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S3014-095-85 (s3014-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S3014-095-85 (s3014-il)
Reynolds number: 100,000
Max Cl/Cd: 51.41 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3014-il-100000-n5.txt
Download as CSV file: xf-s3014-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4468   0.07940   0.07477  -0.0333   1.0000   0.0295
  -8.250  -0.4503   0.07503   0.07047  -0.0360   1.0000   0.0291
  -8.000  -0.4539   0.07047   0.06596  -0.0393   1.0000   0.0288
  -7.750  -0.4561   0.06545   0.06093  -0.0426   1.0000   0.0284
  -7.500  -0.4598   0.06034   0.05577  -0.0449   1.0000   0.0281
  -7.250  -0.4653   0.05585   0.05119  -0.0455   1.0000   0.0278
  -7.000  -0.4726   0.05214   0.04735  -0.0442   1.0000   0.0277
  -6.750  -0.4800   0.04861   0.04361  -0.0422   1.0000   0.0280
  -6.500  -0.4689   0.04364   0.03817  -0.0437   0.9941   0.0287
  -6.250  -0.4451   0.03878   0.03264  -0.0465   0.9855   0.0293
  -6.000  -0.4195   0.03480   0.02810  -0.0483   0.9783   0.0292
  -5.750  -0.3908   0.03142   0.02416  -0.0499   0.9721   0.0292
  -5.500  -0.3612   0.02870   0.02091  -0.0510   0.9660   0.0294
  -5.250  -0.3301   0.02647   0.01821  -0.0521   0.9602   0.0297
  -5.000  -0.2971   0.02438   0.01578  -0.0534   0.9556   0.0303
  -4.750  -0.2690   0.02276   0.01401  -0.0537   0.9485   0.0314
  -4.500  -0.2360   0.02173   0.01286  -0.0550   0.9434   0.0344
  -4.250  -0.2075   0.02075   0.01173  -0.0551   0.9361   0.0368
  -4.000  -0.1763   0.01972   0.01057  -0.0557   0.9302   0.0381
  -3.750  -0.1489   0.01893   0.00964  -0.0555   0.9226   0.0397
  -3.500  -0.1196   0.01810   0.00873  -0.0557   0.9162   0.0424
  -3.250  -0.0930   0.01752   0.00804  -0.0554   0.9082   0.0471
  -3.000  -0.0640   0.01688   0.00737  -0.0555   0.9016   0.0585
  -2.750  -0.0397   0.01609   0.00692  -0.0549   0.8932   0.1209
  -2.500  -0.0131   0.01528   0.00664  -0.0549   0.8867   0.2433
  -2.250   0.0088   0.01456   0.00650  -0.0539   0.8777   0.3908
  -2.000   0.0322   0.01372   0.00643  -0.0527   0.8710   0.5848
  -1.750   0.0564   0.01316   0.00646  -0.0507   0.8628   0.7644
  -1.500   0.1125   0.01287   0.00623  -0.0550   0.8590   0.8966
  -1.250   0.1697   0.01277   0.00596  -0.0605   0.8527   0.9642
  -1.000   0.2200   0.01267   0.00566  -0.0649   0.8460   1.0000
  -0.750   0.2419   0.01270   0.00553  -0.0637   0.8353   1.0000
  -0.500   0.2645   0.01273   0.00541  -0.0626   0.8253   1.0000
  -0.250   0.2875   0.01274   0.00528  -0.0614   0.8155   1.0000
   0.000   0.3100   0.01279   0.00522  -0.0602   0.8039   1.0000
   0.250   0.3329   0.01283   0.00516  -0.0590   0.7923   1.0000
   0.500   0.3560   0.01286   0.00509  -0.0578   0.7805   1.0000
   0.750   0.3793   0.01288   0.00502  -0.0566   0.7684   1.0000
   1.000   0.4028   0.01290   0.00495  -0.0555   0.7559   1.0000
   1.250   0.4265   0.01293   0.00490  -0.0543   0.7427   1.0000
   1.500   0.4503   0.01297   0.00487  -0.0533   0.7288   1.0000
   1.750   0.4743   0.01301   0.00486  -0.0522   0.7141   1.0000
   2.000   0.4984   0.01307   0.00487  -0.0512   0.6988   1.0000
   2.250   0.5227   0.01314   0.00489  -0.0503   0.6829   1.0000
   2.500   0.5470   0.01322   0.00492  -0.0493   0.6663   1.0000
   2.750   0.5715   0.01331   0.00497  -0.0484   0.6490   1.0000
   3.000   0.5960   0.01341   0.00501  -0.0474   0.6313   1.0000
   3.250   0.6203   0.01355   0.00511  -0.0466   0.6113   1.0000
   3.500   0.6446   0.01370   0.00520  -0.0456   0.5907   1.0000
