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NASA/AMES A-03 AIRFOIL (ames03-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NASA/AMES A-03 AIRFOIL (ames03-il)
Reynolds number: 500,000
Max Cl/Cd: 70.88 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ames03-il-500000-n5.txt
Download as CSV file: xf-ames03-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.7829   0.10283   0.10060   0.0372   0.8536   0.0089
 -10.250  -1.0345   0.03753   0.03376   0.0066   0.8467   0.0086
 -10.000  -1.0290   0.03342   0.02914   0.0078   0.8444   0.0088
  -9.750  -1.0152   0.03069   0.02602   0.0087   0.8424   0.0089
  -9.500  -1.0005   0.02796   0.02293   0.0095   0.8405   0.0091
  -9.250  -0.9804   0.02639   0.02114   0.0101   0.8388   0.0094
  -9.000  -0.9580   0.02523   0.01982   0.0105   0.8370   0.0096
  -8.750  -0.9340   0.02420   0.01866   0.0106   0.8348   0.0098
  -8.500  -0.9096   0.02316   0.01748   0.0108   0.8328   0.0100
  -8.250  -0.8846   0.02227   0.01645   0.0109   0.8308   0.0104
  -8.000  -0.8594   0.02135   0.01536   0.0111   0.8290   0.0108
  -7.750  -0.8340   0.02042   0.01426   0.0113   0.8273   0.0113
  -7.500  -0.8084   0.01950   0.01317   0.0115   0.8256   0.0117
  -7.250  -0.7825   0.01866   0.01217   0.0117   0.8241   0.0120
  -7.000  -0.7572   0.01766   0.01104   0.0119   0.8226   0.0124
  -6.750  -0.7301   0.01693   0.01025   0.0118   0.8206   0.0128
  -6.500  -0.7026   0.01637   0.00964   0.0117   0.8187   0.0133
  -6.250  -0.6749   0.01584   0.00906   0.0116   0.8169   0.0138
  -6.000  -0.6473   0.01531   0.00846   0.0115   0.8152   0.0144
  -5.750  -0.6195   0.01481   0.00789   0.0114   0.8135   0.0151
  -5.500  -0.5915   0.01441   0.00741   0.0113   0.8120   0.0158
  -5.250  -0.5639   0.01385   0.00682   0.0113   0.8105   0.0169
  -5.000  -0.5359   0.01348   0.00642   0.0111   0.8090   0.0179
  -4.750  -0.5078   0.01312   0.00602   0.0111   0.8076   0.0190
  -4.500  -0.4787   0.01278   0.00563   0.0108   0.8059   0.0202
  -4.250  -0.4497   0.01239   0.00522   0.0104   0.8041   0.0216
  -4.000  -0.4207   0.01208   0.00493   0.0101   0.8015   0.0239
  -3.750  -0.3920   0.01182   0.00462   0.0100   0.7983   0.0262
  -3.500  -0.3635   0.01150   0.00428   0.0099   0.7954   0.0292
  -3.250  -0.3351   0.01125   0.00401   0.0098   0.7928   0.0328
  -3.000  -0.3055   0.01099   0.00378   0.0094   0.7895   0.0386
  -2.750  -0.2761   0.01075   0.00357   0.0091   0.7862   0.0473
  -2.500  -0.2469   0.01050   0.00337   0.0088   0.7830   0.0602
  -2.000  -0.1892   0.00990   0.00298   0.0082   0.7761   0.1216
  -1.500  -0.1303   0.00904   0.00266   0.0071   0.7683   0.2655
  -1.250  -0.1018   0.00828   0.00245   0.0065   0.7644   0.4211
  -1.000  -0.0730   0.00750   0.00233   0.0059   0.7591   0.5981
  -0.750  -0.0444   0.00712   0.00228   0.0058   0.7523   0.6911
  -0.500  -0.0164   0.00690   0.00225   0.0060   0.7454   0.7529
  -0.250   0.0113   0.00675   0.00222   0.0063   0.7350   0.8000
   0.000   0.0390   0.00666   0.00220   0.0066   0.7218   0.8342
   0.250   0.0658   0.00660   0.00218   0.0073   0.7067   0.8668
   0.500   0.0926   0.00656   0.00214   0.0078   0.6882   0.8864
   0.750   0.1215   0.00661   0.00204   0.0077   0.6439   0.8968
   1.000   0.1574   0.00769   0.00216   0.0051   0.4133   0.9033
   1.250   0.1887   0.00815   0.00229   0.0039   0.3329   0.9112
   1.500   0.2178   0.00841   0.00237   0.0034   0.2922   0.9184
   1.750   0.2470   0.00861   0.00245   0.0030   0.2688   0.9263
   2.000   0.2752   0.00876   0.00251   0.0029   0.2530   0.9334
   2.250   0.3037   0.00890   0.00259   0.0027   0.2415   0.9415
   2.500   0.3317   0.00899   0.00266   0.0026   0.2338   0.9489
