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AQUILA 9.3% smoothed (aquilasm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: AQUILA 9.3% smoothed (aquilasm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 127.11 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-aquilasm-il-1000000.txt
Download as CSV file: xf-aquilasm-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3177   0.08673   0.08521  -0.0309   1.0000   0.0107
  -8.000  -0.3172   0.08369   0.08220  -0.0318   1.0000   0.0107
  -7.750  -0.3192   0.08039   0.07894  -0.0332   0.9918   0.0107
  -7.500  -0.2933   0.07461   0.07313  -0.0434   0.9741   0.0107
  -7.250  -0.2668   0.06811   0.06659  -0.0531   0.9609   0.0111
  -7.000  -0.2323   0.06306   0.06146  -0.0629   0.9383   0.0112
  -6.750  -0.2147   0.05957   0.05782  -0.0670   0.9038   0.0115
  -6.500  -0.2045   0.05643   0.05453  -0.0689   0.8765   0.0116
  -6.250  -0.1933   0.05322   0.05119  -0.0704   0.8549   0.0118
  -6.000  -0.1801   0.05000   0.04783  -0.0719   0.8365   0.0121
  -5.750  -0.1647   0.04679   0.04448  -0.0731   0.8202   0.0127
  -5.500  -0.1471   0.04319   0.04071  -0.0743   0.8055   0.0134
  -5.250  -0.1235   0.03906   0.03632  -0.0749   0.7921   0.0141
  -4.750  -0.0834   0.03241   0.02922  -0.0746   0.7673   0.0142
  -4.500  -0.0699   0.02724   0.02373  -0.0743   0.7561   0.0147
  -4.250  -0.0484   0.02574   0.02209  -0.0740   0.7445   0.0150
  -4.000  -0.0258   0.02443   0.02062  -0.0737   0.7331   0.0156
  -3.750  -0.0019   0.02266   0.01865  -0.0731   0.7219   0.0170
  -3.500   0.0264   0.02135   0.01700  -0.0718   0.7112   0.0185
  -3.250   0.0385   0.00492   0.00035  -0.0668   0.6865   0.0194
  -2.750   0.0944   0.01152   0.00587  -0.0682   0.6822   0.0146
  -2.500   0.1206   0.01067   0.00484  -0.0676   0.6720   0.0145
  -2.000   0.1725   0.00935   0.00334  -0.0666   0.6512   0.0157
  -1.750   0.1991   0.00907   0.00300  -0.0663   0.6414   0.0165
  -1.500   0.2256   0.00883   0.00269  -0.0659   0.6311   0.0175
  -1.250   0.2524   0.00858   0.00237  -0.0656   0.6208   0.0182
  -1.000   0.2786   0.00823   0.00195  -0.0651   0.6110   0.0194
  -0.750   0.3054   0.00811   0.00180  -0.0648   0.6011   0.0217
  -0.500   0.3327   0.00801   0.00166  -0.0646   0.5911   0.0239
  -0.250   0.3595   0.00782   0.00143  -0.0643   0.5816   0.0285
   0.000   0.3866   0.00777   0.00132  -0.0641   0.5716   0.0335
   0.250   0.4138   0.00771   0.00124  -0.0639   0.5613   0.0420
   0.500   0.4406   0.00755   0.00117  -0.0636   0.5516   0.0834
   0.750   0.4573   0.00610   0.00123  -0.0621   0.5428   0.6603
   1.250   0.5630   0.00551   0.00130  -0.0729   0.5186   1.0000
   1.500   0.5880   0.00559   0.00132  -0.0723   0.5084   1.0000
   1.750   0.6130   0.00569   0.00134  -0.0716   0.4983   1.0000
   2.000   0.6381   0.00578   0.00137  -0.0711   0.4879   1.0000
   2.250   0.6634   0.00588   0.00141  -0.0705   0.4773   1.0000
   2.500   0.6885   0.00599   0.00147  -0.0699   0.4671   1.0000
   3.000   0.7390   0.00622   0.00159  -0.0689   0.4454   1.0000
   3.250   0.7643   0.00635   0.00166  -0.0684   0.4342   1.0000
   3.500   0.7895   0.00648   0.00175  -0.0678   0.4230   1.0000
   3.750   0.8146   0.00663   0.00184  -0.0673   0.4115   1.0000
   4.000   0.8398   0.00677   0.00194  -0.0668   0.4004   1.0000
   4.250   0.8651   0.00692   0.00204  -0.0663   0.3889   1.0000
   4.500   0.8902   0.00708   0.00217  -0.0658   0.3772   1.0000
