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NASA/AMES A-03 AIRFOIL (ames03-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA/AMES A-03 AIRFOIL (ames03-il)
Reynolds number: 100,000
Max Cl/Cd: 39.56 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ames03-il-100000-n5.txt
Download as CSV file: xf-ames03-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6607   0.06437   0.05953  -0.0299   0.9762   0.0266
  -8.750  -0.6639   0.05937   0.05425  -0.0314   0.9693   0.0266
  -8.500  -0.6641   0.05456   0.04907  -0.0321   0.9633   0.0266
  -8.250  -0.6612   0.04982   0.04385  -0.0323   0.9583   0.0267
  -8.000  -0.6504   0.04660   0.04043  -0.0324   0.9542   0.0274
  -7.750  -0.6329   0.04504   0.03879  -0.0325   0.9506   0.0286
  -7.500  -0.6174   0.04239   0.03583  -0.0324   0.9469   0.0298
  -7.250  -0.6013   0.03910   0.03207  -0.0320   0.9429   0.0306
  -7.000  -0.5834   0.03593   0.02838  -0.0314   0.9394   0.0311
  -6.750  -0.5630   0.03323   0.02518  -0.0308   0.9365   0.0318
  -6.500  -0.5390   0.03079   0.02224  -0.0306   0.9338   0.0328
  -6.250  -0.5138   0.02895   0.01994  -0.0303   0.9310   0.0346
  -6.000  -0.4893   0.02754   0.01848  -0.0304   0.9281   0.0367
  -5.750  -0.4639   0.02628   0.01705  -0.0301   0.9254   0.0387
  -5.500  -0.4382   0.02502   0.01560  -0.0297   0.9230   0.0406
  -5.250  -0.4107   0.02389   0.01426  -0.0297   0.9205   0.0431
  -5.000  -0.3847   0.02283   0.01321  -0.0298   0.9181   0.0470
  -4.750  -0.3586   0.02201   0.01235  -0.0297   0.9157   0.0509
  -4.500  -0.3330   0.02129   0.01150  -0.0294   0.9132   0.0552
  -4.250  -0.3088   0.02058   0.01084  -0.0290   0.9108   0.0623
  -4.000  -0.2831   0.01995   0.01016  -0.0288   0.9084   0.0706
  -3.750  -0.2564   0.01934   0.00959  -0.0290   0.9060   0.0854
  -3.500  -0.2301   0.01873   0.00909  -0.0290   0.9037   0.1113
  -3.250  -0.2051   0.01795   0.00868  -0.0291   0.9014   0.1811
  -3.000  -0.1835   0.01675   0.00839  -0.0287   0.8989   0.3659
  -2.750  -0.1663   0.01576   0.00854  -0.0263   0.8967   0.6226
  -2.500  -0.1449   0.01573   0.00886  -0.0239   0.8945   0.7442
  -2.250  -0.1217   0.01590   0.00909  -0.0220   0.8922   0.8090
  -2.000  -0.0986   0.01613   0.00930  -0.0201   0.8888   0.8547
  -1.750  -0.0744   0.01636   0.00947  -0.0181   0.8844   0.8904
  -1.500  -0.0453   0.01657   0.00959  -0.0169   0.8791   0.9239
  -1.250  -0.0058   0.01666   0.00957  -0.0181   0.8721   0.9482
  -1.000   0.0287   0.01663   0.00941  -0.0189   0.8661   0.9602
  -0.750   0.0651   0.01656   0.00925  -0.0207   0.8590   0.9692
  -0.500   0.1005   0.01645   0.00904  -0.0219   0.8530   0.9762
  -0.250   0.1367   0.01635   0.00887  -0.0237   0.8446   0.9841
   0.000   0.1697   0.01615   0.00860  -0.0243   0.8376   0.9912
   0.250   0.2055   0.01597   0.00839  -0.0260   0.8272   0.9983
   0.500   0.2275   0.01576   0.00814  -0.0247   0.8172   1.0000
   0.750   0.2436   0.01546   0.00779  -0.0219   0.8072   1.0000
   1.000   0.2634   0.01520   0.00751  -0.0201   0.7942   1.0000
   1.250   0.2837   0.01496   0.00725  -0.0185   0.7809   1.0000
   1.500   0.3044   0.01471   0.00700  -0.0168   0.7668   1.0000
   1.750   0.3256   0.01447   0.00674  -0.0152   0.7508   1.0000
   2.000   0.3480   0.01425   0.00653  -0.0140   0.7304   1.0000
   2.250   0.3718   0.01408   0.00638  -0.0131   0.7013   1.0000
   2.500   0.3943   0.01385   0.00611  -0.0116   0.6462   1.0000
