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NASA/AMES A-02 AIRFOIL (ames02-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA/AMES A-02 AIRFOIL (ames02-il)
Reynolds number: 200,000
Max Cl/Cd: 41.85 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ames02-il-200000-n5.txt
Download as CSV file: xf-ames02-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/AMES A-02 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.7421   0.08350   0.07999   0.0147   1.0000   0.0165
  -8.500  -0.7567   0.07422   0.07068   0.0050   1.0000   0.0162
  -8.250  -0.7687   0.06516   0.06143  -0.0010   1.0000   0.0158
  -8.000  -0.7786   0.05568   0.05160  -0.0046   1.0000   0.0155
  -7.750  -0.7833   0.04624   0.04159  -0.0061   1.0000   0.0154
  -7.500  -0.7776   0.03913   0.03385  -0.0063   1.0000   0.0155
  -7.250  -0.7638   0.03405   0.02816  -0.0060   1.0000   0.0158
  -7.000  -0.7454   0.02994   0.02344  -0.0056   1.0000   0.0163
  -6.750  -0.7238   0.02652   0.01932  -0.0052   1.0000   0.0174
  -6.500  -0.6987   0.02560   0.01836  -0.0052   1.0000   0.0180
  -6.250  -0.6734   0.02402   0.01651  -0.0051   1.0000   0.0189
  -6.000  -0.6477   0.02210   0.01423  -0.0047   1.0000   0.0195
  -5.750  -0.6213   0.02053   0.01240  -0.0045   1.0000   0.0202
  -5.500  -0.5948   0.01953   0.01136  -0.0044   1.0000   0.0209
  -5.250  -0.5679   0.01852   0.01027  -0.0043   1.0000   0.0218
  -5.000  -0.5407   0.01761   0.00921  -0.0042   1.0000   0.0233
  -4.750  -0.5135   0.01693   0.00854  -0.0043   1.0000   0.0249
  -4.500  -0.4861   0.01612   0.00765  -0.0042   1.0000   0.0265
  -4.250  -0.4588   0.01541   0.00697  -0.0042   1.0000   0.0279
  -4.000  -0.4311   0.01476   0.00628  -0.0043   1.0000   0.0301
  -3.750  -0.4032   0.01423   0.00575  -0.0044   1.0000   0.0332
  -3.500  -0.3752   0.01369   0.00523  -0.0045   1.0000   0.0366
  -3.250  -0.3470   0.01320   0.00474  -0.0047   1.0000   0.0412
  -3.000  -0.3187   0.01274   0.00433  -0.0048   1.0000   0.0483
  -2.750  -0.2904   0.01229   0.00394  -0.0050   1.0000   0.0597
  -2.500  -0.2623   0.01181   0.00360  -0.0053   1.0000   0.0830
  -2.250  -0.2347   0.01123   0.00331  -0.0056   1.0000   0.1386
  -2.000  -0.2082   0.01043   0.00305  -0.0059   1.0000   0.2571
  -1.750  -0.1837   0.00943   0.00288  -0.0059   1.0000   0.4534
  -1.250  -0.1251   0.00857   0.00296  -0.0063   0.9826   0.6919
  -1.000  -0.0936   0.00839   0.00299  -0.0067   0.9710   0.7592
  -0.750  -0.0648   0.00825   0.00303  -0.0062   0.9572   0.8154
  -0.500  -0.0410   0.00816   0.00310  -0.0042   0.9380   0.8758
  -0.250  -0.0142   0.00814   0.00312  -0.0027   0.9160   0.9315
   0.000   0.0187   0.00813   0.00306  -0.0032   0.8940   0.9656
   0.250   0.0535   0.00812   0.00299  -0.0043   0.8744   0.9939
   0.500   0.0797   0.00812   0.00290  -0.0036   0.8528   1.0000
   0.750   0.1039   0.00814   0.00283  -0.0025   0.8291   1.0000
   1.000   0.1290   0.00817   0.00276  -0.0016   0.8013   1.0000
   1.250   0.1538   0.00822   0.00269  -0.0006   0.7683   1.0000
