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AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AQUILA 9.3% smoothed (aquilasm-il)
Reynolds number: 50,000
Max Cl/Cd: 36.96 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-aquilasm-il-50000-n5.txt
Download as CSV file: xf-aquilasm-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AQUILA 9.3% smoothed                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3182   0.10121   0.09461  -0.0286   1.0000   0.0989
  -8.000  -0.3276   0.09987   0.09342  -0.0307   1.0000   0.1017
  -7.750  -0.3415   0.09879   0.09252  -0.0333   1.0000   0.1026
  -7.500  -0.3382   0.09502   0.08885  -0.0330   1.0000   0.1038
  -7.250  -0.3248   0.09098   0.08484  -0.0297   1.0000   0.1074
  -7.000  -0.3250   0.08849   0.08247  -0.0294   1.0000   0.1107
  -6.750  -0.3316   0.08652   0.08062  -0.0303   1.0000   0.1147
  -6.500  -0.3493   0.08601   0.08018  -0.0343   1.0000   0.1175
  -6.250  -0.3478   0.08237   0.07668  -0.0311   1.0000   0.1193
  -6.000  -0.3479   0.07982   0.07423  -0.0277   1.0000   0.1222
  -5.750  -0.3527   0.07794   0.07241  -0.0260   1.0000   0.1256
  -5.500  -0.3455   0.07496   0.06936  -0.0314   0.9942   0.1343
  -5.250  -0.3192   0.07087   0.06526  -0.0340   0.9847   0.1426
  -5.000  -0.2925   0.06680   0.06109  -0.0389   0.9732   0.1551
  -4.750  -0.2652   0.06308   0.05728  -0.0435   0.9619   0.1719
  -4.500  -0.2032   0.05495   0.04815  -0.0559   0.9508   0.0714
  -4.250  -0.1703   0.05071   0.04374  -0.0595   0.9424   0.0658
  -3.750  -0.0992   0.04410   0.03597  -0.0654   0.9209   0.0579
  -3.500  -0.0627   0.04074   0.03232  -0.0683   0.9134   0.0567
  -3.250  -0.0323   0.03813   0.02936  -0.0695   0.9026   0.0555
  -3.000  -0.0005   0.03578   0.02661  -0.0706   0.8923   0.0545
  -2.750   0.0358   0.03350   0.02385  -0.0720   0.8840   0.0541
  -2.500   0.0673   0.03176   0.02170  -0.0724   0.8733   0.0551
  -2.250   0.0991   0.03045   0.01989  -0.0725   0.8626   0.0577
  -2.000   0.1332   0.02873   0.01787  -0.0733   0.8538   0.0601
  -1.750   0.1645   0.02738   0.01633  -0.0734   0.8434   0.0621
  -1.500   0.1951   0.02638   0.01516  -0.0734   0.8324   0.0670
  -1.250   0.2286   0.02552   0.01397  -0.0734   0.8227   0.0734
  -1.000   0.2596   0.02452   0.01288  -0.0735   0.8127   0.0799
  -0.750   0.2860   0.02393   0.01216  -0.0728   0.8009   0.0920
  -0.500   0.3129   0.02333   0.01147  -0.0723   0.7897   0.1074
  -0.250   0.3712   0.01964   0.01047  -0.0773   0.7828   1.0000
   0.000   0.3959   0.01984   0.01017  -0.0762   0.7702   1.0000
   0.250   0.4207   0.02003   0.01001  -0.0753   0.7580   1.0000
   0.500   0.4460   0.02021   0.00990  -0.0745   0.7462   1.0000
   0.750   0.4721   0.02036   0.00979  -0.0738   0.7351   1.0000
   1.000   0.4980   0.02052   0.00973  -0.0731   0.7238   1.0000
   1.250   0.5217   0.02076   0.00980  -0.0722   0.7113   1.0000
   1.500   0.5459   0.02101   0.00989  -0.0713   0.6991   1.0000
   1.750   0.5705   0.02123   0.00997  -0.0705   0.6873   1.0000
   2.000   0.5960   0.02142   0.01003  -0.0697   0.6761   1.0000
   2.250   0.6215   0.02161   0.01010  -0.0690   0.6649   1.0000
   2.500   0.6450   0.02191   0.01032  -0.0681   0.6523   1.0000
   2.750   0.6687   0.02220   0.01055  -0.0672   0.6399   1.0000
   3.000   0.6929   0.02248   0.01078  -0.0664   0.6280   1.0000
   3.250   0.7177   0.02273   0.01097  -0.0656   0.6164   1.0000
   3.500   0.7434   0.02293   0.01109  -0.0648   0.6055   1.0000
