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NASA/AMES A-01 AIRFOIL (ames01-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA/AMES A-01 AIRFOIL (ames01-il)
Reynolds number: 100,000
Max Cl/Cd: 40.69 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ames01-il-100000-n5.txt
Download as CSV file: xf-ames01-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/AMES A-01 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6057   0.09616   0.09132  -0.0024   1.0000   0.0372
  -9.500  -0.6113   0.08977   0.08496  -0.0071   1.0000   0.0373
  -9.250  -0.6756   0.07020   0.06513  -0.0239   1.0000   0.0344
  -9.000  -0.6686   0.06831   0.06327  -0.0238   1.0000   0.0352
  -8.750  -0.6712   0.06427   0.05910  -0.0245   1.0000   0.0356
  -8.500  -0.6744   0.05952   0.05413  -0.0250   1.0000   0.0358
  -8.250  -0.6752   0.05462   0.04891  -0.0250   1.0000   0.0359
  -8.000  -0.6707   0.05038   0.04436  -0.0245   1.0000   0.0362
  -7.750  -0.6624   0.04665   0.04028  -0.0239   1.0000   0.0367
  -7.500  -0.6511   0.04342   0.03672  -0.0230   1.0000   0.0375
  -7.250  -0.6377   0.04072   0.03370  -0.0220   1.0000   0.0390
  -7.000  -0.6245   0.03788   0.03042  -0.0206   1.0000   0.0406
  -6.750  -0.6114   0.03516   0.02722  -0.0187   1.0000   0.0416
  -6.500  -0.5980   0.03283   0.02444  -0.0166   1.0000   0.0425
  -6.250  -0.5839   0.03101   0.02218  -0.0143   1.0000   0.0435
  -6.000  -0.5688   0.02937   0.02047  -0.0127   1.0000   0.0450
  -5.750  -0.5523   0.02837   0.01939  -0.0111   1.0000   0.0470
  -5.500  -0.5349   0.02725   0.01810  -0.0094   1.0000   0.0489
  -5.250  -0.5163   0.02599   0.01662  -0.0078   1.0000   0.0505
  -5.000  -0.4903   0.02479   0.01516  -0.0075   0.9979   0.0529
  -4.750  -0.4582   0.02355   0.01373  -0.0086   0.9945   0.0560
  -4.500  -0.4275   0.02245   0.01264  -0.0095   0.9907   0.0588
  -4.250  -0.3949   0.02151   0.01165  -0.0106   0.9871   0.0618
  -4.000  -0.3612   0.02081   0.01082  -0.0119   0.9841   0.0665
  -3.750  -0.3309   0.01992   0.00996  -0.0127   0.9798   0.0706
  -3.500  -0.2986   0.01923   0.00929  -0.0138   0.9761   0.0752
  -3.250  -0.2637   0.01874   0.00872  -0.0154   0.9731   0.0821
  -3.000  -0.2340   0.01812   0.00815  -0.0161   0.9682   0.0890
  -2.750  -0.2018   0.01768   0.00769  -0.0171   0.9636   0.0981
  -2.500  -0.1677   0.01718   0.00728  -0.0186   0.9599   0.1156
  -2.250  -0.1382   0.01655   0.00690  -0.0191   0.9524   0.1594
  -2.000  -0.1100   0.01475   0.00665  -0.0198   0.9450   0.4925
  -1.750  -0.0833   0.01394   0.00682  -0.0182   0.9343   0.7322
  -1.500  -0.0361   0.01394   0.00714  -0.0195   0.9230   0.8776
  -1.250   0.0210   0.01423   0.00736  -0.0234   0.9130   0.9489
  -1.000   0.0836   0.01434   0.00732  -0.0292   0.9023   0.9834
  -0.750   0.1258   0.01420   0.00704  -0.0317   0.8861   0.9959
  -0.500   0.1531   0.01403   0.00678  -0.0315   0.8701   1.0000
  -0.250   0.1734   0.01389   0.00655  -0.0299   0.8557   1.0000
   0.000   0.1941   0.01376   0.00634  -0.0283   0.8411   1.0000
   0.250   0.2153   0.01363   0.00615  -0.0268   0.8252   1.0000
   0.500   0.2370   0.01352   0.00597  -0.0254   0.8072   1.0000
   0.750   0.2587   0.01340   0.00579  -0.0239   0.7864   1.0000
   1.000   0.2804   0.01329   0.00560  -0.0223   0.7614   1.0000
   1.250   0.3021   0.01318   0.00540  -0.0207   0.7292   1.0000
   1.500   0.3233   0.01309   0.00516  -0.0187   0.6848   1.0000
   1.750   0.3436   0.01311   0.00485  -0.0165   0.6176   1.0000
   2.000   0.3640   0.01343   0.00465  -0.0145   0.5249   1.0000
   2.250   0.3859   0.01398   0.00469  -0.0134   0.4416   1.0000
   2.500   0.4090   0.01449   0.00484  -0.0127   0.3903   1.0000
