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AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: AQUILA 9.3% smoothed (aquilasm-il)
Reynolds number: 50,000
Max Cl/Cd: 25.35 at α=11.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-aquilasm-il-50000.txt
Download as CSV file: xf-aquilasm-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3354   0.10725   0.10070  -0.0256   1.0000   0.1572
  -8.250  -0.3239   0.10279   0.09629  -0.0249   1.0000   0.1624
  -8.000  -0.3229   0.10048   0.09407  -0.0251   1.0000   0.1703
  -7.750  -0.3440   0.10049   0.09429  -0.0267   1.0000   0.1729
  -7.500  -0.3200   0.09499   0.08878  -0.0246   1.0000   0.1835
  -7.250  -0.3420   0.09474   0.08876  -0.0255   1.0000   0.1876
  -7.000  -0.3262   0.09038   0.08444  -0.0228   1.0000   0.1972
  -6.750  -0.3492   0.09011   0.08437  -0.0247   1.0000   0.2029
  -6.500  -0.3368   0.08616   0.08050  -0.0209   1.0000   0.2139
  -6.250  -0.3645   0.08643   0.08093  -0.0229   1.0000   0.2184
  -6.000  -0.3573   0.08292   0.07752  -0.0181   1.0000   0.2314
  -5.750  -0.3604   0.08049   0.07520  -0.0147   1.0000   0.2410
  -5.500  -0.3809   0.07980   0.07461  -0.0150   1.0000   0.2495
  -5.250  -0.3899   0.07846   0.07333  -0.0134   1.0000   0.2634
  -5.000  -0.3956   0.07657   0.07151  -0.0114   1.0000   0.2787
  -4.750  -0.3966   0.07379   0.06882  -0.0068   1.0000   0.2953
  -4.500   0.0895   0.04189   0.03573  -0.0337   1.0000   1.0000
  -4.250   0.0962   0.04041   0.03436  -0.0338   1.0000   1.0000
  -3.750   0.0396   0.04244   0.03683  -0.0181   1.0000   0.9712
  -3.500  -0.0118   0.04456   0.03923  -0.0062   1.0000   0.9457
  -3.250  -0.0645   0.04664   0.04155   0.0051   1.0000   0.9271
  -3.000  -0.1125   0.04791   0.04301   0.0146   1.0000   0.9033
  -2.750  -0.1605   0.04893   0.04424   0.0237   1.0000   0.8846
  -2.500  -0.2038   0.04948   0.04495   0.0316   1.0000   0.8686
  -2.250  -0.2487   0.04964   0.04527   0.0396   1.0000   0.8531
  -2.000  -0.2935   0.04931   0.04511   0.0461   0.9967   0.8286
  -1.750  -0.3350   0.04849   0.04441   0.0487   0.9792   0.7938
  -1.500  -0.0457   0.03815   0.02926  -0.0509   0.9573   0.1555
  -1.250  -0.0034   0.03658   0.02719  -0.0534   0.9457   0.1468
  -1.000   0.0396   0.03547   0.02558  -0.0557   0.9341   0.1398
  -0.750   0.0845   0.03437   0.02411  -0.0584   0.9228   0.1375
  -0.500   0.1317   0.03360   0.02297  -0.0613   0.9114   0.1444
  -0.250   0.1736   0.03284   0.02208  -0.0633   0.8993   0.1525
   0.000   0.2109   0.03236   0.02151  -0.0648   0.8867   0.1719
   0.250   0.2476   0.03178   0.02103  -0.0663   0.8742   0.2056
   0.500   0.3090   0.02923   0.02028  -0.0708   0.8639   1.0000
   0.750   0.3473   0.02983   0.02038  -0.0726   0.8506   1.0000
   1.000   0.3891   0.03034   0.02054  -0.0751   0.8377   1.0000
   1.250   0.4227   0.03090   0.02087  -0.0762   0.8238   1.0000
   1.500   0.4534   0.03150   0.02130  -0.0769   0.8097   1.0000
   1.750   0.4833   0.03210   0.02174  -0.0774   0.7956   1.0000
