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S3014-095-85 (s3014-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S3014-095-85 (s3014-il)
Reynolds number: 100,000
Max Cl/Cd: 51.89 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3014-il-100000.txt
Download as CSV file: xf-s3014-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3443   0.11135   0.10680  -0.0159   1.0000   0.0935
 -10.000  -0.3554   0.10867   0.10417  -0.0193   1.0000   0.0963
  -9.750  -0.3729   0.10624   0.10184  -0.0237   1.0000   0.0971
  -9.500  -0.3432   0.09997   0.09552  -0.0204   1.0000   0.1003
  -9.250  -0.3346   0.09642   0.09198  -0.0205   1.0000   0.1041
  -9.000  -0.3371   0.09292   0.08852  -0.0224   1.0000   0.1085
  -8.750  -0.3603   0.09010   0.08581  -0.0278   1.0000   0.1108
  -8.500  -0.3455   0.08481   0.08053  -0.0265   1.0000   0.1133
  -8.250  -0.3315   0.08130   0.07703  -0.0254   1.0000   0.1175
  -8.000  -0.3393   0.07786   0.07366  -0.0278   1.0000   0.1231
  -7.750  -0.4147   0.08363   0.07919  -0.0263   1.0000   0.1166
  -7.500  -0.4178   0.08068   0.07632  -0.0278   1.0000   0.1209
  -7.250  -0.4559   0.07745   0.07304  -0.0405   1.0000   0.1253
  -7.000  -0.4288   0.07328   0.06906  -0.0335   1.0000   0.1284
  -6.750  -0.4262   0.07101   0.06685  -0.0316   1.0000   0.1341
  -6.500  -0.4665   0.06931   0.06492  -0.0359   1.0000   0.1397
  -6.250  -0.4510   0.06567   0.06154  -0.0304   1.0000   0.1425
  -6.000  -0.4511   0.06387   0.05978  -0.0275   1.0000   0.1487
  -5.750  -0.4597   0.06086   0.05668  -0.0275   1.0000   0.1565
  -5.500  -0.4630   0.05860   0.05426  -0.0276   1.0000   0.1691
  -5.250  -0.4551   0.05620   0.05201  -0.0240   1.0000   0.1732
  -5.000  -0.4519   0.05347   0.04916  -0.0236   1.0000   0.1855
  -4.750  -0.4456   0.05101   0.04660  -0.0230   1.0000   0.1990
  -4.500  -0.4107   0.03525   0.02887  -0.0287   1.0000   0.0795
  -4.250  -0.3900   0.03133   0.02401  -0.0271   1.0000   0.0689
  -4.000  -0.3704   0.02872   0.02109  -0.0261   1.0000   0.0670
  -3.750  -0.3490   0.02663   0.01860  -0.0251   1.0000   0.0658
  -3.500  -0.3086   0.02473   0.01620  -0.0273   0.9946   0.0671
  -3.250  -0.2688   0.02360   0.01462  -0.0293   0.9882   0.0701
  -3.000  -0.2280   0.02174   0.01275  -0.0318   0.9832   0.0731
  -2.750  -0.1921   0.02074   0.01175  -0.0334   0.9758   0.0785
  -2.500  -0.1509   0.01979   0.01082  -0.0359   0.9698   0.0912
  -2.250  -0.1194   0.01842   0.00995  -0.0368   0.9616   0.1611
  -2.000  -0.0873   0.01642   0.00991  -0.0380   0.9560   0.5736
  -1.750   0.0093   0.01557   0.00981  -0.0495   0.9581   1.0000
  -1.500   0.0480   0.01577   0.00970  -0.0520   0.9482   1.0000
  -1.250   0.0942   0.01596   0.00960  -0.0559   0.9402   1.0000
  -1.000   0.1377   0.01611   0.00953  -0.0592   0.9311   1.0000
  -0.750   0.1773   0.01626   0.00951  -0.0617   0.9211   1.0000
  -0.500   0.2322   0.01625   0.00932  -0.0669   0.9148   1.0000
  -0.250   0.2653   0.01635   0.00931  -0.0679   0.9030   1.0000
   0.000   0.2988   0.01643   0.00929  -0.0688   0.8914   1.0000
   0.250   0.3328   0.01646   0.00923  -0.0696   0.8801   1.0000
   0.500   0.3673   0.01641   0.00910  -0.0703   0.8693   1.0000
   0.750   0.3980   0.01634   0.00897  -0.0700   0.8578   1.0000
   1.000   0.4226   0.01636   0.00894  -0.0688   0.8444   1.0000
   1.250   0.4466   0.01636   0.00889  -0.0673   0.8309   1.0000
   1.500   0.4702   0.01634   0.00883  -0.0658   0.8174   1.0000
