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S7012 8.75% (s7012-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S7012 8.75% (s7012-il)
Reynolds number: 500,000
Max Cl/Cd: 94.12 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s7012-il-500000.txt
Download as CSV file: xf-s7012-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4693   0.08323   0.08102  -0.0211   1.0000   0.0178
  -8.250  -0.4702   0.07923   0.07705  -0.0232   1.0000   0.0182
  -8.000  -0.4736   0.07510   0.07297  -0.0254   1.0000   0.0185
  -7.750  -0.4809   0.07091   0.06883  -0.0279   1.0000   0.0187
  -7.500  -0.4839   0.06452   0.06244  -0.0354   1.0000   0.0188
  -7.250  -0.4837   0.05862   0.05648  -0.0400   1.0000   0.0190
  -7.000  -0.4810   0.05302   0.05075  -0.0430   1.0000   0.0197
  -6.750  -0.4742   0.04781   0.04536  -0.0446   1.0000   0.0206
  -6.500  -0.4580   0.04507   0.04232  -0.0445   1.0000   0.0220
  -6.250  -0.4485   0.04196   0.03895  -0.0439   1.0000   0.0221
  -6.000  -0.4515   0.03370   0.03023  -0.0440   1.0000   0.0231
  -5.750  -0.4390   0.03082   0.02726  -0.0432   1.0000   0.0239
  -5.500  -0.4209   0.02887   0.02521  -0.0428   0.9996   0.0248
  -5.250  -0.3855   0.02632   0.02242  -0.0456   0.9967   0.0268
  -5.000  -0.3481   0.02401   0.01977  -0.0480   0.9939   0.0296
  -4.750  -0.3121   0.01624   0.01092  -0.0479   0.9907   0.0142
  -4.500  -0.2764   0.01418   0.00858  -0.0494   0.9871   0.0141
  -4.250  -0.2389   0.01285   0.00710  -0.0513   0.9840   0.0144
  -4.000  -0.2045   0.01195   0.00610  -0.0526   0.9786   0.0149
  -3.750  -0.1684   0.01066   0.00472  -0.0545   0.9738   0.0163
  -3.500  -0.1298   0.00989   0.00389  -0.0567   0.9700   0.0173
  -3.250  -0.0960   0.00936   0.00328  -0.0578   0.9610   0.0185
  -3.000  -0.0604   0.00893   0.00277  -0.0593   0.9523   0.0216
  -2.750  -0.0268   0.00789   0.00219  -0.0607   0.9410   0.1365
  -2.500   0.0036   0.00723   0.00195  -0.0616   0.9255   0.2610
  -2.250   0.0316   0.00655   0.00178  -0.0619   0.9066   0.4189
  -2.000   0.0579   0.00599   0.00169  -0.0616   0.8863   0.5710
  -1.750   0.0834   0.00580   0.00170  -0.0608   0.8642   0.6714
  -1.500   0.1096   0.00578   0.00165  -0.0601   0.8420   0.7076
  -1.250   0.1357   0.00579   0.00161  -0.0594   0.8191   0.7360
  -1.000   0.1619   0.00583   0.00158  -0.0587   0.7967   0.7598
  -0.750   0.1879   0.00587   0.00155  -0.0581   0.7743   0.7791
  -0.500   0.2140   0.00592   0.00153  -0.0574   0.7522   0.7975
   0.000   0.2659   0.00603   0.00151  -0.0562   0.7091   0.8325
   0.250   0.2914   0.00608   0.00151  -0.0554   0.6886   0.8499
   0.500   0.3167   0.00613   0.00152  -0.0547   0.6686   0.8682
   0.750   0.3415   0.00617   0.00153  -0.0538   0.6496   0.8878
   1.000   0.3650   0.00621   0.00154  -0.0526   0.6320   0.9103
   1.250   0.3884   0.00622   0.00154  -0.0513   0.6147   0.9391
   1.500   0.4205   0.00625   0.00153  -0.0521   0.5963   0.9738
   1.750   0.4543   0.00635   0.00154  -0.0534   0.5782   1.0000