   2.750   0.4326   0.01492   0.00504  -0.0120   0.3594   1.0000
   3.000   0.4565   0.01531   0.00525  -0.0114   0.3388   1.0000
   3.250   0.4806   0.01568   0.00548  -0.0108   0.3234   1.0000
   3.500   0.5048   0.01603   0.00575  -0.0102   0.3112   1.0000
   3.750   0.5291   0.01638   0.00603  -0.0097   0.3005   1.0000
   4.000   0.5533   0.01676   0.00632  -0.0091   0.2916   1.0000
   4.250   0.5778   0.01712   0.00665  -0.0085   0.2830   1.0000
   4.500   0.6022   0.01753   0.00700  -0.0079   0.2764   1.0000
   4.750   0.6269   0.01790   0.00738  -0.0074   0.2690   1.0000
   5.000   0.6512   0.01836   0.00776  -0.0069   0.2629   1.0000
   5.250   0.6763   0.01874   0.00821  -0.0064   0.2561   1.0000
   5.500   0.7010   0.01919   0.00864  -0.0060   0.2504   1.0000
   5.750   0.7259   0.01966   0.00912  -0.0055   0.2448   1.0000
   6.000   0.7508   0.02010   0.00965  -0.0051   0.2384   1.0000
   6.250   0.7755   0.02061   0.01012  -0.0047   0.2332   1.0000
   6.500   0.8004   0.02109   0.01072  -0.0043   0.2272   1.0000
   6.750   0.8251   0.02156   0.01127  -0.0039   0.2209   1.0000
   7.000   0.8496   0.02210   0.01183  -0.0035   0.2155   1.0000
   7.250   0.8740   0.02257   0.01247  -0.0030   0.2084   1.0000
   7.500   0.8981   0.02307   0.01298  -0.0026   0.2026   1.0000
   7.750   0.9220   0.02356   0.01367  -0.0021   0.1951   1.0000
   8.000   0.9455   0.02398   0.01414  -0.0017   0.1882   1.0000
   8.250   0.9687   0.02445   0.01481  -0.0011   0.1801   1.0000
   8.500   0.9913   0.02482   0.01523  -0.0006   0.1728   1.0000
   8.750   1.0139   0.02527   0.01592   0.0000   0.1635   1.0000
   9.000   1.0357   0.02565   0.01643   0.0007   0.1543   1.0000
   9.250   1.0567   0.02601   0.01685   0.0014   0.1447   1.0000
   9.500   1.0776   0.02648   0.01751   0.0021   0.1330   1.0000
   9.750   1.0976   0.02706   0.01821   0.0028   0.1207   1.0000
  10.000   1.1165   0.02778   0.01902   0.0037   0.1082   1.0000
  10.250   1.1338   0.02867   0.01997   0.0047   0.0959   1.0000
  10.500   1.1493   0.02977   0.02113   0.0058   0.0849   1.0000
  10.750   1.1625   0.03107   0.02251   0.0071   0.0759   1.0000
  11.000   1.1722   0.03257   0.02401   0.0086   0.0687   1.0000
  11.250   1.1816   0.03408   0.02569   0.0102   0.0624   1.0000
  11.500   1.1849   0.03586   0.02749   0.0123   0.0584   1.0000
  11.750   1.1878   0.03755   0.02938   0.0145   0.0547   1.0000
  12.000   1.1880   0.03947   0.03144   0.0165   0.0517   1.0000
  12.250   1.1849   0.04174   0.03379   0.0181   0.0494   1.0000
  12.500   1.1811   0.04430   0.03646   0.0193   0.0475   1.0000
  12.750   1.1782   0.04702   0.03940   0.0201   0.0455   1.0000
  13.000   1.1730   0.05014   0.04270   0.0204   0.0439   1.0000
  13.250   1.1660   0.05369   0.04645   0.0200   0.0427   1.0000
  13.500   1.1574   0.05775   0.05066   0.0190   0.0417   1.0000
  13.750   1.1471   0.06236   0.05542   0.0173   0.0410   1.0000
  14.000   1.1359   0.06747   0.06066   0.0150   0.0403   1.0000
  14.250   1.1245   0.07285   0.06615   0.0125   0.0397   1.0000
  14.500   1.1151   0.07791   0.07126   0.0103   0.0390   1.0000
  14.750   1.1003   0.08450   0.07806   0.0068   0.0386   1.0000
  15.000   1.0839   0.09160   0.08535   0.0030   0.0383   1.0000
  15.250   1.0656   0.09924   0.09317  -0.0012   0.0380   1.0000
  15.500   1.0447   0.10760   0.10170  -0.0057   0.0378   1.0000
  15.750   1.0207   0.11688   0.11115  -0.0108   0.0377   1.0000
  16.000   0.9910   0.12786   0.12227  -0.0168   0.0377   1.0000
  16.250   0.9414   0.14489   0.13944  -0.0261   0.0380   1.0000
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