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NASA/AMES A-02 AIRFOIL (ames02-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NASA/AMES A-02 AIRFOIL (ames02-il)
Reynolds number: 500,000
Max Cl/Cd: 54.39 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ames02-il-500000.txt
Download as CSV file: xf-ames02-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.7304   0.08691   0.08475   0.0206   1.0000   0.0218
  -8.250  -0.7427   0.07858   0.07643   0.0109   1.0000   0.0218
  -8.000  -0.7842   0.05668   0.05382  -0.0038   1.0000   0.0232
  -7.750  -0.7709   0.05440   0.05157  -0.0039   1.0000   0.0233
  -7.500  -0.7575   0.05211   0.04923  -0.0042   1.0000   0.0236
  -7.250  -0.7433   0.04940   0.04642  -0.0046   1.0000   0.0240
  -7.000  -0.7287   0.04581   0.04264  -0.0050   1.0000   0.0248
  -6.750  -0.7382   0.02375   0.01812  -0.0026   1.0000   0.0173
  -6.500  -0.7141   0.02129   0.01542  -0.0024   1.0000   0.0175
  -6.250  -0.6880   0.02006   0.01412  -0.0024   1.0000   0.0180
  -6.000  -0.6613   0.01877   0.01269  -0.0023   1.0000   0.0185
  -5.750  -0.6343   0.01741   0.01112  -0.0021   1.0000   0.0190
  -5.500  -0.6068   0.01625   0.00976  -0.0020   1.0000   0.0196
  -5.250  -0.5794   0.01521   0.00862  -0.0019   1.0000   0.0205
  -5.000  -0.5515   0.01458   0.00800  -0.0021   1.0000   0.0216
  -4.750  -0.5233   0.01385   0.00718  -0.0021   1.0000   0.0226
  -4.500  -0.4955   0.01299   0.00630  -0.0021   1.0000   0.0236
  -4.250  -0.4672   0.01240   0.00572  -0.0022   1.0000   0.0248
  -4.000  -0.4383   0.01190   0.00517  -0.0024   1.0000   0.0263
  -3.750  -0.4097   0.01129   0.00463  -0.0027   1.0000   0.0283
  -3.500  -0.3806   0.01082   0.00417  -0.0030   1.0000   0.0310
  -3.250  -0.3513   0.01038   0.00374  -0.0033   1.0000   0.0343
  -3.000  -0.3217   0.00996   0.00336  -0.0037   1.0000   0.0389
  -2.750  -0.2920   0.00960   0.00304  -0.0042   1.0000   0.0468
  -2.500  -0.2625   0.00916   0.00272  -0.0047   1.0000   0.0624
  -2.250  -0.2335   0.00859   0.00244  -0.0052   1.0000   0.1184
  -2.000  -0.2061   0.00778   0.00221  -0.0058   1.0000   0.2555
  -1.750  -0.1732   0.00673   0.00206  -0.0076   0.9893   0.4903
  -1.500  -0.1407   0.00628   0.00208  -0.0086   0.9763   0.6211
  -1.250  -0.1158   0.00618   0.00219  -0.0074   0.9576   0.6884
  -1.000  -0.0949   0.00613   0.00227  -0.0053   0.9394   0.7368
  -0.750  -0.0725   0.00606   0.00230  -0.0035   0.9250   0.7786
  -0.500  -0.0495   0.00595   0.00230  -0.0019   0.9124   0.8177
  -0.250  -0.0280   0.00580   0.00229   0.0002   0.8989   0.8632
   0.000  -0.0076   0.00564   0.00224   0.0027   0.8848   0.9181
   0.250   0.0264   0.00549   0.00213   0.0020   0.8703   0.9811
   0.500   0.0616   0.00546   0.00204   0.0006   0.8539   1.0000
   0.750   0.0883   0.00547   0.00197   0.0011   0.8351   1.0000
   1.000   0.1151   0.00550   0.00190   0.0016   0.8127   1.0000
   1.250   0.1423   0.00555   0.00185   0.0020   0.7840   1.0000