   3.750   0.7664   0.02329   0.01144  -0.0639   0.5928   1.0000
   4.000   0.7895   0.02365   0.01183  -0.0630   0.5801   1.0000
   4.250   0.8129   0.02400   0.01219  -0.0622   0.5678   1.0000
   4.500   0.8365   0.02435   0.01254  -0.0613   0.5557   1.0000
   4.750   0.8607   0.02467   0.01286  -0.0605   0.5440   1.0000
   5.000   0.8856   0.02494   0.01317  -0.0597   0.5326   1.0000
   5.250   0.9077   0.02540   0.01369  -0.0588   0.5197   1.0000
   5.500   0.9298   0.02587   0.01422  -0.0579   0.5071   1.0000
   5.750   0.9521   0.02634   0.01476  -0.0569   0.4947   1.0000
   6.000   0.9746   0.02681   0.01533  -0.0560   0.4826   1.0000
   6.250   0.9976   0.02725   0.01583  -0.0552   0.4708   1.0000
   6.500   1.0215   0.02764   0.01625  -0.0543   0.4596   1.0000
   6.750   1.0421   0.02824   0.01699  -0.0533   0.4470   1.0000
   7.000   1.0625   0.02888   0.01780  -0.0523   0.4347   1.0000
   7.250   1.0830   0.02952   0.01856  -0.0512   0.4226   1.0000
   7.500   1.1040   0.03014   0.01929  -0.0502   0.4111   1.0000
   7.750   1.1257   0.03070   0.01995  -0.0492   0.3997   1.0000
   8.000   1.1465   0.03132   0.02073  -0.0482   0.3882   1.0000
   8.250   1.1641   0.03215   0.02175  -0.0469   0.3760   1.0000
   8.500   1.1817   0.03298   0.02275  -0.0456   0.3640   1.0000
   8.750   1.1995   0.03377   0.02371  -0.0443   0.3522   1.0000
   9.000   1.2175   0.03453   0.02464  -0.0430   0.3404   1.0000
   9.250   1.2350   0.03524   0.02549  -0.0416   0.3281   1.0000
   9.500   1.2512   0.03597   0.02633  -0.0401   0.3154   1.0000
   9.750   1.2628   0.03688   0.02743  -0.0381   0.3017   1.0000
  10.000   1.2722   0.03782   0.02852  -0.0360   0.2877   1.0000
  10.250   1.2790   0.03883   0.02971  -0.0337   0.2735   1.0000
  10.500   1.2823   0.03997   0.03098  -0.0311   0.2595   1.0000
  10.750   1.2809   0.04132   0.03246  -0.0282   0.2462   1.0000
  11.000   1.2781   0.04292   0.03420  -0.0256   0.2331   1.0000
  11.250   1.2742   0.04480   0.03620  -0.0235   0.2203   1.0000
  11.500   1.2694   0.04695   0.03847  -0.0218   0.2074   1.0000
  11.750   1.2637   0.04941   0.04105  -0.0205   0.1945   1.0000
  12.000   1.2574   0.05218   0.04391  -0.0196   0.1818   1.0000
  12.250   1.2504   0.05524   0.04706  -0.0191   0.1693   1.0000
  12.500   1.2426   0.05861   0.05048  -0.0190   0.1571   1.0000
  12.750   1.2347   0.06218   0.05408  -0.0191   0.1457   1.0000
  13.000   1.2269   0.06589   0.05777  -0.0194   0.1348   1.0000
  13.250   1.2168   0.07027   0.06230  -0.0202   0.1246   1.0000
  13.500   1.2070   0.07478   0.06689  -0.0211   0.1154   1.0000
  13.750   1.1992   0.07899   0.07108  -0.0220   0.1072   1.0000
  14.000   1.1900   0.08368   0.07584  -0.0233   0.0994   1.0000
  14.250   1.1805   0.08866   0.08091  -0.0248   0.0926   1.0000
  14.500   1.1740   0.09303   0.08525  -0.0261   0.0858   1.0000
  14.750   1.1636   0.09867   0.09107  -0.0281   0.0807   1.0000
  15.000   1.1569   0.10346   0.09588  -0.0299   0.0749   1.0000
  15.250   1.1481   0.10899   0.10151  -0.0321   0.0705   1.0000
  15.500   1.1366   0.11545   0.10818  -0.0350   0.0670   1.0000
  15.750   1.1376   0.11857   0.11111  -0.0360   0.0613   1.0000
  16.000   1.1221   0.12649   0.11934  -0.0400   0.0594   1.0000
  16.250   1.1058   0.13497   0.12804  -0.0445   0.0582   1.0000
  16.500   1.0850   0.14518   0.13843  -0.0501   0.0579   1.0000
  16.750   1.0595   0.15772   0.15103  -0.0571   0.0586   1.0000
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