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NASA/AMES A-03 AIRFOIL (ames03-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA/AMES A-03 AIRFOIL (ames03-il)
Reynolds number: 50,000
Max Cl/Cd: 27.64 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ames03-il-50000-n5.txt
Download as CSV file: xf-ames03-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/AMES A-03 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4490   0.11855   0.11241  -0.0055   1.0000   0.0647
 -10.750  -0.5950   0.12502   0.11869   0.0096   1.0000   0.0668
 -10.500  -0.5859   0.12050   0.11416   0.0087   1.0000   0.0635
 -10.000  -0.5968   0.10621   0.09994  -0.0040   1.0000   0.0549
  -9.750  -0.5915   0.10160   0.09534  -0.0060   1.0000   0.0541
  -9.500  -0.5892   0.09635   0.09011  -0.0094   1.0000   0.0533
  -9.250  -0.5895   0.09038   0.08414  -0.0143   1.0000   0.0525
  -9.000  -0.5938   0.08411   0.07786  -0.0199   1.0000   0.0516
  -8.750  -0.6017   0.07857   0.07227  -0.0240   1.0000   0.0509
  -8.500  -0.6078   0.07318   0.06674  -0.0272   1.0000   0.0503
  -8.250  -0.6119   0.06802   0.06139  -0.0295   1.0000   0.0497
  -8.000  -0.6133   0.06324   0.05635  -0.0309   1.0000   0.0495
  -7.750  -0.6117   0.05895   0.05176  -0.0314   1.0000   0.0499
  -7.500  -0.6082   0.05509   0.04754  -0.0312   1.0000   0.0508
  -7.250  -0.6040   0.05160   0.04366  -0.0301   1.0000   0.0518
  -7.000  -0.5992   0.04844   0.04009  -0.0284   1.0000   0.0527
  -6.750  -0.5929   0.04551   0.03672  -0.0263   1.0000   0.0534
  -6.500  -0.5835   0.04270   0.03343  -0.0242   1.0000   0.0538
  -6.250  -0.5714   0.04006   0.03031  -0.0223   1.0000   0.0545
  -6.000  -0.5567   0.03768   0.02745  -0.0205   1.0000   0.0555
  -5.750  -0.5412   0.03572   0.02543  -0.0193   1.0000   0.0582
  -5.500  -0.5237   0.03415   0.02367  -0.0180   1.0000   0.0615
  -5.250  -0.5040   0.03242   0.02159  -0.0166   1.0000   0.0644
  -5.000  -0.4825   0.03074   0.01953  -0.0153   1.0000   0.0670
  -4.750  -0.4616   0.02931   0.01802  -0.0142   1.0000   0.0713
  -4.500  -0.4403   0.02822   0.01682  -0.0131   1.0000   0.0775
  -4.250  -0.4175   0.02709   0.01549  -0.0119   1.0000   0.0829
  -4.000  -0.3901   0.02607   0.01445  -0.0120   0.9976   0.0932
  -3.750  -0.3625   0.02507   0.01338  -0.0121   0.9955   0.1057
  -3.500  -0.3349   0.02412   0.01243  -0.0124   0.9935   0.1270
  -3.250  -0.3092   0.02299   0.01154  -0.0127   0.9911   0.1681
  -3.000  -0.2865   0.02102   0.01073  -0.0130   0.9890   0.3371
  -2.750  -0.2748   0.01976   0.01125  -0.0077   0.9873   0.7074
  -2.500  -0.2519   0.02013   0.01171  -0.0040   0.9856   0.8490
  -2.250  -0.1833   0.02085   0.01211  -0.0087   0.9885   0.9621
  -2.000  -0.0956   0.02098   0.01176  -0.0204   0.9919   1.0000
  -1.750  -0.0747   0.02091   0.01147  -0.0204   0.9875   1.0000
  -1.500  -0.0515   0.02090   0.01126  -0.0208   0.9836   1.0000
  -1.250  -0.0318   0.02093   0.01112  -0.0204   0.9792   1.0000
  -1.000  -0.0087   0.02102   0.01105  -0.0206   0.9753   1.0000
  -0.750   0.0142   0.02115   0.01104  -0.0206   0.9713   1.0000
  -0.500   0.0381   0.02133   0.01108  -0.0208   0.9660   1.0000
  -0.250   0.0741   0.02160   0.01123  -0.0231   0.9589   1.0000
   0.000   0.1250   0.02191   0.01144  -0.0279   0.9478   1.0000
   0.250   0.1743   0.02216   0.01164  -0.0321   0.9326   1.0000