   1.500   0.1695   0.00565   0.00181   0.0024   0.7472   1.0000
   1.750   0.1968   0.00582   0.00178   0.0028   0.6960   1.0000
   2.000   0.2243   0.00612   0.00177   0.0030   0.6177   1.0000
   2.250   0.2521   0.00663   0.00183   0.0029   0.5107   1.0000
   2.750   0.3088   0.00774   0.00210   0.0021   0.3089   1.0000
   3.000   0.3373   0.00818   0.00226   0.0018   0.2460   1.0000
   3.500   0.3944   0.00890   0.00261   0.0012   0.1635   1.0000
   3.750   0.4229   0.00924   0.00280   0.0010   0.1358   1.0000
   4.000   0.4514   0.00957   0.00301   0.0008   0.1143   1.0000
   4.250   0.4799   0.00989   0.00326   0.0006   0.0975   1.0000
   4.500   0.5082   0.01024   0.00351   0.0004   0.0841   1.0000
   4.750   0.5365   0.01058   0.00380   0.0003   0.0736   1.0000
   5.000   0.5648   0.01091   0.00409   0.0002   0.0650   1.0000
   5.250   0.5929   0.01127   0.00442   0.0000   0.0580   1.0000
   5.500   0.6210   0.01166   0.00478  -0.0001   0.0524   1.0000
   5.750   0.6488   0.01208   0.00518  -0.0002   0.0477   1.0000
   6.000   0.6766   0.01252   0.00562  -0.0002   0.0436   1.0000
   6.250   0.7041   0.01299   0.00608  -0.0003   0.0402   1.0000
   6.500   0.7315   0.01345   0.00653  -0.0003   0.0373   1.0000
   6.750   0.7588   0.01398   0.00711  -0.0003   0.0348   1.0000
   7.000   0.7853   0.01466   0.00774  -0.0003   0.0328   1.0000
   7.250   0.8126   0.01512   0.00829  -0.0003   0.0309   1.0000
   7.500   0.8385   0.01587   0.00900  -0.0003   0.0293   1.0000
   7.750   0.8653   0.01643   0.00968  -0.0001   0.0280   1.0000
   8.000   0.8915   0.01707   0.01035   0.0000   0.0268   1.0000
   8.250   0.9163   0.01809   0.01136   0.0001   0.0259   1.0000
   8.500   0.9420   0.01886   0.01228   0.0004   0.0250   1.0000
   8.750   0.9673   0.01968   0.01321   0.0006   0.0242   1.0000
   9.000   0.9922   0.02045   0.01401   0.0007   0.0234   1.0000
   9.250   1.0156   0.02170   0.01531   0.0010   0.0226   1.0000
   9.500   1.0395   0.02274   0.01658   0.0014   0.0220   1.0000
   9.750   1.0625   0.02394   0.01795   0.0017   0.0214   1.0000
  10.000   1.0851   0.02508   0.01922   0.0021   0.0208   1.0000
  10.250   1.1070   0.02627   0.02050   0.0025   0.0204   1.0000
  10.500   1.1266   0.02803   0.02234   0.0029   0.0200   1.0000
  10.750   1.1430   0.03025   0.02491   0.0037   0.0197   1.0000
  11.000   1.1563   0.03277   0.02784   0.0046   0.0194   1.0000
  11.250   1.1645   0.03589   0.03138   0.0057   0.0191   1.0000
  11.500   1.1659   0.03959   0.03550   0.0069   0.0189   1.0000
  11.750   1.1600   0.04364   0.03994   0.0081   0.0187   1.0000
  12.000   1.1419   0.04797   0.04461   0.0097   0.0186   1.0000
  12.250   1.1110   0.05384   0.05077   0.0088   0.0186   1.0000
  12.500   1.0719   0.06400   0.06125   0.0008   0.0189   1.0000
  12.750   1.0264   0.08151   0.07901  -0.0153   0.0194   1.0000
  13.000   0.9667   0.10184   0.09944  -0.0284   0.0200   1.0000
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