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S2046 (s2046-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S2046 (s2046-il)
Reynolds number: 100,000
Max Cl/Cd: 58.02 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2046-il-100000.txt
Download as CSV file: xf-s2046-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2046                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4105   0.09781   0.09269  -0.0266   1.0000   0.1107
  -8.500  -0.4286   0.09555   0.09057  -0.0310   1.0000   0.1147
  -8.250  -0.4583   0.09334   0.08855  -0.0363   1.0000   0.1155
  -8.000  -0.4172   0.08812   0.08323  -0.0299   1.0000   0.1190
  -7.750  -0.4124   0.08537   0.08052  -0.0291   1.0000   0.1223
  -7.500  -0.4212   0.08286   0.07811  -0.0293   1.0000   0.1264
  -7.250  -0.4593   0.07776   0.07317  -0.0428   1.0000   0.1305
  -7.000  -0.4406   0.07564   0.07112  -0.0343   1.0000   0.1325
  -6.750  -0.4338   0.07325   0.06877  -0.0318   1.0000   0.1356
  -6.500  -0.4545   0.06731   0.06275  -0.0442   1.0000   0.1454
  -6.250  -0.4446   0.06475   0.06031  -0.0395   1.0000   0.1472
  -6.000  -0.4389   0.04778   0.04222  -0.0558   1.0000   0.0863
  -5.750  -0.4229   0.03983   0.03378  -0.0580   1.0000   0.0711
  -5.500  -0.4036   0.03537   0.02893  -0.0591   1.0000   0.0682
  -5.250  -0.3798   0.03105   0.02399  -0.0602   1.0000   0.0662
  -5.000  -0.3554   0.02824   0.02069  -0.0606   1.0000   0.0673
  -4.750  -0.3303   0.02624   0.01819  -0.0606   1.0000   0.0714
  -4.500  -0.3039   0.02405   0.01549  -0.0606   1.0000   0.0744
  -4.250  -0.2795   0.02235   0.01375  -0.0604   1.0000   0.0795
  -4.000  -0.2531   0.02080   0.01194  -0.0600   1.0000   0.0887
  -3.750  -0.2284   0.01975   0.01096  -0.0598   1.0000   0.1069
  -3.500  -0.2036   0.01893   0.01008  -0.0597   1.0000   0.1321
  -3.250  -0.1797   0.01839   0.00956  -0.0595   1.0000   0.1584
  -3.000  -0.1557   0.01759   0.00894  -0.0592   1.0000   0.1805
  -2.750  -0.1316   0.01694   0.00842  -0.0589   1.0000   0.2083
  -2.500  -0.1069   0.01623   0.00799  -0.0588   1.0000   0.2515
  -2.250  -0.0812   0.01504   0.00786  -0.0591   1.0000   0.4266
  -2.000  -0.0631   0.01498   0.00834  -0.0570   1.0000   0.5935
  -1.750  -0.0462   0.01519   0.00866  -0.0547   1.0000   0.6594
  -1.500  -0.0296   0.01542   0.00894  -0.0525   1.0000   0.7072
  -1.250  -0.0139   0.01562   0.00916  -0.0502   1.0000   0.7461
  -1.000   0.0158   0.01593   0.00949  -0.0504   0.9941   0.7895
  -0.750   0.0518   0.01613   0.00971  -0.0517   0.9842   0.8336
  -0.500   0.0846   0.01611   0.00975  -0.0523   0.9735   0.8840
  -0.250   0.1343   0.01594   0.00962  -0.0567   0.9623   1.0000
   0.000   0.1871   0.01622   0.00973  -0.0625   0.9527   1.0000
   0.250   0.2385   0.01642   0.00979  -0.0676   0.9425   1.0000
   0.500   0.2834   0.01656   0.00982  -0.0713   0.9307   1.0000
   0.750   0.3288   0.01665   0.00984  -0.0749   0.9193   1.0000
   1.000   0.3768   0.01665   0.00979  -0.0787   0.9088   1.0000
   1.250   0.4292   0.01650   0.00963  -0.0830   0.8994   1.0000
