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S7012 8.75% (s7012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S7012 8.75% (s7012-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.48 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s7012-il-1000000.txt
Download as CSV file: xf-s7012-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S7012 8.75%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4745   0.08278   0.08120  -0.0206   1.0000   0.0100
  -8.500  -0.4748   0.07843   0.07687  -0.0229   1.0000   0.0100
  -8.250  -0.4772   0.07373   0.07220  -0.0256   1.0000   0.0100
  -8.000  -0.4836   0.06879   0.06730  -0.0287   1.0000   0.0100
  -7.750  -0.4895   0.06155   0.06006  -0.0371   1.0000   0.0100
  -7.500  -0.4906   0.05427   0.05267  -0.0419   1.0000   0.0100
  -7.250  -0.4907   0.04831   0.04656  -0.0440   1.0000   0.0101
  -7.000  -0.4893   0.04319   0.04123  -0.0447   1.0000   0.0101
  -6.750  -0.4850   0.03905   0.03685  -0.0443   1.0000   0.0101
  -6.500  -0.4893   0.02974   0.02703  -0.0457   0.9992   0.0109
  -6.250  -0.4582   0.02761   0.02476  -0.0484   0.9971   0.0113
  -6.000  -0.4259   0.02510   0.02202  -0.0510   0.9949   0.0119
  -5.750  -0.3946   0.02267   0.01933  -0.0527   0.9919   0.0127
  -5.500  -0.3615   0.02083   0.01724  -0.0542   0.9884   0.0139
  -5.250  -0.3245   0.02150   0.01774  -0.0555   0.9854   0.0150
  -5.000  -0.2960   0.01226   0.00759  -0.0561   0.9812   0.0085
  -4.750  -0.2638   0.01088   0.00605  -0.0570   0.9759   0.0084
  -4.500  -0.2287   0.01003   0.00510  -0.0585   0.9714   0.0091
  -4.250  -0.1964   0.00940   0.00440  -0.0594   0.9628   0.0096
  -4.000  -0.1629   0.00892   0.00385  -0.0606   0.9531   0.0099
  -3.750  -0.1320   0.00850   0.00336  -0.0611   0.9389   0.0101
  -3.500  -0.1038   0.00788   0.00258  -0.0611   0.9199   0.0108
  -3.250  -0.0765   0.00758   0.00217  -0.0608   0.8989   0.0118
  -3.000  -0.0497   0.00739   0.00186  -0.0603   0.8757   0.0126
  -2.750  -0.0229   0.00725   0.00160  -0.0599   0.8526   0.0147
  -2.250   0.0297   0.00640   0.00115  -0.0595   0.8068   0.1732
  -2.000   0.0562   0.00609   0.00104  -0.0593   0.7846   0.2601
  -1.750   0.0829   0.00575   0.00095  -0.0593   0.7627   0.3645
  -1.500   0.1092   0.00530   0.00087  -0.0593   0.7414   0.5097
  -1.250   0.1357   0.00503   0.00089  -0.0591   0.7201   0.6334
  -1.000   0.1629   0.00503   0.00088  -0.0588   0.6992   0.6677
  -0.750   0.1902   0.00505   0.00088  -0.0586   0.6782   0.6961
  -0.500   0.2177   0.00510   0.00087  -0.0584   0.6584   0.7174
  -0.250   0.2452   0.00514   0.00088  -0.0582   0.6391   0.7348
   0.000   0.2727   0.00520   0.00089  -0.0581   0.6207   0.7510
   0.500   0.3277   0.00530   0.00093  -0.0578   0.5863   0.7814
   0.750   0.3551   0.00536   0.00096  -0.0576   0.5692   0.7965
   1.000   0.3825   0.00541   0.00100  -0.0574   0.5523   0.8120
   1.250   0.4097   0.00547   0.00104  -0.0572   0.5368   0.8278
   1.500   0.4369   0.00552   0.00109  -0.0570   0.5224   0.8447
   1.750   0.4635   0.00556   0.00115  -0.0566   0.5084   0.8639
   2.000   0.4896   0.00560   0.00120  -0.0561   0.4949   0.8865
   2.250   0.5143   0.00562   0.00127  -0.0553   0.4812   0.9133
