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FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX60-100 10.0% smoothed (fx60100sm-il)
Reynolds number: 100,000
Max Cl/Cd: 62.76 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60100sm-il-100000.txt
Download as CSV file: xf-fx60100sm-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX60-100 10.0% smoothed                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3542   0.10230   0.09733  -0.0336   1.0000   0.1070
  -8.750  -0.3677   0.10041   0.09556  -0.0362   1.0000   0.1121
  -8.500  -0.3997   0.09958   0.09494  -0.0395   1.0000   0.1132
  -8.250  -0.3572   0.09400   0.08925  -0.0342   1.0000   0.1180
  -8.000  -0.3598   0.09186   0.08719  -0.0338   1.0000   0.1237
  -7.750  -0.3908   0.09099   0.08652  -0.0342   1.0000   0.1265
  -7.500  -0.4302   0.08968   0.08541  -0.0378   1.0000   0.1274
  -7.250  -0.3795   0.08562   0.08124  -0.0290   1.0000   0.1359
  -7.000  -0.4050   0.08448   0.08025  -0.0275   1.0000   0.1395
  -6.750  -0.4387   0.08084   0.07677  -0.0364   1.0000   0.1420
  -6.500  -0.3940   0.07245   0.06880  -0.0230   1.0000   0.1554
  -6.250  -0.3767   0.06918   0.06552  -0.0171   1.0000   0.1599
  -6.000  -0.4263   0.07487   0.07093  -0.0238   1.0000   0.1607
  -5.750  -0.4321   0.07051   0.06661  -0.0311   1.0000   0.1718
  -5.500  -0.4260   0.06937   0.06551  -0.0249   1.0000   0.1764
  -5.250  -0.4222   0.06561   0.06176  -0.0286   1.0000   0.1883
  -5.000  -0.3289   0.03487   0.02833  -0.0726   1.0000   0.0707
  -4.750  -0.2963   0.03044   0.02341  -0.0750   1.0000   0.0639
  -4.500  -0.2630   0.02871   0.02078  -0.0757   1.0000   0.0590
  -4.250  -0.2338   0.02612   0.01792  -0.0765   1.0000   0.0581
  -4.000  -0.2059   0.02439   0.01593  -0.0767   1.0000   0.0581
  -3.750  -0.1793   0.02307   0.01443  -0.0767   1.0000   0.0595
  -3.500  -0.1535   0.02166   0.01313  -0.0769   1.0000   0.0644
  -3.250  -0.1279   0.02084   0.01227  -0.0767   1.0000   0.0686
  -3.000  -0.1013   0.02005   0.01148  -0.0768   1.0000   0.0738
  -2.750  -0.0729   0.01934   0.01082  -0.0776   0.9999   0.0896
  -2.500  -0.0245   0.01765   0.01070  -0.0824   0.9960   0.4388
  -2.250   0.0134   0.01869   0.01180  -0.0840   0.9872   0.5231
  -2.000   0.0481   0.01951   0.01274  -0.0846   0.9783   0.5737
  -1.750   0.0899   0.01977   0.01288  -0.0874   0.9705   0.5982
  -1.500   0.1257   0.01991   0.01294  -0.0890   0.9609   0.6195
  -1.250   0.1673   0.02005   0.01300  -0.0917   0.9530   0.6411
  -1.000   0.2044   0.02008   0.01301  -0.0935   0.9434   0.6604
  -0.750   0.2408   0.02011   0.01299  -0.0952   0.9335   0.6800
  -0.500   0.2857   0.02004   0.01290  -0.0983   0.9263   0.7002
  -0.250   0.3180   0.01998   0.01285  -0.0992   0.9149   0.7190
   0.000   0.3544   0.01989   0.01277  -0.1007   0.9049   0.7407
   0.250   0.3986   0.01961   0.01254  -0.1033   0.8977   0.7631
   0.500   0.4310   0.01946   0.01243  -0.1039   0.8863   0.7872
   0.750   0.4667   0.01919   0.01223  -0.1049   0.8765   0.8153
   1.000   0.5056   0.01865   0.01181  -0.1060   0.8690   0.8499
   1.250   0.5312   0.01817   0.01152  -0.1047   0.8570   0.9084
   1.500   0.5788   0.01784   0.01117  -0.1086   0.8460   1.0000
