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AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AQUILA 9.3% smoothed (aquilasm-il)
Reynolds number: 100,000
Max Cl/Cd: 56.44 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-aquilasm-il-100000-n5.txt
Download as CSV file: xf-aquilasm-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3192   0.09470   0.09009  -0.0341   1.0000   0.0445
  -7.750  -0.3252   0.09257   0.08807  -0.0356   1.0000   0.0447
  -7.500  -0.3274   0.09007   0.08563  -0.0379   1.0000   0.0448
  -7.250  -0.3297   0.08761   0.08322  -0.0393   1.0000   0.0449
  -7.000  -0.3342   0.08541   0.08107  -0.0393   1.0000   0.0450
  -6.750  -0.3168   0.08131   0.07686  -0.0450   0.9908   0.0451
  -6.500  -0.3031   0.07503   0.07074  -0.0442   0.9847   0.0463
  -6.250  -0.2822   0.07091   0.06662  -0.0463   0.9750   0.0475
  -6.000  -0.2570   0.06686   0.06253  -0.0506   0.9650   0.0497
  -5.750  -0.1643   0.04557   0.04105  -0.0674   0.9208   0.0590
  -5.500  -0.1485   0.04092   0.03649  -0.0673   0.9118   0.0608
  -5.250  -0.1304   0.03720   0.03269  -0.0686   0.9002   0.0626
  -5.000  -0.1127   0.03371   0.02907  -0.0700   0.8874   0.0648
  -4.750  -0.0940   0.03035   0.02552  -0.0714   0.8749   0.0672
  -4.500  -0.0717   0.02742   0.02219  -0.0730   0.8625   0.0714
  -4.000  -0.0319   0.03487   0.02827  -0.0763   0.8711   0.0329
  -3.750  -0.0082   0.03234   0.02548  -0.0762   0.8588   0.0321
  -3.500   0.0168   0.03000   0.02278  -0.0760   0.8471   0.0314
  -3.250   0.0428   0.02785   0.02025  -0.0755   0.8360   0.0309
  -3.000   0.0697   0.02595   0.01795  -0.0751   0.8256   0.0309
  -2.750   0.0963   0.02452   0.01607  -0.0743   0.8139   0.0328
  -2.500   0.1235   0.02339   0.01451  -0.0735   0.8025   0.0339
  -2.250   0.1500   0.02176   0.01260  -0.0729   0.7919   0.0344
  -2.000   0.1770   0.02039   0.01103  -0.0723   0.7818   0.0354
  -1.750   0.2031   0.01940   0.00990  -0.0717   0.7702   0.0367
  -1.500   0.2293   0.01865   0.00904  -0.0711   0.7589   0.0397
  -1.250   0.2558   0.01804   0.00827  -0.0703   0.7484   0.0442
  -1.000   0.2809   0.01717   0.00736  -0.0695   0.7383   0.0473
  -0.750   0.3057   0.01671   0.00687  -0.0687   0.7266   0.0548
  -0.500   0.3307   0.01622   0.00627  -0.0678   0.7157   0.0618
  -0.250   0.3567   0.01586   0.00580  -0.0671   0.7053   0.0770
   0.000   0.3832   0.01536   0.00540  -0.0667   0.6947   0.1242
   0.500   0.4680   0.01308   0.00501  -0.0720   0.6715   1.0000
   0.750   0.4927   0.01320   0.00493  -0.0712   0.6607   1.0000
   1.000   0.5175   0.01333   0.00486  -0.0704   0.6499   1.0000
   1.250   0.5420   0.01348   0.00487  -0.0697   0.6382   1.0000
   1.500   0.5667   0.01363   0.00488  -0.0690   0.6268   1.0000
   1.750   0.5915   0.01378   0.00491  -0.0683   0.6158   1.0000
   2.000   0.6164   0.01394   0.00493  -0.0675   0.6052   1.0000
   2.250   0.6411   0.01412   0.00502  -0.0669   0.5934   1.0000
   2.500   0.6658   0.01430   0.00512  -0.0662   0.5818   1.0000
   2.750   0.6905   0.01448   0.00523  -0.0655   0.5706   1.0000
   3.000   0.7153   0.01468   0.00535  -0.0649   0.5596   1.0000
