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SD7043 (9.1%) (sd7043-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SD7043 (9.1%) (sd7043-il)
Reynolds number: 100,000
Max Cl/Cd: 60.67 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7043-il-100000.txt
Download as CSV file: xf-sd7043-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7043 (9.1%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3382   0.10477   0.09975  -0.0326   1.0000   0.0858
  -8.750  -0.3498   0.10345   0.09855  -0.0357   1.0000   0.0879
  -8.500  -0.3668   0.10246   0.09771  -0.0381   1.0000   0.0885
  -8.250  -0.3378   0.09616   0.09137  -0.0339   1.0000   0.0924
  -8.000  -0.3344   0.09371   0.08897  -0.0328   1.0000   0.0957
  -7.750  -0.3398   0.09170   0.08706  -0.0323   1.0000   0.0987
  -7.500  -0.3588   0.09070   0.08619  -0.0312   1.0000   0.1011
  -7.250  -0.3824   0.09009   0.08573  -0.0293   1.0000   0.1019
  -7.000  -0.4074   0.08879   0.08453  -0.0333   1.0000   0.1028
  -6.750  -0.4141   0.08510   0.08092  -0.0332   1.0000   0.1038
  -6.500  -0.4029   0.08255   0.07841  -0.0249   1.0000   0.1064
  -6.250  -0.4042   0.08043   0.07634  -0.0229   1.0000   0.1093
  -6.000  -0.4086   0.07798   0.07393  -0.0236   1.0000   0.1131
  -5.750  -0.4141   0.07301   0.06888  -0.0347   1.0000   0.1187
  -5.500  -0.4104   0.07089   0.06687  -0.0289   1.0000   0.1210
  -5.250  -0.4053   0.06861   0.06459  -0.0275   1.0000   0.1251
  -5.000  -0.3946   0.06367   0.05952  -0.0351   1.0000   0.1346
  -4.750  -0.3876   0.06160   0.05751  -0.0321   1.0000   0.1386
  -4.500  -0.3717   0.05752   0.05329  -0.0368   1.0000   0.1506
  -4.250  -0.3541   0.05423   0.04986  -0.0398   1.0000   0.1646
  -4.000  -0.3383   0.05165   0.04723  -0.0405   1.0000   0.1798
  -3.750  -0.2581   0.03594   0.02957  -0.0571   1.0000   0.0900
  -3.500  -0.2220   0.03146   0.02426  -0.0587   1.0000   0.0742
  -3.250  -0.1882   0.02835   0.02076  -0.0606   0.9985   0.0721
  -3.000  -0.1428   0.02668   0.01838  -0.0637   0.9937   0.0748
  -2.750  -0.1022   0.02431   0.01575  -0.0663   0.9886   0.0771
  -2.500  -0.0589   0.02324   0.01454  -0.0693   0.9836   0.0840
  -2.250  -0.0213   0.02217   0.01333  -0.0711   0.9767   0.0912
  -2.000   0.0223   0.02134   0.01257  -0.0741   0.9714   0.1064
  -1.750   0.0579   0.02045   0.01190  -0.0757   0.9634   0.1386
  -1.500   0.0984   0.01847   0.01169  -0.0787   0.9587   0.5009
  -1.250   0.1202   0.01791   0.01203  -0.0763   0.9499   0.7613
  -1.000   0.1663   0.01766   0.01186  -0.0789   0.9429   1.0000
  -0.750   0.2011   0.01790   0.01180  -0.0806   0.9321   1.0000
  -0.500   0.2408   0.01817   0.01182  -0.0831   0.9228   1.0000
  -0.250   0.2852   0.01838   0.01181  -0.0863   0.9145   1.0000
   0.000   0.3198   0.01858   0.01184  -0.0877   0.9034   1.0000
   0.250   0.3641   0.01868   0.01180  -0.0906   0.8952   1.0000
   0.500   0.4041   0.01872   0.01173  -0.0927   0.8851   1.0000
   0.750   0.4403   0.01879   0.01171  -0.0941   0.8740   1.0000
   1.000   0.4908   0.01854   0.01138  -0.0975   0.8677   1.0000
   1.250   0.5224   0.01851   0.01131  -0.0977   0.8550   1.0000
   1.500   0.5554   0.01841   0.01117  -0.0980   0.8430   1.0000