   2.500   0.5375   0.00562   0.00130  -0.0540   0.4668   0.9549
   2.750   0.5707   0.00569   0.00134  -0.0552   0.4515   1.0000
   3.000   0.5988   0.00582   0.00142  -0.0553   0.4375   1.0000
   3.250   0.6268   0.00595   0.00150  -0.0553   0.4223   1.0000
   3.750   0.6822   0.00627   0.00172  -0.0554   0.3851   1.0000
   4.000   0.7095   0.00647   0.00184  -0.0553   0.3639   1.0000
   4.250   0.7369   0.00667   0.00199  -0.0553   0.3422   1.0000
   4.750   0.7888   0.00744   0.00239  -0.0549   0.2574   1.0000
   5.000   0.8145   0.00787   0.00263  -0.0547   0.2174   1.0000
   5.250   0.8403   0.00828   0.00291  -0.0545   0.1845   1.0000
   5.500   0.8661   0.00870   0.00319  -0.0543   0.1536   1.0000
   5.750   0.8913   0.00918   0.00352  -0.0541   0.1201   1.0000
   6.000   0.9160   0.00975   0.00390  -0.0537   0.0843   1.0000
   6.250   0.9397   0.01046   0.00439  -0.0533   0.0467   1.0000
   6.500   0.9621   0.01139   0.00509  -0.0526   0.0119   1.0000
   6.750   0.9876   0.01185   0.00556  -0.0522   0.0088   1.0000
   7.000   1.0127   0.01233   0.00608  -0.0518   0.0076   1.0000
   7.250   1.0368   0.01298   0.00684  -0.0512   0.0068   1.0000
   7.500   1.0616   0.01347   0.00740  -0.0508   0.0065   1.0000
   7.750   1.0856   0.01406   0.00806  -0.0503   0.0062   1.0000
   8.000   1.1089   0.01474   0.00884  -0.0496   0.0058   1.0000
   8.250   1.1314   0.01551   0.00970  -0.0489   0.0056   1.0000
   8.500   1.1529   0.01638   0.01066  -0.0480   0.0054   1.0000
   8.750   1.1734   0.01734   0.01173  -0.0470   0.0053   1.0000
   9.000   1.1926   0.01843   0.01293  -0.0458   0.0052   1.0000
   9.250   1.2117   0.01948   0.01408  -0.0447   0.0051   1.0000
   9.500   1.2302   0.02054   0.01523  -0.0436   0.0049   1.0000
   9.750   1.2471   0.02176   0.01657  -0.0423   0.0048   1.0000
  10.000   1.2619   0.02322   0.01815  -0.0408   0.0047   1.0000
  10.250   1.2756   0.02477   0.01983  -0.0392   0.0047   1.0000
  10.500   1.2879   0.02642   0.02162  -0.0374   0.0046   1.0000
  10.750   1.2982   0.02820   0.02356  -0.0355   0.0046   1.0000
  11.000   1.3058   0.03011   0.02563  -0.0334   0.0046   1.0000
  11.250   1.3081   0.03199   0.02767  -0.0305   0.0046   1.0000
  11.500   1.3047   0.03415   0.02999  -0.0273   0.0045   1.0000
  11.750   1.3023   0.03620   0.03220  -0.0248   0.0046   1.0000
  12.000   1.2953   0.03891   0.03509  -0.0226   0.0045   1.0000
  12.250   1.2866   0.04202   0.03838  -0.0213   0.0045   1.0000
  12.500   1.2776   0.04546   0.04199  -0.0207   0.0045   1.0000
  12.750   1.2631   0.04998   0.04671  -0.0211   0.0045   1.0000
  13.000   1.2536   0.05417   0.05106  -0.0223   0.0045   1.0000
  13.250   1.2457   0.05857   0.05563  -0.0240   0.0046   1.0000
  13.500   1.2294   0.06458   0.06179  -0.0269   0.0045   1.0000
  13.750   1.2178   0.07036   0.06775  -0.0301   0.0046   1.0000
  14.000   1.1967   0.07805   0.07558  -0.0345   0.0045   1.0000
  14.250   1.1837   0.08482   0.08249  -0.0387   0.0045   1.0000
  14.500   1.1672   0.09276   0.09058  -0.0437   0.0046   1.0000
  14.750   1.1498   0.10153   0.09949  -0.0493   0.0046   1.0000
  15.000   1.1299   0.11156   0.10968  -0.0557   0.0047   1.0000
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