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NASA/AMES A-03 AIRFOIL (ames03-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NASA/AMES A-03 AIRFOIL (ames03-il)
Reynolds number: 1,000,000
Max Cl/Cd: 87.84 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ames03-il-1000000.txt
Download as CSV file: xf-ames03-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5678   0.11183   0.11018   0.0289   0.8460   0.0144
 -10.250  -1.0078   0.04381   0.04125   0.0076   0.8523   0.0089
 -10.000  -1.0423   0.03276   0.02925   0.0101   0.8499   0.0091
  -9.750  -1.0360   0.02844   0.02448   0.0114   0.8478   0.0094
  -9.500  -1.0139   0.02750   0.02346   0.0117   0.8458   0.0097
  -9.250  -0.9898   0.02700   0.02290   0.0119   0.8438   0.0099
  -9.000  -0.9669   0.02605   0.02183   0.0122   0.8420   0.0102
  -8.750  -0.9441   0.02489   0.02052   0.0125   0.8402   0.0105
  -8.500  -0.9217   0.02339   0.01881   0.0130   0.8383   0.0107
  -8.250  -0.8980   0.02197   0.01718   0.0133   0.8365   0.0110
  -8.000  -0.8734   0.02059   0.01561   0.0135   0.8347   0.0113
  -7.750  -0.8479   0.01946   0.01431   0.0137   0.8329   0.0115
  -7.500  -0.8218   0.01852   0.01323   0.0138   0.8311   0.0118
  -7.250  -0.7950   0.01786   0.01245   0.0139   0.8293   0.0120
  -7.000  -0.7709   0.01593   0.01030   0.0143   0.8277   0.0126
  -6.750  -0.7442   0.01522   0.00954   0.0143   0.8261   0.0131
  -6.500  -0.7165   0.01489   0.00918   0.0142   0.8245   0.0137
  -6.250  -0.6889   0.01443   0.00866   0.0142   0.8227   0.0143
  -6.000  -0.6607   0.01389   0.00806   0.0141   0.8211   0.0148
  -5.750  -0.6324   0.01343   0.00756   0.0139   0.8195   0.0153
  -5.500  -0.6038   0.01304   0.00712   0.0137   0.8178   0.0158
  -5.250  -0.5762   0.01218   0.00618   0.0137   0.8162   0.0167
  -5.000  -0.5478   0.01172   0.00570   0.0135   0.8145   0.0177
  -4.750  -0.5193   0.01142   0.00538   0.0133   0.8123   0.0187
  -4.500  -0.4909   0.01114   0.00506   0.0133   0.8099   0.0198
  -4.250  -0.4622   0.01100   0.00488   0.0131   0.8074   0.0207
  -4.000  -0.4331   0.01042   0.00429   0.0128   0.8051   0.0233
  -3.750  -0.4039   0.01017   0.00404   0.0126   0.8022   0.0253
  -3.500  -0.3746   0.00998   0.00382   0.0123   0.7999   0.0268
  -3.250  -0.3455   0.00963   0.00348   0.0121   0.7976   0.0318
  -3.000  -0.3165   0.00941   0.00324   0.0119   0.7950   0.0364
  -2.750  -0.2875   0.00921   0.00304   0.0117   0.7922   0.0438
  -2.500  -0.2577   0.00891   0.00285   0.0113   0.7897   0.0624
  -2.250  -0.2281   0.00861   0.00269   0.0108   0.7870   0.0951
  -2.000  -0.1988   0.00822   0.00252   0.0104   0.7840   0.1549
  -1.750  -0.1697   0.00773   0.00234   0.0099   0.7806   0.2433
  -1.500  -0.1406   0.00697   0.00215   0.0092   0.7767   0.4085
  -1.250  -0.1108   0.00619   0.00202   0.0083   0.7723   0.5882
  -1.000  -0.0816   0.00579   0.00192   0.0081   0.7666   0.6850
  -0.750  -0.0526   0.00557   0.00187   0.0079   0.7603   0.7435
  -0.500  -0.0237   0.00539   0.00185   0.0079   0.7534   0.7914
  -0.250   0.0051   0.00533   0.00181   0.0079   0.7478   0.8180
   0.000   0.0341   0.00524   0.00181   0.0078   0.7406   0.8423
   0.250   0.0627   0.00520   0.00178   0.0079   0.7321   0.8641
   0.500   0.0915   0.00517   0.00177   0.0079   0.7215   0.8788
   0.750   0.1197   0.00515   0.00176   0.0081   0.7079   0.8972
   1.000   0.1471   0.00515   0.00174   0.0084   0.6870   0.9139
   1.250   0.1766   0.00532   0.00169   0.0082   0.6154   0.9242
   1.500   0.2149   0.00656   0.00196   0.0047   0.3668   0.9298
   1.750   0.2450   0.00695   0.00207   0.0039   0.2970   0.9368
   2.000   0.2742   0.00715   0.00215   0.0034   0.2679   0.9440
   2.250   0.3017   0.00727   0.00220   0.0035   0.2521   0.9516
   2.500   0.3296   0.00739   0.00226   0.0035   0.2401   0.9593
   2.750   0.3565   0.00745   0.00230   0.0037   0.2325   0.9680