   3.250   0.7400   0.01488   0.00548  -0.0642   0.5481   1.0000
   3.500   0.7645   0.01509   0.00566  -0.0636   0.5361   1.0000
   3.750   0.7890   0.01532   0.00587  -0.0629   0.5243   1.0000
   4.000   0.8135   0.01555   0.00607  -0.0623   0.5129   1.0000
   4.250   0.8380   0.01579   0.00626  -0.0616   0.5014   1.0000
   4.500   0.8622   0.01604   0.00649  -0.0609   0.4897   1.0000
   4.750   0.8863   0.01631   0.00679  -0.0603   0.4773   1.0000
   5.000   0.9102   0.01659   0.00708  -0.0596   0.4652   1.0000
   5.250   0.9341   0.01689   0.00738  -0.0589   0.4533   1.0000
   5.500   0.9577   0.01720   0.00769  -0.0582   0.4415   1.0000
   5.750   0.9812   0.01753   0.00804  -0.0575   0.4300   1.0000
   6.000   1.0044   0.01787   0.00842  -0.0568   0.4178   1.0000
   6.250   1.0275   0.01823   0.00883  -0.0560   0.4056   1.0000
   6.500   1.0503   0.01861   0.00925  -0.0553   0.3938   1.0000
   6.750   1.0729   0.01901   0.00972  -0.0545   0.3822   1.0000
   7.000   1.0952   0.01943   0.01017  -0.0536   0.3710   1.0000
   7.250   1.1172   0.01987   0.01067  -0.0528   0.3595   1.0000
   7.500   1.1388   0.02034   0.01122  -0.0519   0.3477   1.0000
   7.750   1.1601   0.02082   0.01182  -0.0510   0.3362   1.0000
   8.000   1.1809   0.02133   0.01240  -0.0500   0.3249   1.0000
   8.250   1.2010   0.02186   0.01299  -0.0489   0.3134   1.0000
   8.500   1.2203   0.02241   0.01361  -0.0478   0.3013   1.0000
   8.750   1.2383   0.02298   0.01429  -0.0465   0.2875   1.0000
   9.000   1.2550   0.02359   0.01497  -0.0450   0.2729   1.0000
   9.250   1.2706   0.02424   0.01570  -0.0435   0.2576   1.0000
   9.500   1.2854   0.02493   0.01649  -0.0418   0.2428   1.0000
   9.750   1.2989   0.02568   0.01734  -0.0401   0.2281   1.0000
  10.000   1.3110   0.02649   0.01828  -0.0382   0.2136   1.0000
  10.250   1.3210   0.02737   0.01927  -0.0361   0.1986   1.0000
  10.500   1.3276   0.02834   0.02032  -0.0335   0.1837   1.0000
  10.750   1.3320   0.02948   0.02152  -0.0309   0.1678   1.0000
  11.000   1.3337   0.03087   0.02294  -0.0284   0.1511   1.0000
  11.250   1.3330   0.03256   0.02463  -0.0261   0.1344   1.0000
  11.500   1.3307   0.03455   0.02662  -0.0241   0.1162   1.0000
  11.750   1.3252   0.03698   0.02903  -0.0224   0.1000   1.0000
  12.000   1.3183   0.03976   0.03177  -0.0211   0.0861   1.0000
  12.250   1.3109   0.04282   0.03482  -0.0202   0.0743   1.0000
  12.500   1.3042   0.04602   0.03807  -0.0198   0.0653   1.0000
  12.750   1.2957   0.04962   0.04172  -0.0197   0.0580   1.0000
  13.000   1.2864   0.05352   0.04569  -0.0199   0.0524   1.0000
  13.250   1.2772   0.05760   0.04988  -0.0205   0.0481   1.0000
  13.500   1.2681   0.06186   0.05429  -0.0212   0.0445   1.0000
  13.750   1.2555   0.06677   0.05928  -0.0225   0.0416   1.0000
  14.000   1.2440   0.07172   0.06435  -0.0239   0.0390   1.0000
  14.250   1.2344   0.07662   0.06941  -0.0254   0.0365   1.0000
  14.500   1.2232   0.08192   0.07484  -0.0272   0.0345   1.0000
  14.750   1.2111   0.08756   0.08058  -0.0293   0.0328   1.0000
  15.000   1.1988   0.09333   0.08638  -0.0315   0.0315   1.0000
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