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S3014-095-85 (s3014-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S3014-095-85 (s3014-il)
Reynolds number: 1,000,000
Max Cl/Cd: 106.55 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3014-il-1000000.txt
Download as CSV file: xf-s3014-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3014-095-85                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4471   0.09647   0.09489  -0.0171   1.0000   0.0113
  -9.500  -0.4473   0.09177   0.09021  -0.0195   1.0000   0.0118
  -6.500  -0.4424   0.02218   0.01819  -0.0497   0.8774   0.0131
  -6.250  -0.4202   0.02076   0.01652  -0.0489   0.8715   0.0130
  -6.000  -0.3969   0.01925   0.01481  -0.0483   0.8652   0.0129
  -5.750  -0.3777   0.01584   0.01097  -0.0471   0.8593   0.0132
  -5.500  -0.3543   0.01400   0.00895  -0.0465   0.8537   0.0138
  -5.250  -0.3289   0.01306   0.00791  -0.0460   0.8478   0.0141
  -5.000  -0.3032   0.01236   0.00711  -0.0456   0.8425   0.0146
  -4.750  -0.2769   0.01167   0.00634  -0.0452   0.8366   0.0149
  -4.500  -0.2508   0.01107   0.00565  -0.0448   0.8308   0.0152
  -4.250  -0.2245   0.01048   0.00499  -0.0444   0.8251   0.0155
  -4.000  -0.1979   0.00999   0.00443  -0.0440   0.8190   0.0159
  -3.750  -0.1713   0.00960   0.00397  -0.0437   0.8133   0.0166
  -3.500  -0.1443   0.00918   0.00350  -0.0434   0.8069   0.0171
  -3.250  -0.1174   0.00886   0.00310  -0.0430   0.8008   0.0176
  -3.000  -0.0898   0.00861   0.00281  -0.0429   0.7944   0.0180
  -2.750  -0.0629   0.00823   0.00233  -0.0425   0.7878   0.0188
  -2.500  -0.0354   0.00797   0.00201  -0.0423   0.7810   0.0199
  -2.250  -0.0078   0.00778   0.00177  -0.0421   0.7735   0.0214
  -2.000   0.0200   0.00762   0.00157  -0.0420   0.7654   0.0238
  -1.750   0.0469   0.00731   0.00137  -0.0417   0.7570   0.0621
  -1.500   0.0731   0.00682   0.00123  -0.0415   0.7476   0.1603
  -1.250   0.0997   0.00652   0.00113  -0.0413   0.7383   0.2362
  -1.000   0.1262   0.00623   0.00106  -0.0411   0.7281   0.3157
  -0.750   0.1526   0.00591   0.00100  -0.0409   0.7170   0.4109
  -0.500   0.1780   0.00552   0.00097  -0.0405   0.7062   0.5365
  -0.250   0.2025   0.00515   0.00096  -0.0398   0.6949   0.6623
   0.000   0.2244   0.00473   0.00097  -0.0384   0.6830   0.8064
   0.250   0.2593   0.00445   0.00104  -0.0394   0.6701   0.9507
   0.500   0.3046   0.00453   0.00104  -0.0431   0.6551   0.9752
   0.750   0.3436   0.00462   0.00105  -0.0454   0.6394   0.9882
   1.000   0.3832   0.00471   0.00106  -0.0480   0.6228   0.9953
   1.250   0.4251   0.00480   0.00105  -0.0511   0.6043   0.9999
   1.500   0.4511   0.00490   0.00106  -0.0507   0.5866   1.0000
   1.750   0.4767   0.00500   0.00109  -0.0502   0.5688   1.0000
   2.000   0.5023   0.00512   0.00112  -0.0497   0.5485   1.0000
   2.250   0.5278   0.00526   0.00117  -0.0492   0.5277   1.0000
   2.500   0.5534   0.00540   0.00123  -0.0488   0.5066   1.0000
   2.750   0.5788   0.00557   0.00131  -0.0483   0.4846   1.0000
   3.000   0.6043   0.00574   0.00139  -0.0478   0.4607   1.0000
   3.250   0.6296   0.00594   0.00148  -0.0473   0.4366   1.0000
   3.500   0.6547   0.00616   0.00159  -0.0469   0.4112   1.0000
   3.750   0.6798   0.00638   0.00172  -0.0464   0.3860   1.0000
   4.000   0.7047   0.00662   0.00186  -0.0459   0.3592   1.0000
   4.250   0.7296   0.00687   0.00200  -0.0453   0.3343   1.0000