   3.000   0.3848   0.00755   0.00235   0.0036   0.2247   0.9766
   3.250   0.4153   0.00761   0.00240   0.0030   0.2193   0.9852
   3.500   0.4486   0.00774   0.00249   0.0016   0.2123   0.9926
   3.750   0.4819   0.00784   0.00258   0.0003   0.2070   1.0000
   4.000   0.5126   0.00797   0.00269  -0.0005   0.2018   1.0000
   4.250   0.5433   0.00816   0.00283  -0.0014   0.1954   1.0000
   4.500   0.5738   0.00827   0.00294  -0.0021   0.1913   1.0000
   4.750   0.6042   0.00841   0.00306  -0.0029   0.1857   1.0000
   5.000   0.6345   0.00861   0.00323  -0.0036   0.1797   1.0000
   5.250   0.6646   0.00871   0.00335  -0.0043   0.1754   1.0000
   5.500   0.6946   0.00888   0.00349  -0.0049   0.1700   1.0000
   5.750   0.7245   0.00907   0.00366  -0.0056   0.1645   1.0000
   6.000   0.7542   0.00920   0.00381  -0.0061   0.1590   1.0000
   6.250   0.7838   0.00943   0.00399  -0.0068   0.1512   1.0000
   6.500   0.8132   0.00958   0.00413  -0.0073   0.1437   1.0000
   6.750   0.8425   0.00981   0.00434  -0.0079   0.1356   1.0000
   7.000   0.8716   0.01004   0.00454  -0.0084   0.1268   1.0000
   7.250   0.9006   0.01028   0.00476  -0.0089   0.1186   1.0000
   7.500   0.9293   0.01058   0.00502  -0.0095   0.1082   1.0000
   7.750   0.9576   0.01092   0.00531  -0.0100   0.0963   1.0000
   8.000   0.9857   0.01131   0.00563  -0.0104   0.0847   1.0000
   8.250   1.0134   0.01173   0.00600  -0.0109   0.0733   1.0000
   8.500   1.0408   0.01218   0.00640  -0.0113   0.0625   1.0000
   8.750   1.0679   0.01266   0.00683  -0.0116   0.0528   1.0000
   9.000   1.0946   0.01317   0.00729  -0.0119   0.0434   1.0000
   9.250   1.1208   0.01376   0.00782  -0.0122   0.0342   1.0000
   9.500   1.1466   0.01437   0.00839  -0.0123   0.0273   1.0000
   9.750   1.1724   0.01493   0.00897  -0.0125   0.0232   1.0000
  10.000   1.1971   0.01568   0.00972  -0.0125   0.0195   1.0000
  10.250   1.2228   0.01616   0.01026  -0.0126   0.0184   1.0000
  10.500   1.2477   0.01673   0.01086  -0.0127   0.0170   1.0000
  10.750   1.2711   0.01752   0.01168  -0.0126   0.0155   1.0000
  11.000   1.2939   0.01834   0.01260  -0.0124   0.0145   1.0000
  11.250   1.3175   0.01893   0.01326  -0.0123   0.0140   1.0000
  11.500   1.3402   0.01961   0.01400  -0.0121   0.0133   1.0000
  11.750   1.3620   0.02034   0.01479  -0.0119   0.0127   1.0000
  12.000   1.3823   0.02120   0.01572  -0.0115   0.0121   1.0000
  12.250   1.3989   0.02241   0.01701  -0.0108   0.0115   1.0000
  12.500   1.4089   0.02416   0.01893  -0.0096   0.0110   1.0000
  12.750   1.4255   0.02507   0.01992  -0.0090   0.0108   1.0000
  13.000   1.4373   0.02608   0.02102  -0.0078   0.0106   1.0000
  13.250   1.4480   0.02718   0.02222  -0.0065   0.0104   1.0000
  13.500   1.4582   0.02838   0.02350  -0.0053   0.0101   1.0000
  13.750   1.4676   0.02968   0.02489  -0.0042   0.0098   1.0000
  14.000   1.4758   0.03113   0.02643  -0.0031   0.0095   1.0000
  14.250   1.4831   0.03268   0.02805  -0.0021   0.0093   1.0000
  14.500   1.4886   0.03444   0.02991  -0.0012   0.0091   1.0000
  14.750   1.4910   0.03654   0.03211  -0.0004   0.0089   1.0000
  15.000   1.4891   0.03915   0.03483   0.0003   0.0087   1.0000
  15.250   1.4826   0.04239   0.03819   0.0007   0.0085   1.0000
  15.500   1.4708   0.04643   0.04237   0.0007   0.0084   1.0000
  15.750   1.4546   0.05143   0.04754  -0.0003   0.0083   1.0000
  16.000   1.4358   0.05741   0.05369  -0.0024   0.0082   1.0000
  16.250   1.4140   0.06498   0.06145  -0.0064   0.0082   1.0000
  16.500   1.3923   0.07370   0.07035  -0.0117   0.0082   1.0000
  16.750   1.3709   0.08271   0.07952  -0.0169   0.0082   1.0000
  17.000   1.3458   0.09197   0.08893  -0.0217   0.0083   1.0000
  17.250   1.3200   0.10097   0.09805  -0.0263   0.0083   1.0000
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