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S3016-095-87 (s3016-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S3016-095-87 (s3016-il)
Reynolds number: 50,000
Max Cl/Cd: 31.76 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3016-il-50000.txt
Download as CSV file: xf-s3016-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3016-095-87                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.4339   0.08759   0.08143  -0.0047   1.0000   0.3273
  -7.000  -0.4339   0.08471   0.07864  -0.0040   1.0000   0.3420
  -6.750  -0.4112   0.08021   0.07414  -0.0025   1.0000   0.3604
  -6.000  -0.4733   0.05461   0.04792  -0.0359   1.0000   0.1389
  -5.750  -0.4709   0.04933   0.04210  -0.0357   1.0000   0.1254
  -5.500  -0.4612   0.04569   0.03834  -0.0341   1.0000   0.1214
  -5.250  -0.4523   0.04194   0.03415  -0.0327   1.0000   0.1179
  -5.000  -0.4403   0.03887   0.03064  -0.0312   1.0000   0.1183
  -4.750  -0.4258   0.03611   0.02745  -0.0296   1.0000   0.1201
  -4.500  -0.4085   0.03340   0.02427  -0.0281   1.0000   0.1207
  -4.250  -0.3889   0.03098   0.02136  -0.0266   1.0000   0.1224
  -4.000  -0.3680   0.02887   0.01878  -0.0252   1.0000   0.1277
  -3.750  -0.3474   0.02733   0.01708  -0.0238   1.0000   0.1390
  -3.500  -0.3251   0.02563   0.01529  -0.0225   1.0000   0.1513
  -3.250  -0.3023   0.02407   0.01378  -0.0212   1.0000   0.1740
  -3.000  -0.2787   0.02229   0.01233  -0.0201   1.0000   0.2423
  -2.750  -0.2640   0.02004   0.01154  -0.0174   1.0000   0.4511
  -2.500  -0.2581   0.01867   0.01145  -0.0112   1.0000   0.6699
  -2.250  -0.1510   0.01805   0.01065  -0.0227   1.0000   1.0000
  -2.000  -0.1439   0.01802   0.01022  -0.0207   1.0000   1.0000
  -1.750  -0.1317   0.01812   0.00996  -0.0191   1.0000   1.0000
  -1.500  -0.1174   0.01829   0.00980  -0.0178   1.0000   1.0000
  -1.250  -0.1020   0.01851   0.00970  -0.0166   1.0000   1.0000
  -1.000  -0.0859   0.01877   0.00971  -0.0156   1.0000   1.0000
  -0.750  -0.0694   0.01909   0.00979  -0.0147   1.0000   1.0000
  -0.500  -0.0526   0.01945   0.00994  -0.0139   1.0000   1.0000
  -0.250  -0.0357   0.01985   0.01013  -0.0132   1.0000   1.0000
   0.000  -0.0188   0.02030   0.01041  -0.0126   1.0000   1.0000
   0.250  -0.0019   0.02080   0.01076  -0.0121   1.0000   1.0000
   0.500   0.0149   0.02135   0.01118  -0.0116   1.0000   1.0000
   0.750   0.0341   0.02200   0.01171  -0.0117   0.9989   1.0000
   1.000   0.0914   0.02338   0.01294  -0.0190   0.9817   1.0000
   1.250   0.1428   0.02453   0.01401  -0.0249   0.9628   1.0000
   1.500   0.1981   0.02569   0.01511  -0.0311   0.9438   1.0000
   1.750   0.2438   0.02660   0.01600  -0.0353   0.9229   1.0000
   2.000   0.2963   0.02745   0.01688  -0.0404   0.9019   1.0000
   2.250   0.3389   0.02814   0.01760  -0.0434   0.8798   1.0000
   2.500   0.3935   0.02864   0.01818  -0.0480   0.8583   1.0000
   2.750   0.4340   0.02906   0.01870  -0.0500   0.8348   1.0000
   3.000   0.4932   0.02899   0.01878  -0.0541   0.8139   1.0000
   3.250   0.5245   0.02919   0.01907  -0.0539   0.7894   1.0000
   3.500   0.5641   0.02900   0.01904  -0.0541   0.7666   1.0000
   3.750   0.6025   0.02856   0.01871  -0.0536   0.7435   1.0000
   4.000   0.6318   0.02832   0.01858  -0.0520   0.7182   1.0000
   4.250   0.6633   0.02782   0.01821  -0.0502   0.6934   1.0000
   4.500   0.6971   0.02699   0.01746  -0.0482   0.6693   1.0000
   4.750   0.7252   0.02648   0.01699  -0.0457   0.6420   1.0000
   5.000   0.7519   0.02611   0.01668  -0.0432   0.6132   1.0000
   5.250   0.7767   0.02599   0.01655  -0.0408   0.5827   1.0000
   5.500   0.8000   0.02613   0.01668  -0.0385   0.5509   1.0000
   5.750   0.8237   0.02639   0.01690  -0.0365   0.5196   1.0000
   6.000   0.8471   0.02681   0.01731  -0.0345   0.4891   1.0000
   6.250   0.8700   0.02739   0.01783  -0.0327   0.4592   1.0000
   6.500   0.8923   0.02817   0.01858  -0.0311   0.4307   1.0000
   6.750   0.9140   0.02908   0.01947  -0.0295   0.4030   1.0000
   7.000   0.9355   0.03015   0.02057  -0.0280   0.3769   1.0000
   7.250   0.9577   0.03124   0.02161  -0.0266   0.3522   1.0000
   7.500   0.9784   0.03250   0.02290  -0.0252   0.3282   1.0000
   7.750   0.9973   0.03409   0.02461  -0.0238   0.3061   1.0000
   8.000   1.0188   0.03544   0.02592  -0.0225   0.2845   1.0000
   8.250   1.0358   0.03742   0.02810  -0.0211   0.2656   1.0000
   8.500   1.0520   0.03935   0.03027  -0.0196   0.2469   1.0000
   8.750   1.0698   0.04131   0.03233  -0.0182   0.2297   1.0000
   9.000   1.0879   0.04336   0.03444  -0.0168   0.2134   1.0000
   9.250   1.1025   0.04562   0.03683  -0.0153   0.1977   1.0000
   9.500   1.1150   0.04821   0.03962  -0.0136   0.1840   1.0000
   9.750   1.1244   0.05070   0.04231  -0.0118   0.1700   1.0000
  10.000   1.1116   0.05516   0.04745  -0.0092   0.1646   1.0000
  10.250   1.1164   0.05800   0.05043  -0.0074   0.1533   1.0000
  10.500   1.1017   0.06226   0.05506  -0.0053   0.1487   1.0000
  10.750   1.1029   0.06568   0.05856  -0.0038   0.1407   1.0000
  11.000   1.0775   0.07066   0.06380  -0.0022   0.1407   1.0000
  11.250   1.0510   0.07575   0.06901  -0.0013   0.1416   1.0000
  11.500   1.0248   0.08168   0.07502  -0.0021   0.1425   1.0000
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