   4.500   0.7544   0.00714   0.00216  -0.0448   0.3103   1.0000
   4.750   0.7793   0.00738   0.00234  -0.0443   0.2895   1.0000
   5.000   0.8040   0.00765   0.00252  -0.0438   0.2702   1.0000
   5.250   0.8288   0.00790   0.00270  -0.0433   0.2516   1.0000
   5.500   0.8536   0.00814   0.00289  -0.0428   0.2362   1.0000
   5.750   0.8783   0.00840   0.00310  -0.0423   0.2200   1.0000
   6.000   0.9027   0.00869   0.00332  -0.0418   0.2031   1.0000
   6.250   0.9269   0.00900   0.00355  -0.0412   0.1842   1.0000
   6.500   0.9511   0.00931   0.00379  -0.0407   0.1668   1.0000
   6.750   0.9744   0.00971   0.00408  -0.0400   0.1455   1.0000
   7.000   0.9984   0.01004   0.00435  -0.0395   0.1305   1.0000
   7.250   1.0221   0.01039   0.00464  -0.0389   0.1167   1.0000
   7.500   1.0457   0.01075   0.00496  -0.0383   0.1034   1.0000
   7.750   1.0686   0.01117   0.00530  -0.0376   0.0877   1.0000
   8.000   1.0911   0.01163   0.00569  -0.0369   0.0730   1.0000
   8.250   1.1126   0.01218   0.00614  -0.0361   0.0567   1.0000
   8.500   1.1329   0.01283   0.00667  -0.0351   0.0378   1.0000
   8.750   1.1476   0.01404   0.00764  -0.0333   0.0102   1.0000
   9.000   1.1676   0.01469   0.00831  -0.0322   0.0073   1.0000
   9.250   1.1884   0.01524   0.00893  -0.0312   0.0066   1.0000
   9.500   1.2090   0.01577   0.00952  -0.0302   0.0063   1.0000
   9.750   1.2288   0.01635   0.01017  -0.0291   0.0059   1.0000
  10.000   1.2478   0.01696   0.01084  -0.0279   0.0057   1.0000
  10.250   1.2653   0.01766   0.01161  -0.0265   0.0053   1.0000
  10.500   1.2811   0.01845   0.01247  -0.0249   0.0051   1.0000
  10.750   1.2940   0.01938   0.01349  -0.0230   0.0048   1.0000
  11.000   1.3028   0.02036   0.01459  -0.0203   0.0048   1.0000
  11.250   1.2987   0.02189   0.01628  -0.0160   0.0045   1.0000
  11.500   1.3099   0.02265   0.01710  -0.0140   0.0044   1.0000
  11.750   1.3147   0.02386   0.01841  -0.0116   0.0044   1.0000
  12.000   1.3205   0.02508   0.01973  -0.0095   0.0043   1.0000
  12.250   1.3251   0.02649   0.02123  -0.0075   0.0042   1.0000
  12.500   1.3272   0.02815   0.02300  -0.0056   0.0042   1.0000
  12.750   1.3296   0.02991   0.02487  -0.0040   0.0040   1.0000
  13.000   1.3306   0.03189   0.02695  -0.0027   0.0041   1.0000
  13.250   1.3309   0.03407   0.02924  -0.0016   0.0040   1.0000
  13.500   1.3266   0.03681   0.03211  -0.0007   0.0041   1.0000
  13.750   1.3257   0.03939   0.03480  -0.0002   0.0040   1.0000
  14.000   1.3209   0.04254   0.03807   0.0000   0.0039   1.0000
  14.250   1.3176   0.04571   0.04137  -0.0002   0.0038   1.0000
  14.500   1.3132   0.04916   0.04494  -0.0007   0.0038   1.0000
  14.750   1.3069   0.05304   0.04894  -0.0016   0.0038   1.0000
  15.000   1.2935   0.05809   0.05414  -0.0029   0.0038   1.0000
  15.250   1.2939   0.06149   0.05762  -0.0044   0.0037   1.0000
  15.500   1.2826   0.06677   0.06303  -0.0064   0.0037   1.0000
  15.750   1.2717   0.07219   0.06858  -0.0087   0.0037   1.0000
  16.000   1.2606   0.07786   0.07438  -0.0113   0.0037   1.0000
  16.250   1.2491   0.08382   0.08046  -0.0141   0.0037   1.0000
  16.500   1.2345   0.09049   0.08727  -0.0173   0.0037   1.0000
  16.750   1.2246   0.09656   0.09345  -0.0204   0.0037   1.0000
  17.000   1.2092   0.10376   0.10078  -0.0241   0.0037   1.0000
  17.250   1.1949   0.11096   0.10810  -0.0279   0.0037   1.0000
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