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S1048 14% (Danny Howell) (s1048-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S1048 14% (Danny Howell) (s1048-il)
Reynolds number: 100,000
Max Cl/Cd: 40.33 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1048-il-100000.txt
Download as CSV file: xf-s1048-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1048 14% (Danny Howell)                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.8750   0.09024   0.08483  -0.0253   1.0000   0.0457
 -14.000  -0.9020   0.08353   0.07786  -0.0301   1.0000   0.0450
 -13.750  -0.9245   0.07738   0.07153  -0.0333   1.0000   0.0449
 -13.500  -0.9441   0.07188   0.06583  -0.0356   1.0000   0.0447
 -13.250  -0.9614   0.06714   0.06089  -0.0372   1.0000   0.0446
 -13.000  -0.9809   0.06290   0.05639  -0.0382   1.0000   0.0448
 -12.750  -0.9967   0.05933   0.05256  -0.0382   1.0000   0.0449
 -12.500  -1.0105   0.05612   0.04912  -0.0374   1.0000   0.0451
 -12.250  -1.0069   0.05167   0.04459  -0.0371   1.0000   0.0468
 -12.000  -1.0045   0.04899   0.04180  -0.0361   1.0000   0.0481
 -11.750  -1.0035   0.04654   0.03916  -0.0347   1.0000   0.0496
 -11.500  -0.9988   0.04402   0.03643  -0.0332   1.0000   0.0512
 -11.250  -0.9918   0.04156   0.03372  -0.0316   1.0000   0.0531
 -11.000  -0.9856   0.03954   0.03139  -0.0295   1.0000   0.0552
 -10.750  -0.9663   0.03694   0.02894  -0.0292   1.0000   0.0602
 -10.500  -0.9564   0.03522   0.02707  -0.0274   1.0000   0.0648
 -10.250  -0.9417   0.03304   0.02495  -0.0261   1.0000   0.0710
 -10.000  -0.9346   0.03159   0.02334  -0.0238   1.0000   0.0788
  -9.750  -0.9266   0.02973   0.02164  -0.0217   1.0000   0.0897
  -9.500  -0.9210   0.02798   0.01992  -0.0192   1.0000   0.1052
  -9.250  -0.9177   0.02622   0.01841  -0.0165   1.0000   0.1253
  -9.000  -0.9133   0.02469   0.01706  -0.0137   1.0000   0.1535
  -8.750  -0.9060   0.02349   0.01598  -0.0112   1.0000   0.1845
  -8.500  -0.8956   0.02261   0.01518  -0.0089   1.0000   0.2145
  -8.250  -0.8830   0.02198   0.01461  -0.0068   1.0000   0.2422
  -8.000  -0.8688   0.02154   0.01422  -0.0047   1.0000   0.2685
  -7.750  -0.8533   0.02117   0.01382  -0.0027   1.0000   0.2931
  -7.500  -0.8364   0.02086   0.01350  -0.0009   1.0000   0.3159
  -7.250  -0.8186   0.02052   0.01315   0.0009   1.0000   0.3364
  -7.000  -0.7996   0.02024   0.01292   0.0025   1.0000   0.3555
  -6.750  -0.7810   0.01996   0.01261   0.0042   1.0000   0.3744
  -6.500  -0.7630   0.01967   0.01223   0.0060   1.0000   0.3930
  -6.250  -0.7438   0.01940   0.01198   0.0076   1.0000   0.4098
  -6.000  -0.7247   0.01914   0.01175   0.0092   1.0000   0.4257
  -5.750  -0.7065   0.01889   0.01151   0.0109   1.0000   0.4411
  -5.500  -0.6892   0.01866   0.01128   0.0127   1.0000   0.4561
  -5.250  -0.6729   0.01845   0.01105   0.0147   1.0000   0.4707
  -5.000  -0.6575   0.01826   0.01084   0.0166   1.0000   0.4850
  -4.750  -0.6427   0.01810   0.01066   0.0185   1.0000   0.4992
  -4.500  -0.6273   0.01800   0.01059   0.0204   1.0000   0.5123
  -4.250  -0.6119   0.01792   0.01053   0.0221   1.0000   0.5253
  -4.000  -0.5963   0.01788   0.01051   0.0237   1.0000   0.5383
  -3.750  -0.5544   0.01794   0.01053   0.0203   0.9906   0.5561
  -3.500  -0.5065   0.01796   0.01049   0.0160   0.9783   0.5747
  -3.250  -0.4588   0.01798   0.01054   0.0120   0.9664   0.5915
  -3.000  -0.4095   0.01797   0.01053   0.0079   0.9554   0.6082
  -2.750  -0.3646   0.01791   0.01048   0.0047   0.9428   0.6243
  -2.500  -0.3190   0.01783   0.01042   0.0014   0.9309   0.6404
  -2.250  -0.2744   0.01772   0.01032  -0.0015   0.9193   0.6563
  -2.000  -0.2303   0.01758   0.01020  -0.0041   0.9080   0.6719
  -1.750  -0.1916   0.01746   0.01008  -0.0056   0.8950   0.6870
  -1.500  -0.1585   0.01735   0.00998  -0.0060   0.8803   0.7016
  -1.250  -0.1282   0.01727   0.00990  -0.0058   0.8653   0.7161
  -1.000  -0.1003   0.01720   0.00982  -0.0051   0.8501   0.7306