   2.750   0.4040   0.01353   0.00492  -0.0058   0.4962   1.0000
   3.000   0.4263   0.01444   0.00512  -0.0053   0.3876   1.0000
   3.250   0.4512   0.01505   0.00543  -0.0052   0.3430   1.0000
   3.500   0.4765   0.01553   0.00572  -0.0052   0.3182   1.0000
   3.750   0.5020   0.01597   0.00602  -0.0050   0.3010   1.0000
   4.000   0.5278   0.01637   0.00633  -0.0049   0.2873   1.0000
   4.250   0.5538   0.01676   0.00668  -0.0048   0.2763   1.0000
   4.500   0.5797   0.01719   0.00704  -0.0046   0.2669   1.0000
   4.750   0.6057   0.01762   0.00743  -0.0045   0.2577   1.0000
   5.000   0.6320   0.01806   0.00785  -0.0044   0.2493   1.0000
   5.250   0.6580   0.01854   0.00832  -0.0043   0.2416   1.0000
   5.500   0.6844   0.01900   0.00881  -0.0043   0.2335   1.0000
   5.750   0.7105   0.01951   0.00930  -0.0043   0.2262   1.0000
   6.000   0.7369   0.01999   0.00988  -0.0043   0.2184   1.0000
   6.250   0.7629   0.02052   0.01040  -0.0042   0.2110   1.0000
   6.500   0.7893   0.02102   0.01102  -0.0042   0.2032   1.0000
   6.750   0.8150   0.02155   0.01156  -0.0042   0.1957   1.0000
   7.000   0.8411   0.02205   0.01225  -0.0043   0.1874   1.0000
   7.250   0.8665   0.02258   0.01278  -0.0042   0.1800   1.0000
   7.500   0.8922   0.02307   0.01348  -0.0042   0.1708   1.0000
   7.750   0.9172   0.02357   0.01408  -0.0042   0.1625   1.0000
   8.000   0.9420   0.02405   0.01470  -0.0041   0.1533   1.0000
   8.250   0.9664   0.02456   0.01538  -0.0041   0.1429   1.0000
   8.500   0.9902   0.02507   0.01600  -0.0040   0.1324   1.0000
   8.750   1.0132   0.02561   0.01663  -0.0038   0.1211   1.0000
   9.000   1.0356   0.02624   0.01736  -0.0036   0.1094   1.0000
   9.250   1.0570   0.02700   0.01818  -0.0034   0.0976   1.0000
   9.500   1.0774   0.02792   0.01918  -0.0031   0.0859   1.0000
   9.750   1.0968   0.02902   0.02039  -0.0026   0.0753   1.0000
  10.000   1.1145   0.03031   0.02180  -0.0020   0.0664   1.0000
  10.250   1.1295   0.03179   0.02336  -0.0013   0.0595   1.0000
  10.500   1.1438   0.03327   0.02499  -0.0005   0.0532   1.0000
  10.750   1.1544   0.03503   0.02685   0.0006   0.0489   1.0000
  11.000   1.1646   0.03681   0.02884   0.0017   0.0453   1.0000
  11.250   1.1700   0.03860   0.03075   0.0030   0.0426   1.0000
  11.500   1.1714   0.04074   0.03295   0.0045   0.0405   1.0000
  11.750   1.1752   0.04291   0.03540   0.0058   0.0383   1.0000
  12.000   1.1765   0.04529   0.03798   0.0068   0.0364   1.0000
  12.250   1.1759   0.04788   0.04077   0.0077   0.0351   1.0000
  12.500   1.1736   0.05072   0.04376   0.0083   0.0341   1.0000
  12.750   1.1694   0.05388   0.04705   0.0085   0.0333   1.0000
  13.000   1.1635   0.05740   0.05068   0.0084   0.0326   1.0000
  13.250   1.1550   0.06153   0.05501   0.0078   0.0320   1.0000
  13.500   1.1432   0.06644   0.06018   0.0063   0.0315   1.0000
  13.750   1.1285   0.07221   0.06621   0.0037   0.0312   1.0000
  14.000   1.1110   0.07912   0.07335  -0.0002   0.0310   1.0000
  14.250   1.0907   0.08731   0.08177  -0.0053   0.0310   1.0000
  14.500   1.0676   0.09676   0.09141  -0.0114   0.0311   1.0000
  14.750   1.0415   0.10721   0.10203  -0.0178   0.0314   1.0000
  15.000   1.0115   0.11879   0.11372  -0.0247   0.0317   1.0000
  15.250   0.9769   0.13194   0.12697  -0.0322   0.0321   1.0000
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