   3.750   0.6687   0.01389   0.00537  -0.0448   0.5686   1.0000
   4.000   0.6927   0.01410   0.00551  -0.0438   0.5454   1.0000
   4.250   0.7164   0.01435   0.00570  -0.0429   0.5204   1.0000
   4.500   0.7399   0.01463   0.00592  -0.0420   0.4943   1.0000
   4.750   0.7631   0.01496   0.00620  -0.0411   0.4674   1.0000
   5.000   0.7860   0.01532   0.00649  -0.0401   0.4401   1.0000
   5.250   0.8086   0.01573   0.00682  -0.0392   0.4129   1.0000
   5.500   0.8308   0.01617   0.00719  -0.0383   0.3861   1.0000
   5.750   0.8528   0.01665   0.00760  -0.0373   0.3608   1.0000
   6.000   0.8746   0.01716   0.00809  -0.0364   0.3362   1.0000
   6.250   0.8963   0.01769   0.00859  -0.0355   0.3138   1.0000
   6.500   0.9174   0.01827   0.00912  -0.0345   0.2927   1.0000
   6.750   0.9387   0.01884   0.00969  -0.0336   0.2731   1.0000
   7.000   0.9596   0.01945   0.01030  -0.0326   0.2544   1.0000
   7.250   0.9800   0.02009   0.01093  -0.0316   0.2372   1.0000
   7.500   1.0000   0.02076   0.01164  -0.0306   0.2211   1.0000
   7.750   1.0200   0.02142   0.01237  -0.0296   0.2052   1.0000
   8.000   1.0395   0.02212   0.01312  -0.0285   0.1901   1.0000
   8.250   1.0584   0.02285   0.01392  -0.0274   0.1757   1.0000
   8.500   1.0767   0.02363   0.01476  -0.0262   0.1623   1.0000
   8.750   1.0941   0.02445   0.01564  -0.0250   0.1495   1.0000
   9.000   1.1105   0.02533   0.01661  -0.0237   0.1375   1.0000
   9.250   1.1259   0.02623   0.01758  -0.0223   0.1249   1.0000
   9.500   1.1407   0.02711   0.01854  -0.0209   0.1093   1.0000
   9.750   1.1541   0.02806   0.01953  -0.0195   0.0923   1.0000
  10.000   1.1644   0.02921   0.02058  -0.0179   0.0742   1.0000
  10.250   1.1739   0.03037   0.02180  -0.0160   0.0601   1.0000
  10.500   1.1801   0.03180   0.02328  -0.0138   0.0478   1.0000
  10.750   1.1826   0.03357   0.02508  -0.0115   0.0374   1.0000
  11.000   1.1813   0.03572   0.02725  -0.0094   0.0303   1.0000
  11.250   1.1812   0.03786   0.02956  -0.0075   0.0255   1.0000
  11.500   1.1773   0.04041   0.03217  -0.0060   0.0225   1.0000
  11.750   1.1744   0.04300   0.03492  -0.0048   0.0206   1.0000
  12.000   1.1720   0.04567   0.03778  -0.0040   0.0195   1.0000
  12.250   1.1672   0.04876   0.04105  -0.0036   0.0182   1.0000
  12.500   1.1615   0.05213   0.04459  -0.0036   0.0175   1.0000
  12.750   1.1537   0.05598   0.04860  -0.0041   0.0168   1.0000
  13.000   1.1458   0.06005   0.05284  -0.0050   0.0166   1.0000
  13.250   1.1363   0.06460   0.05755  -0.0064   0.0163   1.0000
  13.500   1.1254   0.06960   0.06271  -0.0082   0.0160   1.0000
  13.750   1.1141   0.07490   0.06816  -0.0103   0.0158   1.0000
  14.000   1.1038   0.08032   0.07372  -0.0126   0.0156   1.0000
  14.250   1.0944   0.08585   0.07943  -0.0151   0.0155   1.0000
  14.500   1.0850   0.09158   0.08532  -0.0177   0.0154   1.0000
  14.750   1.0746   0.09773   0.09164  -0.0207   0.0153   1.0000
  15.000   1.0643   0.10405   0.09813  -0.0238   0.0152   1.0000
  15.250   1.0529   0.11084   0.10509  -0.0273   0.0151   1.0000
  15.500   1.0426   0.11760   0.11198  -0.0308   0.0151   1.0000
  15.750   1.0305   0.12502   0.11956  -0.0348   0.0151   1.0000
  16.000   1.0190   0.13255   0.12722  -0.0389   0.0151   1.0000
  16.250   1.0063   0.14074   0.13555  -0.0434   0.0151   1.0000
  16.500   0.9937   0.14919   0.14412  -0.0481   0.0152   1.0000
  16.750   0.9805   0.15828   0.15331  -0.0530   0.0153   1.0000
  17.000   0.9662   0.16829   0.16338  -0.0584   0.0155   1.0000
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