   2.000   0.5115   0.03273   0.02225  -0.0775   0.7816   1.0000
   2.250   0.5386   0.03337   0.02280  -0.0774   0.7676   1.0000
   2.500   0.5655   0.03400   0.02335  -0.0772   0.7536   1.0000
   2.750   0.5915   0.03466   0.02395  -0.0769   0.7398   1.0000
   3.000   0.6173   0.03532   0.02456  -0.0765   0.7260   1.0000
   3.250   0.6427   0.03597   0.02519  -0.0759   0.7123   1.0000
   3.500   0.6684   0.03661   0.02582  -0.0754   0.6988   1.0000
   3.750   0.6947   0.03719   0.02640  -0.0748   0.6857   1.0000
   4.000   0.7244   0.03755   0.02675  -0.0743   0.6730   1.0000
   4.250   0.7586   0.03757   0.02682  -0.0740   0.6614   1.0000
   4.500   0.7784   0.03846   0.02774  -0.0728   0.6474   1.0000
   4.750   0.7968   0.03947   0.02878  -0.0716   0.6334   1.0000
   5.000   0.8147   0.04055   0.02990  -0.0703   0.6196   1.0000
   5.250   0.8320   0.04169   0.03110  -0.0691   0.6059   1.0000
   5.500   0.8479   0.04300   0.03250  -0.0678   0.5924   1.0000
   5.750   0.8640   0.04431   0.03388  -0.0665   0.5792   1.0000
   6.000   0.8807   0.04562   0.03526  -0.0653   0.5666   1.0000
   6.250   0.9064   0.04618   0.03590  -0.0644   0.5549   1.0000
   6.500   0.9455   0.04555   0.03543  -0.0637   0.5444   1.0000
   6.750   0.9499   0.04792   0.03789  -0.0621   0.5310   1.0000
   7.000   0.9499   0.05073   0.04078  -0.0606   0.5177   1.0000
   7.250   0.9408   0.05452   0.04462  -0.0591   0.5049   1.0000
   7.500   0.9238   0.05903   0.04914  -0.0578   0.4931   1.0000
   7.750   0.9515   0.05947   0.04972  -0.0566   0.4826   1.0000
   8.000   1.0002   0.05787   0.04840  -0.0556   0.4719   1.0000
   8.250   0.9196   0.06922   0.05951  -0.0558   0.4609   1.0000
   8.500   0.9132   0.07333   0.06365  -0.0556   0.4513   1.0000
   8.750   0.9456   0.07348   0.06403  -0.0543   0.4406   1.0000
   9.000   0.9076   0.08101   0.07150  -0.0554   0.4327   1.0000
   9.250   0.9126   0.08426   0.07483  -0.0552   0.4239   1.0000
  10.500   1.2710   0.05557   0.04805  -0.0383   0.3259   1.0000
  10.750   1.2017   0.06504   0.05752  -0.0356   0.3267   1.0000
  11.000   1.2037   0.06650   0.05910  -0.0332   0.3114   1.0000
  11.250   1.1929   0.06970   0.06239  -0.0316   0.2987   1.0000
  11.500   1.1958   0.07102   0.06386  -0.0295   0.2821   1.0000
  11.750   1.3522   0.05335   0.04575  -0.0238   0.1956   1.0000
  12.000   1.3442   0.05549   0.04791  -0.0205   0.1807   1.0000
  12.250   1.3363   0.05778   0.05021  -0.0177   0.1669   1.0000
  12.500   1.3291   0.06039   0.05282  -0.0155   0.1543   1.0000
  12.750   1.3233   0.06310   0.05551  -0.0138   0.1425   1.0000
  13.000   1.3193   0.06588   0.05824  -0.0124   0.1309   1.0000
  13.250   1.2953   0.07108   0.06377  -0.0121   0.1293   1.0000
  13.500   1.2688   0.07708   0.07004  -0.0130   0.1286   1.0000
  13.750   1.2390   0.08430   0.07750  -0.0151   0.1297   1.0000
  14.000   1.2082   0.09249   0.08585  -0.0182   0.1313   1.0000
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