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AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: AQUILA 9.3% smoothed (aquilasm-il)
Reynolds number: 500,000
Max Cl/Cd: 99.57 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-aquilasm-il-500000-n5.txt
Download as CSV file: xf-aquilasm-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2432   0.09247   0.09038  -0.0291   1.0000   0.0118
  -9.250  -0.2402   0.08915   0.08707  -0.0299   1.0000   0.0118
  -9.000  -0.2372   0.08596   0.08390  -0.0305   1.0000   0.0121
  -8.750  -0.2263   0.08164   0.07957  -0.0338   0.9745   0.0125
  -8.500  -0.2114   0.07666   0.07457  -0.0386   0.9539   0.0133
  -8.250  -0.1976   0.07158   0.06944  -0.0435   0.9318   0.0139
  -8.000  -0.1931   0.06690   0.06469  -0.0479   0.9042   0.0145
  -7.750  -0.1935   0.06320   0.06091  -0.0498   0.8778   0.0145
  -7.500  -0.1966   0.05984   0.05748  -0.0514   0.8555   0.0146
  -7.250  -0.2023   0.05665   0.05423  -0.0526   0.8353   0.0147
  -7.000  -0.2023   0.05292   0.05044  -0.0552   0.8198   0.0147
  -6.750  -0.1983   0.04889   0.04632  -0.0578   0.8057   0.0147
  -6.500  -0.1917   0.04475   0.04209  -0.0602   0.7932   0.0147
  -6.250  -0.1830   0.04056   0.03779  -0.0622   0.7816   0.0147
  -6.000  -0.1721   0.03643   0.03353  -0.0640   0.7700   0.0147
  -5.750  -0.1594   0.03238   0.02934  -0.0653   0.7593   0.0147
  -5.250  -0.1362   0.03656   0.03288  -0.0738   0.7652   0.0110
  -5.000  -0.1171   0.03255   0.02858  -0.0737   0.7539   0.0110
  -4.750  -0.0970   0.02893   0.02465  -0.0733   0.7427   0.0110
  -4.500  -0.0762   0.02525   0.02060  -0.0725   0.7327   0.0111
  -4.250  -0.0557   0.02172   0.01665  -0.0716   0.7225   0.0113
  -4.000  -0.0318   0.02082   0.01557  -0.0713   0.7114   0.0117
  -3.750  -0.0075   0.01944   0.01397  -0.0708   0.7009   0.0120
  -3.500   0.0153   0.01556   0.00944  -0.0693   0.6918   0.0117
  -3.250   0.0405   0.01389   0.00741  -0.0685   0.6817   0.0117
  -3.000   0.0663   0.01290   0.00620  -0.0680   0.6717   0.0118
  -2.750   0.0923   0.01222   0.00535  -0.0675   0.6617   0.0120
  -2.500   0.1184   0.01165   0.00465  -0.0670   0.6513   0.0123
  -2.250   0.1446   0.01117   0.00407  -0.0665   0.6412   0.0127
  -2.000   0.1707   0.01077   0.00356  -0.0661   0.6313   0.0134
  -1.750   0.1968   0.01044   0.00312  -0.0656   0.6211   0.0141
  -1.500   0.2232   0.01015   0.00276  -0.0652   0.6108   0.0149
  -1.250   0.2496   0.00992   0.00248  -0.0649   0.6009   0.0162
  -1.000   0.2762   0.00981   0.00231  -0.0646   0.5909   0.0182
  -0.750   0.3030   0.00965   0.00212  -0.0643   0.5807   0.0210
  -0.500   0.3298   0.00956   0.00198  -0.0640   0.5708   0.0242
  -0.250   0.3564   0.00946   0.00184  -0.0637   0.5609   0.0288
   0.000   0.3834   0.00941   0.00175  -0.0635   0.5505   0.0344
   0.250   0.4102   0.00934   0.00166  -0.0632   0.5407   0.0444
   0.500   0.4369   0.00927   0.00160  -0.0629   0.5308   0.0645
   0.750   0.4550   0.00788   0.00165  -0.0618   0.5214   0.5889
   1.250   0.5522   0.00712   0.00171  -0.0705   0.4973   1.0000
   1.500   0.5770   0.00724   0.00173  -0.0699   0.4873   1.0000
   1.750   0.6021   0.00735   0.00176  -0.0693   0.4766   1.0000
   2.000   0.6272   0.00746   0.00180  -0.0687   0.4663   1.0000
   2.250   0.6522   0.00758   0.00185  -0.0681   0.4559   1.0000
   2.500   0.6771   0.00772   0.00191  -0.0675   0.4452   1.0000
   2.750   0.7023   0.00785   0.00198  -0.0670   0.4345   1.0000
   3.000   0.7273   0.00799   0.00207  -0.0664   0.4237   1.0000
