.750  -0.2458   0.04696   0.03816   0.0012   0.8293   0.7319
  -0.500  -0.2411   0.04740   0.03867   0.0047   0.8180   0.7553
   0.000  -0.1982   0.04871   0.04005   0.0075   0.7981   0.8151
   0.250  -0.1347   0.04999   0.04135   0.0038   0.7883   0.8461
   0.500  -0.1221   0.05119   0.04258   0.0052   0.7770   0.8725
   0.750  -0.0262   0.05264   0.04392  -0.0049   0.7668   0.9043
   1.000   0.0229   0.05453   0.04580  -0.0110   0.7530   0.9259
   1.250   0.1364   0.05607   0.04726  -0.0263   0.7407   0.9467
   1.500   0.2315   0.05702   0.04818  -0.0394   0.7276   0.9676
   1.750   0.3055   0.05819   0.04935  -0.0501   0.7144   0.9883
   2.000   0.3946   0.05753   0.04863  -0.0611   0.7042   1.0000
   2.250   0.3406   0.05931   0.05038  -0.0528   0.6941   1.0000
   2.500   0.3293   0.05960   0.05059  -0.0491   0.6853   1.0000
   2.750   0.3283   0.05979   0.05070  -0.0463   0.6774   1.0000
   3.000   0.2726   0.06115   0.05199  -0.0376   0.6688   1.0000
   3.250   0.3058   0.06075   0.05149  -0.0379   0.6599   1.0000
   3.500   0.2579   0.06250   0.05315  -0.0303   0.6517   1.0000
   3.750   0.2599   0.06332   0.05388  -0.0277   0.6424   1.0000
   4.000   0.2728   0.06424   0.05470  -0.0262   0.6335   1.0000
   4.250   0.2570   0.06601   0.05640  -0.0226   0.6243   1.0000
   4.500   0.3027   0.06621   0.05652  -0.0239   0.6143   1.0000
   4.750   0.2711   0.06899   0.05926  -0.0198   0.6056   1.0000
   5.000   0.3295   0.06872   0.05893  -0.0217   0.5947   1.0000
   5.250   0.2919   0.07222   0.06239  -0.0179   0.5864   1.0000
   5.500   0.3237   0.07303   0.06317  -0.0182   0.5758   1.0000
   5.750   0.3152   0.07571   0.06581  -0.0165   0.5668   1.0000
   6.000   0.3222   0.07778   0.06787  -0.0158   0.5580   1.0000
   6.250   0.3428   0.07938   0.06944  -0.0156   0.5480   1.0000
   6.500   0.3311   0.08254   0.07259  -0.0145   0.5413   1.0000
   6.750   0.2204   0.09419   0.08444  -0.0161   0.6456   1.0000
   7.000   0.2825   0.09328   0.08344  -0.0156   0.5797   1.0000
   7.250   0.3114   0.09630   0.08645  -0.0170   0.5747   1.0000
   7.500   0.3200   0.09666   0.08676  -0.0149   0.5460   1.0000
   7.750   0.3480   0.09851   0.08861  -0.0153   0.5332   1.0000
   8.000   0.3673   0.10188   0.09198  -0.0162   0.5298   1.0000
   8.250   0.3897   0.10270   0.09276  -0.0153   0.5086   1.0000
   8.500   0.4225   0.10323   0.09328  -0.0146   0.4884   1.0000
   8.750   0.3176   0.11380   0.10400  -0.0172   0.5688   1.0000
   9.000   0.3352   0.11607   0.10627  -0.0175   0.5555   1.0000
   9.250   0.3491   0.11962   0.10982  -0.0182   0.5497   1.0000
   9.500   0.3494   0.12080   0.11101  -0.0174   0.5362   1.0000
   9.750   0.3838   0.12584   0.11606  -0.0193   0.5298   1.0000
  10.000   0.3647   0.12581   0.11604  -0.0176   0.5177   1.0000
  10.250   0.4186   0.13220   0.12246  -0.0204   0.5095   1.0000
  10.500   0.3827   0.13115   0.12139  -0.0181   0.5003   1.0000
  10.750   0.4137   0.13502   0.12530  -0.0192   0.4905   1.0000
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