   4.750   0.9152   0.00725   0.00230  -0.0653   0.3656   1.0000
   5.000   0.9401   0.00743   0.00243  -0.0648   0.3539   1.0000
   5.250   0.9651   0.00761   0.00258  -0.0643   0.3425   1.0000
   5.500   0.9902   0.00779   0.00274  -0.0639   0.3312   1.0000
   5.750   1.0152   0.00799   0.00290  -0.0634   0.3197   1.0000
   6.000   1.0400   0.00820   0.00307  -0.0629   0.3089   1.0000
   6.250   1.0645   0.00843   0.00327  -0.0624   0.2974   1.0000
   6.500   1.0889   0.00868   0.00347  -0.0619   0.2830   1.0000
   6.750   1.1130   0.00895   0.00369  -0.0614   0.2672   1.0000
   7.000   1.1371   0.00921   0.00391  -0.0609   0.2548   1.0000
   7.250   1.1617   0.00944   0.00414  -0.0604   0.2449   1.0000
   7.500   1.1855   0.00973   0.00439  -0.0599   0.2314   1.0000
   7.750   1.2088   0.01005   0.00466  -0.0592   0.2169   1.0000
   8.000   1.2313   0.01044   0.00497  -0.0585   0.1991   1.0000
   8.250   1.2538   0.01082   0.00530  -0.0578   0.1823   1.0000
   8.500   1.2759   0.01122   0.00564  -0.0570   0.1661   1.0000
   8.750   1.2964   0.01174   0.00606  -0.0561   0.1464   1.0000
   9.000   1.3154   0.01236   0.00655  -0.0549   0.1221   1.0000
   9.250   1.3331   0.01306   0.00712  -0.0535   0.0980   1.0000
   9.500   1.3491   0.01385   0.00777  -0.0519   0.0744   1.0000
   9.750   1.3650   0.01462   0.00843  -0.0503   0.0559   1.0000
  10.000   1.3809   0.01533   0.00908  -0.0487   0.0433   1.0000
  10.250   1.3969   0.01600   0.00971  -0.0471   0.0342   1.0000
  10.500   1.4107   0.01676   0.01043  -0.0452   0.0251   1.0000
  10.750   1.4206   0.01764   0.01125  -0.0426   0.0156   1.0000
  11.000   1.4265   0.01852   0.01212  -0.0393   0.0107   1.0000
  11.250   1.4346   0.01932   0.01297  -0.0365   0.0090   1.0000
  11.500   1.4445   0.02006   0.01377  -0.0342   0.0084   1.0000
  11.750   1.4510   0.02105   0.01482  -0.0317   0.0076   1.0000
  12.000   1.4558   0.02222   0.01607  -0.0292   0.0070   1.0000
  12.250   1.4621   0.02337   0.01732  -0.0271   0.0067   1.0000
  12.500   1.4699   0.02450   0.01853  -0.0254   0.0065   1.0000
  12.750   1.4752   0.02590   0.02001  -0.0238   0.0063   1.0000
  13.000   1.4792   0.02751   0.02171  -0.0223   0.0060   1.0000
  13.250   1.4839   0.02914   0.02343  -0.0211   0.0058   1.0000
  13.500   1.4858   0.03114   0.02553  -0.0200   0.0057   1.0000
  13.750   1.4843   0.03359   0.02807  -0.0191   0.0054   1.0000
  14.000   1.4829   0.03617   0.03075  -0.0185   0.0053   1.0000
  14.250   1.4798   0.03905   0.03374  -0.0181   0.0052   1.0000
  14.500   1.4743   0.04235   0.03715  -0.0180   0.0051   1.0000
  14.750   1.4654   0.04617   0.04111  -0.0181   0.0050   1.0000
  15.000   1.4483   0.05116   0.04625  -0.0187   0.0049   1.0000
  15.250   1.4418   0.05503   0.05023  -0.0194   0.0049   1.0000
  15.500   1.4266   0.06020   0.05554  -0.0205   0.0048   1.0000
  15.750   1.4176   0.06477   0.06022  -0.0216   0.0048   1.0000
  16.000   1.4113   0.06902   0.06458  -0.0228   0.0048   1.0000
  16.250   1.4012   0.07400   0.06966  -0.0244   0.0047   1.0000
  16.500   1.3915   0.07903   0.07480  -0.0261   0.0047   1.0000
  16.750   1.3834   0.08392   0.07980  -0.0278   0.0047   1.0000
  17.000   1.3760   0.08884   0.08482  -0.0296   0.0047   1.0000
  17.250   1.3669   0.09413   0.09022  -0.0317   0.0046   1.0000
  17.500   1.3570   0.09959   0.09578  -0.0339   0.0046   1.0000
  17.750   1.3479   0.10507   0.10136  -0.0362   0.0046   1.0000
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