   1.500   0.4710   0.01639   0.00951  -0.0852   0.8868   1.0000
   1.750   0.5114   0.01622   0.00936  -0.0870   0.8738   1.0000
   2.000   0.5502   0.01599   0.00915  -0.0883   0.8601   1.0000
   2.250   0.5873   0.01571   0.00890  -0.0890   0.8455   1.0000
   2.500   0.6224   0.01540   0.00863  -0.0892   0.8298   1.0000
   2.750   0.6559   0.01508   0.00834  -0.0890   0.8129   1.0000
   3.000   0.6848   0.01488   0.00816  -0.0881   0.7920   1.0000
   3.250   0.7143   0.01464   0.00794  -0.0871   0.7697   1.0000
   3.500   0.7415   0.01449   0.00778  -0.0858   0.7432   1.0000
   3.750   0.7684   0.01437   0.00763  -0.0845   0.7132   1.0000
   4.000   0.7947   0.01431   0.00746  -0.0830   0.6793   1.0000
   4.250   0.8190   0.01438   0.00746  -0.0814   0.6379   1.0000
   4.500   0.8429   0.01459   0.00750  -0.0799   0.5940   1.0000
   4.750   0.8662   0.01493   0.00764  -0.0784   0.5494   1.0000
   5.000   0.8891   0.01540   0.00791  -0.0771   0.5060   1.0000
   5.250   0.9115   0.01595   0.00828  -0.0759   0.4639   1.0000
   5.500   0.9335   0.01657   0.00876  -0.0746   0.4235   1.0000
   5.750   0.9549   0.01724   0.00925  -0.0734   0.3830   1.0000
   6.000   0.9754   0.01797   0.00982  -0.0721   0.3395   1.0000
   6.250   0.9942   0.01882   0.01048  -0.0706   0.2874   1.0000
   6.500   1.0110   0.02002   0.01136  -0.0690   0.2295   1.0000
   6.750   1.0280   0.02146   0.01243  -0.0674   0.1849   1.0000
   7.000   1.0471   0.02286   0.01360  -0.0661   0.1573   1.0000
   7.250   1.0678   0.02443   0.01495  -0.0651   0.1405   1.0000
   7.500   1.0902   0.02594   0.01637  -0.0643   0.1273   1.0000
   7.750   1.1130   0.02724   0.01779  -0.0634   0.1164   1.0000
   8.000   1.1377   0.02907   0.01968  -0.0629   0.1089   1.0000
   8.250   1.1621   0.03076   0.02134  -0.0624   0.1020   1.0000
   8.500   1.1852   0.03273   0.02353  -0.0616   0.0958   1.0000
   8.750   1.2081   0.03464   0.02563  -0.0609   0.0909   1.0000
   9.000   1.2321   0.03768   0.02868  -0.0607   0.0866   1.0000
   9.250   1.2477   0.03961   0.03117  -0.0589   0.0825   1.0000
   9.500   1.2651   0.04205   0.03393  -0.0576   0.0789   1.0000
   9.750   1.2829   0.04479   0.03679  -0.0567   0.0757   1.0000
  10.000   1.2914   0.04874   0.04113  -0.0550   0.0730   1.0000
  10.250   1.2927   0.05191   0.04493  -0.0523   0.0708   1.0000
  10.500   1.2905   0.05597   0.04949  -0.0497   0.0697   1.0000
  10.750   1.2830   0.06011   0.05408  -0.0471   0.0687   1.0000
  11.000   1.2701   0.06424   0.05858  -0.0444   0.0679   1.0000
  11.250   1.2496   0.06825   0.06289  -0.0415   0.0677   1.0000
  11.500   1.2220   0.07286   0.06776  -0.0393   0.0683   1.0000
  11.750   1.1912   0.07847   0.07360  -0.0391   0.0693   1.0000
  12.000   1.1607   0.08505   0.08037  -0.0409   0.0706   1.0000
  12.250   1.1319   0.09264   0.08808  -0.0444   0.0718   1.0000
  12.500   1.1068   0.10106   0.09659  -0.0490   0.0729   1.0000
  12.750   1.0890   0.10967   0.10524  -0.0532   0.0737   1.0000
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