   0.500   0.2148   0.02239   0.01182  -0.0343   0.9163   1.0000
   0.750   0.2523   0.02254   0.01195  -0.0356   0.8985   1.0000
   1.000   0.2815   0.02258   0.01198  -0.0350   0.8785   1.0000
   1.250   0.3045   0.02254   0.01193  -0.0333   0.8587   1.0000
   1.500   0.3268   0.02250   0.01191  -0.0316   0.8424   1.0000
   1.750   0.3482   0.02245   0.01189  -0.0298   0.8272   1.0000
   2.000   0.3700   0.02230   0.01178  -0.0279   0.8104   1.0000
   2.250   0.3920   0.02204   0.01158  -0.0257   0.7924   1.0000
   2.500   0.4113   0.02181   0.01143  -0.0235   0.7691   1.0000
   2.750   0.4315   0.02144   0.01114  -0.0212   0.7413   1.0000
   3.000   0.4511   0.02111   0.01091  -0.0190   0.7019   1.0000
   3.500   0.4946   0.01969   0.00897  -0.0117   0.5131   1.0000
   3.750   0.5120   0.02023   0.00872  -0.0087   0.4348   1.0000
   4.000   0.5319   0.02106   0.00916  -0.0075   0.3935   1.0000
   4.250   0.5540   0.02182   0.00972  -0.0067   0.3668   1.0000
   4.500   0.5769   0.02254   0.01027  -0.0060   0.3477   1.0000
   4.750   0.6008   0.02323   0.01085  -0.0054   0.3320   1.0000
   5.000   0.6254   0.02389   0.01146  -0.0049   0.3180   1.0000
   5.250   0.6507   0.02455   0.01216  -0.0045   0.3055   1.0000
   5.500   0.6765   0.02523   0.01286  -0.0041   0.2942   1.0000
   5.750   0.7026   0.02595   0.01357  -0.0037   0.2836   1.0000
   6.000   0.7289   0.02668   0.01437  -0.0035   0.2731   1.0000
   6.250   0.7551   0.02747   0.01530  -0.0032   0.2627   1.0000
   6.500   0.7810   0.02831   0.01618  -0.0030   0.2529   1.0000
   6.750   0.8067   0.02919   0.01719  -0.0028   0.2428   1.0000
   7.000   0.8319   0.03016   0.01837  -0.0026   0.2324   1.0000
   7.250   0.8569   0.03114   0.01941  -0.0024   0.2232   1.0000
   7.500   0.8810   0.03215   0.02063  -0.0022   0.2124   1.0000
   7.750   0.9044   0.03330   0.02204  -0.0020   0.2019   1.0000
   8.000   0.9275   0.03434   0.02325  -0.0017   0.1919   1.0000
   8.250   0.9499   0.03539   0.02448  -0.0014   0.1814   1.0000
   8.500   0.9704   0.03663   0.02605  -0.0010   0.1698   1.0000
   8.750   0.9904   0.03786   0.02753  -0.0006   0.1590   1.0000
   9.000   1.0097   0.03883   0.02866   0.0000   0.1484   1.0000
   9.250   1.0283   0.03966   0.02963   0.0006   0.1380   1.0000
   9.500   1.0435   0.04103   0.03132   0.0013   0.1265   1.0000
   9.750   1.0573   0.04263   0.03319   0.0021   0.1160   1.0000
  10.000   1.0702   0.04402   0.03474   0.0030   0.1068   1.0000
  10.250   1.0828   0.04524   0.03600   0.0039   0.0988   1.0000
  10.500   1.0883   0.04790   0.03905   0.0050   0.0910   1.0000
  10.750   1.0989   0.04910   0.04016   0.0060   0.0852   1.0000
  11.000   1.0944   0.05290   0.04451   0.0072   0.0803   1.0000
  11.250   1.0924   0.05532   0.04707   0.0084   0.0762   1.0000
  11.500   1.0943   0.05732   0.04902   0.0095   0.0728   1.0000
  11.750   1.0762   0.06216   0.05428   0.0099   0.0711   1.0000
  12.000   1.0542   0.06773   0.06017   0.0092   0.0702   1.0000
  12.250   1.0265   0.07464   0.06735   0.0069   0.0700   1.0000
  12.500   0.9916   0.08383   0.07674   0.0020   0.0706   1.0000
  12.750   0.9508   0.09640   0.08940  -0.0061   0.0720   1.0000
  13.000   0.9094   0.11147   0.10445  -0.0153   0.0728   1.0000
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