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S3014-095-85 (s3014-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S3014-095-85 (s3014-il)
Reynolds number: 50,000
Max Cl/Cd: 32.54 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3014-il-50000.txt
Download as CSV file: xf-s3014-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4390   0.11761   0.11089  -0.0106   1.0000   0.2110
  -9.250  -0.4142   0.11166   0.10491  -0.0093   1.0000   0.2196
  -9.000  -0.4324   0.11100   0.10441  -0.0121   1.0000   0.2261
  -8.750  -0.4097   0.10580   0.09918  -0.0108   1.0000   0.2375
  -8.500  -0.4024   0.10210   0.09553  -0.0111   1.0000   0.2456
  -8.250  -0.4229   0.10172   0.09531  -0.0134   1.0000   0.2547
  -8.000  -0.4022   0.09687   0.09045  -0.0121   1.0000   0.2675
  -7.750  -0.3903   0.09297   0.08659  -0.0116   1.0000   0.2786
  -7.500  -0.3862   0.08992   0.08361  -0.0114   1.0000   0.2908
  -7.250  -0.3826   0.08709   0.08086  -0.0109   1.0000   0.3060
  -7.000  -0.3815   0.08452   0.07838  -0.0100   1.0000   0.3231
  -6.750  -0.3892   0.08259   0.07659  -0.0087   1.0000   0.3404
  -6.500  -0.4045   0.08119   0.07535  -0.0073   1.0000   0.3565
  -6.250  -0.3757   0.07658   0.07070  -0.0049   1.0000   0.3777
  -6.000  -0.3799   0.07448   0.06872  -0.0023   1.0000   0.3958
  -4.750  -0.4132   0.04566   0.03837  -0.0318   1.0000   0.1371
  -4.500  -0.3987   0.04187   0.03420  -0.0313   1.0000   0.1300
  -4.250  -0.3806   0.03837   0.02998  -0.0306   1.0000   0.1230
  -4.000  -0.3619   0.03555   0.02677  -0.0297   1.0000   0.1205
  -3.750  -0.3413   0.03302   0.02375  -0.0287   1.0000   0.1192
  -3.500  -0.3193   0.03087   0.02115  -0.0277   1.0000   0.1198
  -3.250  -0.2967   0.02919   0.01897  -0.0267   1.0000   0.1240
  -3.000  -0.2748   0.02770   0.01741  -0.0258   1.0000   0.1322
  -2.750  -0.2510   0.02635   0.01578  -0.0248   1.0000   0.1412
  -2.500  -0.2265   0.02500   0.01441  -0.0239   1.0000   0.1566
  -2.250  -0.2024   0.02371   0.01323  -0.0230   1.0000   0.1979
  -2.000  -0.1465   0.01875   0.01190  -0.0243   1.0000   1.0000
  -1.750  -0.1288   0.01893   0.01146  -0.0234   1.0000   1.0000
  -1.500  -0.1114   0.01918   0.01124  -0.0225   1.0000   1.0000
  -1.250  -0.0939   0.01947   0.01112  -0.0217   1.0000   1.0000
  -1.000  -0.0763   0.01981   0.01113  -0.0209   1.0000   1.0000
  -0.750  -0.0587   0.02019   0.01121  -0.0202   1.0000   1.0000
  -0.500  -0.0410   0.02061   0.01138  -0.0196   1.0000   1.0000
  -0.250  -0.0235   0.02108   0.01162  -0.0190   1.0000   1.0000
   0.000  -0.0060   0.02159   0.01191  -0.0185   1.0000   1.0000
   0.250   0.0114   0.02215   0.01228  -0.0181   1.0000   1.0000
   0.500   0.0349   0.02288   0.01284  -0.0189   0.9973   1.0000
   0.750   0.0880   0.02425   0.01399  -0.0253   0.9822   1.0000
   1.000   0.1349   0.02540   0.01498  -0.0303   0.9657   1.0000
   1.250   0.1811   0.02650   0.01598  -0.0350   0.9486   1.0000
