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S8064 (s8064-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S8064 (s8064-il)
Reynolds number: 50,000
Max Cl/Cd: 30.97 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8064-il-50000.txt
Download as CSV file: xf-s8064-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8064                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4325   0.10549   0.09866  -0.0255   1.0000   0.3235
  -9.500  -0.5632   0.08416   0.07777  -0.0518   1.0000   0.1389
  -9.250  -0.5721   0.07968   0.07332  -0.0508   1.0000   0.1294
  -9.000  -0.6156   0.07722   0.07092  -0.0472   1.0000   0.1272
  -8.750  -0.6673   0.07495   0.06859  -0.0424   1.0000   0.1247
  -8.500  -0.6741   0.07123   0.06481  -0.0399   1.0000   0.1192
  -8.250  -0.6929   0.06777   0.06124  -0.0366   1.0000   0.1156
  -8.000  -0.7380   0.06449   0.05727  -0.0310   1.0000   0.1091
  -7.750  -0.7321   0.06035   0.05311  -0.0290   1.0000   0.1071
  -7.500  -0.7344   0.05667   0.04921  -0.0261   1.0000   0.1050
  -7.250  -0.7365   0.05306   0.04525  -0.0231   1.0000   0.1030
  -7.000  -0.7356   0.04949   0.04124  -0.0200   1.0000   0.1018
  -6.750  -0.7302   0.04637   0.03768  -0.0172   1.0000   0.1031
  -6.500  -0.7222   0.04351   0.03430  -0.0145   1.0000   0.1062
  -6.250  -0.7111   0.04084   0.03096  -0.0118   1.0000   0.1089
  -6.000  -0.6934   0.03788   0.02798  -0.0103   1.0000   0.1149
  -5.750  -0.6767   0.03560   0.02523  -0.0082   1.0000   0.1247
  -5.500  -0.6567   0.03344   0.02283  -0.0066   1.0000   0.1382
  -5.250  -0.6352   0.03135   0.02085  -0.0053   1.0000   0.1586
  -5.000  -0.6137   0.02947   0.01904  -0.0038   1.0000   0.1877
  -4.750  -0.5928   0.02763   0.01745  -0.0021   1.0000   0.2303
  -4.500  -0.5757   0.02562   0.01600   0.0000   1.0000   0.3009
  -4.250  -0.5710   0.02304   0.01509   0.0047   1.0000   0.4766
  -4.000  -0.5711   0.02345   0.01661   0.0151   1.0000   0.6929
  -3.750  -0.5638   0.02476   0.01781   0.0233   1.0000   0.7782
  -3.500  -0.5343   0.02660   0.01934   0.0286   1.0000   0.8428
  -3.250  -0.3126   0.03118   0.02244   0.0021   1.0000   0.9318
  -3.000  -0.1726   0.03085   0.02134  -0.0193   1.0000   0.9789
  -2.750  -0.1016   0.02992   0.02001  -0.0302   1.0000   1.0000
  -2.500  -0.1020   0.02944   0.01945  -0.0276   1.0000   1.0000
  -2.250  -0.1023   0.02900   0.01893  -0.0250   1.0000   1.0000
  -2.000  -0.1025   0.02860   0.01845  -0.0222   1.0000   1.0000
  -1.750  -0.1026   0.02824   0.01801  -0.0194   1.0000   1.0000
  -1.500  -0.1025   0.02792   0.01762  -0.0165   1.0000   1.0000
  -1.250  -0.1023   0.02763   0.01724  -0.0136   1.0000   1.0000
  -1.000  -0.1020   0.02737   0.01692  -0.0106   1.0000   1.0000
  -0.750  -0.1017   0.02714   0.01662  -0.0075   1.0000   1.0000
  -0.500  -0.1013   0.02693   0.01634  -0.0044   1.0000   1.0000
  -0.250  -0.1010   0.02673   0.01609  -0.0013   1.0000   1.0000
   0.000  -0.1005   0.02655   0.01585   0.0019   1.0000   1.0000
   0.250  -0.0995   0.02640   0.01564   0.0050   1.0000   1.0000