   3.250   0.7523   0.00814   0.00216  -0.0659   0.4130   1.0000
   3.750   0.8023   0.00847   0.00239  -0.0648   0.3907   1.0000
   4.000   0.8274   0.00863   0.00251  -0.0643   0.3800   1.0000
   4.250   0.8523   0.00882   0.00265  -0.0638   0.3692   1.0000
   4.500   0.8771   0.00902   0.00280  -0.0633   0.3580   1.0000
   4.750   0.9021   0.00920   0.00296  -0.0628   0.3472   1.0000
   5.000   0.9270   0.00940   0.00313  -0.0623   0.3367   1.0000
   5.250   0.9517   0.00962   0.00332  -0.0618   0.3261   1.0000
   5.500   0.9762   0.00986   0.00353  -0.0613   0.3155   1.0000
   5.750   1.0010   0.01007   0.00373  -0.0608   0.3052   1.0000
   6.000   1.0256   0.01030   0.00395  -0.0603   0.2954   1.0000
   6.250   1.0497   0.01056   0.00418  -0.0598   0.2853   1.0000
   6.500   1.0740   0.01081   0.00444  -0.0593   0.2751   1.0000
   6.750   1.0981   0.01107   0.00470  -0.0587   0.2651   1.0000
   7.000   1.1216   0.01137   0.00498  -0.0581   0.2525   1.0000
   7.250   1.1441   0.01176   0.00529  -0.0574   0.2341   1.0000
   7.500   1.1666   0.01214   0.00563  -0.0567   0.2187   1.0000
   7.750   1.1893   0.01249   0.00597  -0.0560   0.2061   1.0000
   8.000   1.2114   0.01288   0.00633  -0.0552   0.1923   1.0000
   8.250   1.2320   0.01339   0.00676  -0.0543   0.1728   1.0000
   8.500   1.2525   0.01389   0.00721  -0.0533   0.1548   1.0000
   8.750   1.2712   0.01451   0.00773  -0.0521   0.1346   1.0000
   9.000   1.2886   0.01520   0.00832  -0.0508   0.1117   1.0000
   9.250   1.3035   0.01606   0.00903  -0.0491   0.0867   1.0000
   9.500   1.3178   0.01690   0.00978  -0.0473   0.0665   1.0000
   9.750   1.3305   0.01780   0.01059  -0.0453   0.0499   1.0000
  10.250   1.3572   0.01921   0.01200  -0.0414   0.0344   1.0000
  10.500   1.3673   0.01995   0.01275  -0.0389   0.0285   1.0000
  10.750   1.3761   0.02078   0.01359  -0.0364   0.0234   1.0000
  11.000   1.3844   0.02168   0.01452  -0.0340   0.0183   1.0000
  11.250   1.3898   0.02280   0.01565  -0.0315   0.0131   1.0000
  11.500   1.3956   0.02397   0.01686  -0.0293   0.0101   1.0000
  11.750   1.4021   0.02518   0.01814  -0.0274   0.0087   1.0000
  12.000   1.4072   0.02657   0.01960  -0.0256   0.0076   1.0000
  12.250   1.4117   0.02810   0.02121  -0.0241   0.0069   1.0000
  12.500   1.4167   0.02969   0.02289  -0.0227   0.0066   1.0000
  12.750   1.4209   0.03144   0.02475  -0.0216   0.0063   1.0000
  13.000   1.4241   0.03339   0.02683  -0.0207   0.0060   1.0000
  13.250   1.4265   0.03551   0.02905  -0.0199   0.0058   1.0000
  13.500   1.4282   0.03780   0.03146  -0.0194   0.0056   1.0000
  13.750   1.4278   0.04041   0.03417  -0.0190   0.0054   1.0000
  14.000   1.4259   0.04330   0.03718  -0.0189   0.0052   1.0000
  14.250   1.4242   0.04627   0.04026  -0.0189   0.0052   1.0000
  14.500   1.4190   0.04976   0.04386  -0.0192   0.0050   1.0000
  14.750   1.4116   0.05366   0.04789  -0.0198   0.0049   1.0000
  15.000   1.4047   0.05767   0.05202  -0.0205   0.0048   1.0000
  15.250   1.3953   0.06217   0.05665  -0.0216   0.0048   1.0000
  15.500   1.3861   0.06682   0.06144  -0.0229   0.0047   1.0000
  15.750   1.3757   0.07181   0.06655  -0.0245   0.0047   1.0000
  16.000   1.3667   0.07676   0.07162  -0.0261   0.0046   1.0000
  16.250   1.3581   0.08175   0.07674  -0.0279   0.0045   1.0000
  16.500   1.3482   0.08706   0.08217  -0.0299   0.0046   1.0000
  16.750   1.3392   0.09239   0.08763  -0.0320   0.0045   1.0000
  17.000   1.3300   0.09783   0.09319  -0.0342   0.0045   1.0000
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