   1.750   0.4936   0.01630   0.00876  -0.0642   0.8037   1.0000
   2.000   0.5170   0.01624   0.00868  -0.0625   0.7899   1.0000
   2.250   0.5405   0.01616   0.00858  -0.0608   0.7759   1.0000
   2.500   0.5642   0.01606   0.00846  -0.0592   0.7615   1.0000
   2.750   0.5880   0.01594   0.00834  -0.0575   0.7467   1.0000
   3.000   0.6121   0.01580   0.00818  -0.0559   0.7313   1.0000
   3.250   0.6365   0.01565   0.00800  -0.0543   0.7153   1.0000
   3.500   0.6606   0.01554   0.00787  -0.0527   0.6976   1.0000
   3.750   0.6842   0.01548   0.00784  -0.0512   0.6773   1.0000
   4.000   0.7090   0.01536   0.00766  -0.0497   0.6576   1.0000
   4.250   0.7325   0.01539   0.00767  -0.0483   0.6337   1.0000
   4.500   0.7565   0.01542   0.00765  -0.0469   0.6091   1.0000
   4.750   0.7802   0.01552   0.00770  -0.0455   0.5823   1.0000
   5.000   0.8033   0.01572   0.00782  -0.0441   0.5534   1.0000
   5.250   0.8260   0.01599   0.00802  -0.0428   0.5225   1.0000
   5.500   0.8484   0.01635   0.00828  -0.0415   0.4910   1.0000
   5.750   0.8704   0.01679   0.00859  -0.0402   0.4598   1.0000
   6.000   0.8922   0.01732   0.00902  -0.0390   0.4297   1.0000
   6.250   0.9137   0.01790   0.00950  -0.0378   0.4008   1.0000
   6.500   0.9350   0.01855   0.01006  -0.0367   0.3733   1.0000
   6.750   0.9561   0.01924   0.01068  -0.0356   0.3474   1.0000
   7.000   0.9772   0.01999   0.01138  -0.0345   0.3237   1.0000
   7.250   0.9980   0.02077   0.01209  -0.0334   0.3011   1.0000
   7.500   1.0185   0.02161   0.01293  -0.0323   0.2795   1.0000
   7.750   1.0389   0.02247   0.01375  -0.0312   0.2593   1.0000
   8.000   1.0591   0.02341   0.01467  -0.0302   0.2404   1.0000
   8.250   1.0782   0.02433   0.01569  -0.0290   0.2216   1.0000
   8.500   1.0975   0.02532   0.01669  -0.0278   0.2045   1.0000
   8.750   1.1164   0.02634   0.01769  -0.0266   0.1883   1.0000
   9.000   1.1352   0.02748   0.01882  -0.0255   0.1731   1.0000
   9.250   1.1520   0.02861   0.02002  -0.0241   0.1581   1.0000
   9.500   1.1650   0.02955   0.02112  -0.0223   0.1425   1.0000
   9.750   1.1724   0.03015   0.02189  -0.0200   0.1256   1.0000
  10.000   1.1772   0.03083   0.02261  -0.0176   0.1092   1.0000
  10.250   1.1809   0.03203   0.02382  -0.0151   0.0939   1.0000
  10.500   1.1788   0.03372   0.02556  -0.0118   0.0775   1.0000
  10.750   1.1765   0.03598   0.02786  -0.0087   0.0633   1.0000
  11.000   1.1771   0.03854   0.03038  -0.0063   0.0540   1.0000
  11.250   1.1808   0.04065   0.03261  -0.0044   0.0481   1.0000
  11.500   1.1860   0.04340   0.03540  -0.0028   0.0438   1.0000
  11.750   1.1902   0.04590   0.03819  -0.0012   0.0409   1.0000
  12.000   1.1941   0.04857   0.04105   0.0001   0.0388   1.0000
  12.250   1.1975   0.05146   0.04408   0.0013   0.0372   1.0000
  12.500   1.2007   0.05486   0.04761   0.0022   0.0361   1.0000
  12.750   1.1982   0.05934   0.05236   0.0030   0.0354   1.0000
  13.000   1.1889   0.06369   0.05699   0.0035   0.0352   1.0000
  13.250   1.1747   0.06804   0.06159   0.0035   0.0351   1.0000
  13.500   1.1589   0.07279   0.06659   0.0028   0.0351   1.0000
  13.750   1.1416   0.07809   0.07213   0.0013   0.0351   1.0000
  14.000   1.1230   0.08373   0.07803  -0.0009   0.0352   1.0000
  14.250   1.1022   0.08994   0.08447  -0.0042   0.0354   1.0000
  14.500   1.0785   0.09707   0.09181  -0.0090   0.0359   1.0000
  14.750   0.9821   0.12295   0.11821  -0.0288   0.0409   1.0000
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