  -0.750  -0.0740   0.01715   0.00977  -0.0040   0.8348   0.7451
  -0.500  -0.0489   0.01711   0.00973  -0.0028   0.8196   0.7597
  -0.250  -0.0243   0.01709   0.00971  -0.0014   0.8044   0.7745
   0.000   0.0000   0.01708   0.00970   0.0000   0.7894   0.7894
   0.250   0.0243   0.01709   0.00971   0.0014   0.7745   0.8044
   0.500   0.0489   0.01711   0.00973   0.0028   0.7597   0.8196
   0.750   0.0740   0.01715   0.00977   0.0040   0.7451   0.8348
   1.000   0.1003   0.01720   0.00982   0.0051   0.7306   0.8501
   1.250   0.1282   0.01727   0.00990   0.0058   0.7161   0.8653
   1.500   0.1585   0.01735   0.00998   0.0060   0.7016   0.8803
   1.750   0.1916   0.01746   0.01008   0.0056   0.6870   0.8950
   2.000   0.2303   0.01759   0.01020   0.0041   0.6720   0.9080
   2.250   0.2744   0.01772   0.01032   0.0015   0.6564   0.9193
   2.500   0.3191   0.01783   0.01042  -0.0014   0.6404   0.9309
   2.750   0.3646   0.01791   0.01049  -0.0047   0.6244   0.9428
   3.000   0.4095   0.01797   0.01053  -0.0079   0.6082   0.9554
   3.250   0.4587   0.01798   0.01053  -0.0120   0.5914   0.9664
   3.500   0.5065   0.01796   0.01048  -0.0160   0.5747   0.9783
   3.750   0.5544   0.01793   0.01053  -0.0203   0.5561   0.9906
   4.000   0.5963   0.01788   0.01051  -0.0237   0.5384   1.0000
   4.250   0.6119   0.01792   0.01053  -0.0221   0.5253   1.0000
   4.500   0.6272   0.01799   0.01059  -0.0204   0.5123   1.0000
   4.750   0.6427   0.01810   0.01066  -0.0185   0.4992   1.0000
   5.000   0.6575   0.01826   0.01084  -0.0166   0.4850   1.0000
   5.250   0.6729   0.01845   0.01104  -0.0147   0.4707   1.0000
   5.500   0.6892   0.01866   0.01128  -0.0127   0.4561   1.0000
   5.750   0.7065   0.01889   0.01151  -0.0109   0.4411   1.0000
   6.000   0.7247   0.01914   0.01175  -0.0092   0.4257   1.0000
   6.250   0.7438   0.01939   0.01198  -0.0076   0.4098   1.0000
   6.500   0.7630   0.01967   0.01223  -0.0060   0.3930   1.0000
   6.750   0.7810   0.01996   0.01261  -0.0042   0.3744   1.0000
   7.000   0.7996   0.02024   0.01292  -0.0025   0.3555   1.0000
   7.250   0.8186   0.02052   0.01315  -0.0009   0.3364   1.0000
   7.500   0.8365   0.02086   0.01351   0.0009   0.3159   1.0000
   7.750   0.8534   0.02117   0.01383   0.0027   0.2932   1.0000
   8.000   0.8688   0.02154   0.01422   0.0047   0.2684   1.0000
   8.250   0.8830   0.02198   0.01461   0.0068   0.2422   1.0000
   8.500   0.8956   0.02262   0.01518   0.0089   0.2145   1.0000
   8.750   0.9060   0.02348   0.01598   0.0112   0.1844   1.0000
   9.000   0.9134   0.02469   0.01706   0.0137   0.1535   1.0000
   9.250   0.9178   0.02622   0.01841   0.0165   0.1254   1.0000
   9.500   0.9209   0.02799   0.01992   0.0192   0.1050   1.0000
   9.750   0.9268   0.02973   0.02161   0.0217   0.0898   1.0000
  10.000   0.9352   0.03160   0.02334   0.0237   0.0789   1.0000
  10.250   0.9422   0.03305   0.02496   0.0261   0.0711   1.0000
  10.500   0.9566   0.03522   0.02707   0.0274   0.0648   1.0000
  10.750   0.9658   0.03692   0.02892   0.0293   0.0601   1.0000
  11.000   0.9855   0.03954   0.03139   0.0295   0.0552   1.0000
  11.250   0.9916   0.04158   0.03374   0.0316   0.0530   1.0000
  11.500   0.9991   0.04404   0.03646   0.0332   0.0512   1.0000
  11.750   1.0038   0.04654   0.03916   0.0347   0.0496   1.0000
  12.000   1.0049   0.04913   0.04194   0.0361   0.0483   1.0000
  12.250   1.0063   0.05171   0.04466   0.0371   0.0470   1.0000
  12.500   1.0114   0.05573   0.04872   0.0374   0.0453   1.0000
  12.750   0.9984   0.05941   0.05264   0.0381   0.0450   1.0000
  13.000   0.9813   0.06294   0.05643   0.0381   0.0448   1.0000
  13.250   0.9640   0.06715   0.06088   0.0373   0.0447   1.0000
  13.500   0.9446   0.07201   0.06597   0.0356   0.0447   1.0000
  13.750   0.9253   0.07738   0.07153   0.0332   0.0449   1.0000
  14.000   0.9054   0.08332   0.07763   0.0303   0.0450   1.0000
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