   1.500   0.1790   0.00832   0.00263   0.0004   0.7249   1.0000
   1.750   0.2042   0.00851   0.00257   0.0014   0.6640   1.0000
   2.000   0.2297   0.00886   0.00253   0.0021   0.5766   1.0000
   2.250   0.2560   0.00940   0.00258   0.0024   0.4717   1.0000
   2.500   0.2831   0.00998   0.00272   0.0023   0.3729   1.0000
   2.750   0.3107   0.01052   0.00290   0.0021   0.2968   1.0000
   3.000   0.3386   0.01098   0.00310   0.0019   0.2423   1.0000
   3.250   0.3665   0.01139   0.00331   0.0017   0.2009   1.0000
   3.500   0.3944   0.01178   0.00355   0.0015   0.1687   1.0000
   3.750   0.4223   0.01216   0.00381   0.0013   0.1432   1.0000
   4.000   0.4502   0.01255   0.00409   0.0012   0.1229   1.0000
   4.250   0.4781   0.01293   0.00441   0.0011   0.1061   1.0000
   4.500   0.5058   0.01334   0.00474   0.0010   0.0927   1.0000
   4.750   0.5335   0.01375   0.00510   0.0009   0.0818   1.0000
   5.000   0.5611   0.01418   0.00550   0.0008   0.0728   1.0000
   5.250   0.5886   0.01463   0.00595   0.0008   0.0652   1.0000
   5.500   0.6160   0.01511   0.00642   0.0008   0.0589   1.0000
   5.750   0.6431   0.01561   0.00692   0.0007   0.0536   1.0000
   6.000   0.6701   0.01615   0.00747   0.0007   0.0491   1.0000
   6.250   0.6969   0.01671   0.00803   0.0007   0.0453   1.0000
   6.500   0.7236   0.01729   0.00866   0.0008   0.0417   1.0000
   6.750   0.7500   0.01793   0.00936   0.0009   0.0388   1.0000
   7.000   0.7761   0.01862   0.01005   0.0009   0.0367   1.0000
   7.250   0.8020   0.01937   0.01091   0.0011   0.0344   1.0000
   7.500   0.8276   0.02012   0.01168   0.0012   0.0326   1.0000
   7.750   0.8530   0.02093   0.01263   0.0014   0.0306   1.0000
   8.000   0.8779   0.02176   0.01348   0.0015   0.0294   1.0000
   8.250   0.9024   0.02287   0.01477   0.0018   0.0282   1.0000
   8.500   0.9265   0.02392   0.01595   0.0021   0.0271   1.0000
   8.750   0.9503   0.02487   0.01693   0.0023   0.0262   1.0000
   9.000   0.9732   0.02621   0.01853   0.0026   0.0250   1.0000
   9.250   0.9957   0.02746   0.01997   0.0030   0.0240   1.0000
   9.500   1.0176   0.02864   0.02127   0.0033   0.0233   1.0000
   9.750   1.0384   0.03002   0.02275   0.0037   0.0228   1.0000
  10.000   1.0558   0.03237   0.02554   0.0043   0.0221   1.0000
  10.250   1.0711   0.03481   0.02836   0.0050   0.0216   1.0000
  10.500   1.0844   0.03728   0.03116   0.0057   0.0211   1.0000
  10.750   1.0966   0.03956   0.03370   0.0063   0.0206   1.0000
  11.000   1.1085   0.04150   0.03582   0.0070   0.0203   1.0000
  11.250   1.1198   0.04328   0.03769   0.0076   0.0199   1.0000
  11.500   1.1082   0.04806   0.04300   0.0085   0.0196   1.0000
  11.750   1.0852   0.05295   0.04828   0.0092   0.0195   1.0000
  12.000   1.0596   0.05915   0.05477   0.0065   0.0195   1.0000
  12.250   1.0328   0.06805   0.06392  -0.0011   0.0197   1.0000
  12.500   1.0054   0.08032   0.07637  -0.0120   0.0199   1.0000
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