   1.500   0.2290   0.02759   0.01698  -0.0397   0.9310   1.0000
   1.750   0.2749   0.02857   0.01791  -0.0438   0.9130   1.0000
   2.000   0.3121   0.02938   0.01870  -0.0462   0.8934   1.0000
   2.250   0.3578   0.03016   0.01948  -0.0498   0.8742   1.0000
   2.500   0.3990   0.03083   0.02017  -0.0523   0.8544   1.0000
   2.750   0.4372   0.03139   0.02079  -0.0541   0.8336   1.0000
   3.000   0.4923   0.03161   0.02111  -0.0580   0.8144   1.0000
   3.250   0.5212   0.03205   0.02162  -0.0579   0.7921   1.0000
   3.500   0.5697   0.03188   0.02160  -0.0599   0.7725   1.0000
   3.750   0.5996   0.03203   0.02184  -0.0592   0.7503   1.0000
   4.000   0.6412   0.03153   0.02148  -0.0593   0.7302   1.0000
   4.250   0.6712   0.03135   0.02144  -0.0580   0.7077   1.0000
   4.500   0.7099   0.03050   0.02071  -0.0569   0.6871   1.0000
   4.750   0.7378   0.03017   0.02048  -0.0550   0.6629   1.0000
   5.000   0.7737   0.02917   0.01961  -0.0532   0.6408   1.0000
   5.250   0.8034   0.02858   0.01909  -0.0511   0.6154   1.0000
   5.500   0.8303   0.02825   0.01881  -0.0488   0.5882   1.0000
   5.750   0.8569   0.02805   0.01862  -0.0467   0.5603   1.0000
   6.000   0.8826   0.02804   0.01865  -0.0447   0.5319   1.0000
   6.250   0.9073   0.02824   0.01883  -0.0427   0.5032   1.0000
   6.500   0.9309   0.02867   0.01922  -0.0409   0.4748   1.0000
   6.750   0.9535   0.02930   0.01984  -0.0392   0.4471   1.0000
   7.000   0.9755   0.03007   0.02060  -0.0375   0.4201   1.0000
   7.250   0.9975   0.03099   0.02154  -0.0360   0.3944   1.0000
   7.500   1.0208   0.03189   0.02235  -0.0346   0.3695   1.0000
   7.750   1.0395   0.03322   0.02379  -0.0330   0.3457   1.0000
   8.000   1.0591   0.03461   0.02524  -0.0315   0.3233   1.0000
   8.250   1.0794   0.03601   0.02667  -0.0301   0.3018   1.0000
   8.500   1.0972   0.03772   0.02854  -0.0287   0.2819   1.0000
   8.750   1.1130   0.03964   0.03065  -0.0270   0.2632   1.0000
   9.000   1.1323   0.04128   0.03231  -0.0257   0.2445   1.0000
   9.250   1.1499   0.04334   0.03444  -0.0242   0.2278   1.0000
   9.500   1.1593   0.04565   0.03704  -0.0222   0.2120   1.0000
   9.750   1.1694   0.04825   0.03988  -0.0203   0.1977   1.0000
  10.000   1.1757   0.05070   0.04256  -0.0182   0.1828   1.0000
  10.250   1.1809   0.05350   0.04561  -0.0160   0.1692   1.0000
  10.500   1.1819   0.05597   0.04827  -0.0136   0.1546   1.0000
  10.750   1.1809   0.05845   0.05088  -0.0112   0.1409   1.0000
  11.000   1.1774   0.06067   0.05319  -0.0087   0.1273   1.0000
  11.250   1.1752   0.06303   0.05557  -0.0065   0.1156   1.0000
  11.500   1.1510   0.06721   0.06005  -0.0039   0.1147   1.0000
  11.750   1.1252   0.07188   0.06495  -0.0026   0.1150   1.0000
  12.000   1.0995   0.07732   0.07057  -0.0027   0.1161   1.0000
  12.250   1.0734   0.08357   0.07694  -0.0042   0.1173   1.0000
  12.500   1.0496   0.09045   0.08389  -0.0066   0.1182   1.0000
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