   1.750   0.5910   0.01818   0.01091  -0.0986   0.8322   1.0000
   2.000   0.6299   0.01773   0.01044  -0.0993   0.8228   1.0000
   2.250   0.6597   0.01751   0.01021  -0.0987   0.8092   1.0000
   2.500   0.6896   0.01724   0.00995  -0.0981   0.7953   1.0000
   2.750   0.7194   0.01694   0.00964  -0.0973   0.7810   1.0000
   3.000   0.7488   0.01662   0.00932  -0.0964   0.7659   1.0000
   3.250   0.7781   0.01630   0.00899  -0.0955   0.7499   1.0000
   3.500   0.8071   0.01599   0.00867  -0.0945   0.7329   1.0000
   3.750   0.8326   0.01589   0.00857  -0.0933   0.7116   1.0000
   4.000   0.8602   0.01570   0.00834  -0.0922   0.6902   1.0000
   4.250   0.8859   0.01564   0.00828  -0.0909   0.6654   1.0000
   4.500   0.9119   0.01563   0.00819  -0.0897   0.6389   1.0000
   4.750   0.9368   0.01572   0.00820  -0.0885   0.6092   1.0000
   5.000   0.9608   0.01592   0.00830  -0.0872   0.5767   1.0000
   5.250   0.9841   0.01622   0.00849  -0.0858   0.5420   1.0000
   5.500   1.0066   0.01663   0.00874  -0.0844   0.5056   1.0000
   5.750   1.0280   0.01714   0.00909  -0.0830   0.4673   1.0000
   6.000   1.0488   0.01776   0.00955  -0.0816   0.4296   1.0000
   6.250   1.0690   0.01847   0.01008  -0.0802   0.3925   1.0000
   6.500   1.0889   0.01929   0.01067  -0.0789   0.3588   1.0000
   6.750   1.1086   0.02016   0.01137  -0.0776   0.3268   1.0000
   7.000   1.1282   0.02108   0.01215  -0.0763   0.2979   1.0000
   7.250   1.1478   0.02203   0.01300  -0.0751   0.2716   1.0000
   7.500   1.1674   0.02303   0.01393  -0.0739   0.2477   1.0000
   7.750   1.1871   0.02409   0.01486  -0.0728   0.2272   1.0000
   8.000   1.2068   0.02521   0.01593  -0.0717   0.2084   1.0000
   8.250   1.2265   0.02635   0.01708  -0.0706   0.1913   1.0000
   8.500   1.2461   0.02755   0.01827  -0.0695   0.1760   1.0000
   8.750   1.2662   0.02884   0.01956  -0.0686   0.1626   1.0000
   9.000   1.2871   0.03027   0.02096  -0.0677   0.1509   1.0000
   9.250   1.3082   0.03167   0.02229  -0.0670   0.1401   1.0000
   9.500   1.3262   0.03310   0.02399  -0.0657   0.1307   1.0000
   9.750   1.3479   0.03492   0.02583  -0.0650   0.1229   1.0000
  10.000   1.3660   0.03637   0.02741  -0.0639   0.1154   1.0000
  10.250   1.3854   0.03851   0.02973  -0.0630   0.1093   1.0000
  10.500   1.4014   0.04034   0.03182  -0.0616   0.1038   1.0000
  10.750   1.4224   0.04274   0.03417  -0.0613   0.0985   1.0000
  11.000   1.4297   0.04491   0.03685  -0.0588   0.0945   1.0000
  11.250   1.4415   0.04717   0.03937  -0.0572   0.0908   1.0000
  11.500   1.4626   0.05026   0.04237  -0.0573   0.0866   1.0000
  11.750   1.4566   0.05286   0.04554  -0.0538   0.0846   1.0000
  12.000   1.4492   0.05587   0.04901  -0.0505   0.0826   1.0000
  12.250   1.4386   0.05902   0.05252  -0.0472   0.0812   1.0000
  12.500   1.4249   0.06230   0.05610  -0.0441   0.0801   1.0000
  12.750   1.4100   0.06579   0.05985  -0.0416   0.0791   1.0000
  13.000   1.3950   0.06953   0.06382  -0.0399   0.0781   1.0000
  13.250   1.4184   0.07266   0.06678  -0.0402   0.0744   1.0000
  13.500   1.3929   0.07739   0.07176  -0.0389   0.0742   1.0000
  13.750   1.3656   0.08268   0.07732  -0.0386   0.0742   1.0000
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