   1.750   0.6284   0.01742   0.01069  -0.1123   0.8381   1.0000
   2.000   0.6657   0.01723   0.01045  -0.1137   0.8256   1.0000
   2.250   0.6999   0.01705   0.01024  -0.1143   0.8122   1.0000
   2.500   0.7329   0.01686   0.01002  -0.1146   0.7984   1.0000
   2.750   0.7650   0.01666   0.00983  -0.1145   0.7841   1.0000
   3.000   0.7964   0.01645   0.00960  -0.1143   0.7689   1.0000
   3.250   0.8272   0.01623   0.00936  -0.1138   0.7528   1.0000
   3.500   0.8548   0.01616   0.00928  -0.1130   0.7333   1.0000
   3.750   0.8829   0.01603   0.00915  -0.1121   0.7126   1.0000
   4.000   0.9104   0.01592   0.00900  -0.1111   0.6900   1.0000
   4.250   0.9374   0.01587   0.00888  -0.1100   0.6659   1.0000
   4.500   0.9627   0.01595   0.00896  -0.1088   0.6393   1.0000
   4.750   0.9878   0.01609   0.00906  -0.1077   0.6120   1.0000
   5.000   1.0124   0.01629   0.00920  -0.1066   0.5833   1.0000
   5.250   1.0362   0.01655   0.00940  -0.1053   0.5526   1.0000
   5.500   1.0594   0.01688   0.00966  -0.1040   0.5203   1.0000
   5.750   1.0813   0.01729   0.01002  -0.1027   0.4840   1.0000
   6.000   1.1021   0.01780   0.01040  -0.1011   0.4447   1.0000
   6.250   1.1209   0.01843   0.01089  -0.0994   0.3979   1.0000
   6.500   1.1375   0.01932   0.01152  -0.0975   0.3451   1.0000
   6.750   1.1525   0.02050   0.01238  -0.0954   0.2898   1.0000
   7.000   1.1674   0.02193   0.01343  -0.0935   0.2455   1.0000
   7.250   1.1843   0.02335   0.01459  -0.0920   0.2142   1.0000
   7.500   1.2036   0.02469   0.01582  -0.0907   0.1919   1.0000
   7.750   1.2242   0.02610   0.01710  -0.0897   0.1757   1.0000
   8.000   1.2457   0.02747   0.01845  -0.0889   0.1618   1.0000
   8.250   1.2682   0.02892   0.01995  -0.0881   0.1503   1.0000
   8.500   1.2912   0.03051   0.02160  -0.0874   0.1404   1.0000
   8.750   1.3148   0.03221   0.02322  -0.0870   0.1307   1.0000
   9.000   1.3354   0.03368   0.02489  -0.0860   0.1219   1.0000
   9.250   1.3555   0.03552   0.02693  -0.0850   0.1131   1.0000
   9.500   1.3772   0.03756   0.02890  -0.0846   0.1043   1.0000
   9.750   1.3905   0.03900   0.03069  -0.0826   0.0960   1.0000
  10.000   1.4056   0.04125   0.03313  -0.0812   0.0879   1.0000
  10.250   1.4237   0.04367   0.03542  -0.0806   0.0791   1.0000
  10.500   1.4267   0.04542   0.03774  -0.0774   0.0727   1.0000
  10.750   1.4399   0.04828   0.04058  -0.0763   0.0662   1.0000
  11.000   1.4374   0.05064   0.04348  -0.0728   0.0615   1.0000
  11.250   1.4463   0.05244   0.04529  -0.0712   0.0565   1.0000
  11.500   1.4421   0.05664   0.04986  -0.0684   0.0540   1.0000
  11.750   1.4266   0.05975   0.05342  -0.0644   0.0526   1.0000
  12.000   1.4101   0.06321   0.05725  -0.0611   0.0513   1.0000
  12.250   1.3931   0.06703   0.06139  -0.0588   0.0503   1.0000
  12.500   1.3761   0.07109   0.06573  -0.0574   0.0492   1.0000
  12.750   1.3718   0.07400   0.06871  -0.0568   0.0470   1.0000
  13.000   1.3716   0.07747   0.07214  -0.0566   0.0449   1.0000
  13.250   1.3504   0.08315   0.07808  -0.0570   0.0446   1.0000
  13.500   1.3254   0.08913   0.08434  -0.0586   0.0448   1.0000
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