   3.000   0.3896   0.00922   0.00282   0.0021   0.2204   0.9649
   3.250   0.4199   0.00935   0.00291   0.0014   0.2135   0.9729
   3.500   0.4516   0.00949   0.00303   0.0004   0.2083   0.9806
   3.750   0.4844   0.00962   0.00315  -0.0008   0.2027   0.9884
   4.000   0.5172   0.00978   0.00327  -0.0021   0.1967   1.0000
   4.250   0.5468   0.00994   0.00343  -0.0027   0.1919   1.0000
   4.500   0.5765   0.01010   0.00359  -0.0033   0.1866   1.0000
   4.750   0.6060   0.01030   0.00375  -0.0039   0.1811   1.0000
   5.000   0.6355   0.01047   0.00394  -0.0044   0.1761   1.0000
   5.250   0.6649   0.01066   0.00411  -0.0050   0.1700   1.0000
   5.500   0.6941   0.01087   0.00431  -0.0055   0.1645   1.0000
   5.750   0.7232   0.01105   0.00451  -0.0060   0.1587   1.0000
   6.000   0.7522   0.01129   0.00472  -0.0066   0.1523   1.0000
   6.250   0.7811   0.01150   0.00495  -0.0070   0.1469   1.0000
   6.500   0.8098   0.01175   0.00518  -0.0075   0.1393   1.0000
   6.750   0.8383   0.01199   0.00544  -0.0079   0.1312   1.0000
   7.000   0.8665   0.01230   0.00570  -0.0084   0.1205   1.0000
   7.250   0.8945   0.01264   0.00600  -0.0088   0.1088   1.0000
   7.500   0.9221   0.01301   0.00633  -0.0091   0.0975   1.0000
   7.750   0.9494   0.01342   0.00670  -0.0095   0.0859   1.0000
   8.000   0.9764   0.01386   0.00711  -0.0098   0.0754   1.0000
   8.250   1.0032   0.01432   0.00755  -0.0101   0.0657   1.0000
   8.500   1.0295   0.01483   0.00802  -0.0103   0.0563   1.0000
   8.750   1.0554   0.01537   0.00855  -0.0105   0.0478   1.0000
   9.000   1.0810   0.01595   0.00911  -0.0106   0.0402   1.0000
   9.250   1.1062   0.01656   0.00970  -0.0107   0.0333   1.0000
   9.500   1.1311   0.01716   0.01032  -0.0108   0.0280   1.0000
   9.750   1.1555   0.01782   0.01100  -0.0108   0.0241   1.0000
  10.000   1.1797   0.01847   0.01168  -0.0108   0.0214   1.0000
  10.250   1.2030   0.01920   0.01245  -0.0107   0.0192   1.0000
  10.500   1.2265   0.01984   0.01318  -0.0105   0.0178   1.0000
  10.750   1.2490   0.02057   0.01397  -0.0103   0.0164   1.0000
  11.000   1.2701   0.02145   0.01491  -0.0101   0.0151   1.0000
  11.250   1.2910   0.02226   0.01581  -0.0097   0.0143   1.0000
  11.500   1.3115   0.02307   0.01671  -0.0093   0.0136   1.0000
  11.750   1.3306   0.02395   0.01769  -0.0088   0.0129   1.0000
  12.000   1.3483   0.02492   0.01875  -0.0083   0.0124   1.0000
  12.250   1.3637   0.02603   0.01995  -0.0076   0.0118   1.0000
  12.500   1.3742   0.02731   0.02133  -0.0064   0.0114   1.0000
  12.750   1.3800   0.02887   0.02301  -0.0048   0.0110   1.0000
  13.000   1.3895   0.03018   0.02444  -0.0036   0.0108   1.0000
  13.250   1.3976   0.03165   0.02603  -0.0024   0.0105   1.0000
  13.500   1.4042   0.03329   0.02781  -0.0014   0.0103   1.0000
  13.750   1.4091   0.03513   0.02977  -0.0004   0.0101   1.0000
  14.000   1.4123   0.03718   0.03195   0.0005   0.0099   1.0000
  14.250   1.4137   0.03948   0.03438   0.0012   0.0097   1.0000
  14.500   1.4131   0.04207   0.03711   0.0017   0.0095   1.0000
  14.750   1.4103   0.04506   0.04023   0.0018   0.0093   1.0000
  15.000   1.4054   0.04846   0.04378   0.0015   0.0092   1.0000
  15.250   1.3976   0.05251   0.04798   0.0006   0.0091   1.0000
  15.500   1.3863   0.05744   0.05307  -0.0011   0.0090   1.0000
  15.750   1.3707   0.06380   0.05962  -0.0044   0.0089   1.0000
  16.000   1.3493   0.07235   0.06838  -0.0096   0.0089   1.0000
  16.250   1.3224   0.08263   0.07886  -0.0157   0.0090   1.0000
  16.500   1.2923   0.09294   0.08934  -0.0212   0.0090   1.0000
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