   2.000   0.4823   0.00649   0.00159  -0.0536   0.5620   1.0000
   2.250   0.5101   0.00664   0.00165  -0.0536   0.5465   1.0000
   2.500   0.5380   0.00677   0.00174  -0.0537   0.5311   1.0000
   2.750   0.5657   0.00691   0.00183  -0.0537   0.5159   1.0000
   3.000   0.5933   0.00706   0.00192  -0.0537   0.4999   1.0000
   3.250   0.6209   0.00721   0.00203  -0.0537   0.4840   1.0000
   3.500   0.6484   0.00737   0.00217  -0.0536   0.4685   1.0000
   3.750   0.6758   0.00753   0.00230  -0.0536   0.4525   1.0000
   4.000   0.7030   0.00771   0.00244  -0.0535   0.4355   1.0000
   4.250   0.7301   0.00790   0.00259  -0.0534   0.4152   1.0000
   4.500   0.7571   0.00811   0.00277  -0.0533   0.3945   1.0000
   4.750   0.7839   0.00833   0.00295  -0.0531   0.3718   1.0000
   5.000   0.8104   0.00861   0.00316  -0.0530   0.3452   1.0000
   5.250   0.8356   0.00903   0.00340  -0.0527   0.3014   1.0000
   5.500   0.8601   0.00958   0.00373  -0.0523   0.2504   1.0000
   5.750   0.8848   0.01011   0.00408  -0.0520   0.2093   1.0000
   6.000   0.9094   0.01066   0.00447  -0.0517   0.1714   1.0000
   6.500   0.9570   0.01200   0.00545  -0.0509   0.0930   1.0000
   6.750   0.9789   0.01295   0.00613  -0.0502   0.0475   1.0000
   7.000   0.9986   0.01431   0.00728  -0.0491   0.0153   1.0000
   7.250   1.0227   0.01492   0.00797  -0.0485   0.0130   1.0000
   7.500   1.0454   0.01571   0.00884  -0.0478   0.0115   1.0000
   7.750   1.0643   0.01706   0.01034  -0.0465   0.0104   1.0000
   8.000   1.0860   0.01791   0.01129  -0.0457   0.0101   1.0000
   8.250   1.1063   0.01893   0.01245  -0.0446   0.0097   1.0000
   8.500   1.1251   0.02012   0.01377  -0.0434   0.0093   1.0000
   8.750   1.1428   0.02145   0.01523  -0.0420   0.0090   1.0000
   9.000   1.1595   0.02295   0.01686  -0.0406   0.0089   1.0000
   9.250   1.1754   0.02467   0.01874  -0.0390   0.0088   1.0000
   9.500   1.1904   0.02666   0.02092  -0.0374   0.0089   1.0000
   9.750   1.2043   0.02899   0.02346  -0.0358   0.0090   1.0000
  10.000   1.2170   0.03141   0.02612  -0.0341   0.0090   1.0000
  10.250   1.2280   0.03371   0.02867  -0.0324   0.0089   1.0000
  10.500   1.2362   0.03605   0.03124  -0.0305   0.0088   1.0000
  10.750   1.2397   0.03864   0.03408  -0.0283   0.0087   1.0000
  11.000   1.2343   0.04147   0.03717  -0.0252   0.0088   1.0000
  11.250   1.2222   0.04479   0.04076  -0.0221   0.0089   1.0000
  11.500   1.2093   0.04817   0.04438  -0.0201   0.0090   1.0000
  11.750   1.1919   0.05248   0.04893  -0.0192   0.0093   1.0000
  12.000   1.1744   0.05719   0.05386  -0.0197   0.0094   1.0000
  12.250   1.1571   0.06240   0.05926  -0.0214   0.0095   1.0000
  12.500   1.1392   0.06826   0.06530  -0.0241   0.0095   1.0000
  12.750   1.1207   0.07483   0.07204  -0.0279   0.0096   1.0000
  13.000   1.1015   0.08217   0.07954  -0.0326   0.0097   1.0000
  13.250   1.0765   0.09137   0.08890  -0.0386   0.0099   1.0000
  13.500   1.0584   0.09990   0.09756  -0.0445   0.0099   1.0000
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