   0.500  -0.0970   0.02629   0.01547   0.0079   1.0000   1.0000
   0.750  -0.0923   0.02627   0.01537   0.0104   1.0000   1.0000
   1.000  -0.0854   0.02634   0.01537   0.0126   1.0000   1.0000
   1.250  -0.0762   0.02652   0.01547   0.0144   1.0000   1.0000
   1.500  -0.0649   0.02679   0.01567   0.0158   1.0000   1.0000
   1.750  -0.0522   0.02715   0.01598   0.0169   1.0000   1.0000
   2.000  -0.0386   0.02758   0.01636   0.0179   1.0000   1.0000
   2.250  -0.0242   0.02808   0.01682   0.0186   1.0000   1.0000
   2.500  -0.0095   0.02864   0.01736   0.0193   1.0000   1.0000
   2.750   0.0056   0.02926   0.01796   0.0198   1.0000   1.0000
   3.000   0.0208   0.02994   0.01864   0.0202   1.0000   1.0000
   3.250   0.0360   0.03068   0.01939   0.0205   1.0000   1.0000
   3.500   0.0762   0.03241   0.02119   0.0159   0.9882   1.0000
   3.750   0.1322   0.03463   0.02353   0.0085   0.9642   1.0000
   4.000   0.1818   0.03653   0.02557   0.0027   0.9411   1.0000
   4.250   0.2263   0.03808   0.02726  -0.0017   0.9180   1.0000
   4.500   0.2632   0.03930   0.02862  -0.0046   0.8946   1.0000
   4.750   0.3078   0.04058   0.03012  -0.0083   0.8705   1.0000
   5.000   0.3506   0.04156   0.03130  -0.0114   0.8457   1.0000
   5.250   0.3857   0.04222   0.03219  -0.0130   0.8200   1.0000
   5.500   0.4278   0.04260   0.03283  -0.0150   0.7929   1.0000
   5.750   0.4764   0.04240   0.03295  -0.0171   0.7637   1.0000
   6.000   0.5462   0.04070   0.03175  -0.0201   0.7315   1.0000
   6.250   0.6049   0.03792   0.02945  -0.0201   0.6937   1.0000
   6.500   0.7178   0.02957   0.02203  -0.0208   0.6416   1.0000
   6.750   0.7706   0.02488   0.01729  -0.0153   0.5065   1.0000
   7.000   0.7725   0.02628   0.01713  -0.0087   0.3532   1.0000
   7.250   0.7847   0.02865   0.01867  -0.0058   0.2714   1.0000
   7.500   0.8194   0.03111   0.02070  -0.0064   0.2183   1.0000
   7.750   0.8527   0.03343   0.02287  -0.0069   0.1858   1.0000
   8.000   0.8882   0.03622   0.02559  -0.0077   0.1645   1.0000
   8.250   0.9130   0.03889   0.02849  -0.0070   0.1496   1.0000
   8.500   0.9357   0.04179   0.03148  -0.0062   0.1372   1.0000
   8.750   0.9477   0.04445   0.03464  -0.0037   0.1292   1.0000
   9.000   0.9619   0.04776   0.03818  -0.0020   0.1221   1.0000
   9.250   0.9648   0.05071   0.04162   0.0013   0.1171   1.0000
   9.500   0.9735   0.05414   0.04531   0.0034   0.1134   1.0000
   9.750   0.9837   0.05838   0.04966   0.0049   0.1102   1.0000
  10.000   0.9735   0.06174   0.05349   0.0087   0.1093   1.0000
  10.250   0.9612   0.06529   0.05741   0.0122   0.1089   1.0000
  10.500   0.9478   0.06911   0.06150   0.0152   0.1091   1.0000
  10.750   0.9326   0.07291   0.06551   0.0181   0.1095   1.0000
  11.000   0.9175   0.07696   0.06970   0.0204   0.1100   1.0000
  11.250   0.8404   0.08238   0.07549   0.0225   0.1200   1.0000
  11.500   0.8186   0.08819   0.08135   0.0215   0.1221   1.0000
  11.750   0.8088   0.09399   0.08717   0.0203   0.1237   1.0000
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