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FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX60-100 10.0% smoothed (fx60100sm-il)
Reynolds number: 50,000
Max Cl/Cd: 40.63 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60100sm-il-50000.txt
Download as CSV file: xf-fx60100sm-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3691   0.12111   0.11401  -0.0256   1.0000   0.2144
  -9.500  -0.3512   0.11651   0.10940  -0.0246   1.0000   0.2231
  -9.250  -0.3620   0.11545   0.10847  -0.0256   1.0000   0.2288
  -9.000  -0.3438   0.11092   0.10394  -0.0246   1.0000   0.2375
  -8.750  -0.3506   0.10914   0.10227  -0.0250   1.0000   0.2440
  -8.500  -0.3401   0.10581   0.09897  -0.0241   1.0000   0.2534
  -8.250  -0.3398   0.10315   0.09638  -0.0237   1.0000   0.2600
  -8.000  -0.3477   0.10207   0.09542  -0.0231   1.0000   0.2703
  -7.750  -0.3316   0.09784   0.09121  -0.0218   1.0000   0.2799
  -7.500  -0.3367   0.09584   0.08934  -0.0208   1.0000   0.2888
  -7.250  -0.3447   0.09467   0.08830  -0.0193   1.0000   0.2990
  -7.000  -0.3326   0.09093   0.08459  -0.0178   1.0000   0.3078
  -6.750  -0.3577   0.09091   0.08479  -0.0151   1.0000   0.3157
  -6.500  -0.3424   0.08707   0.08096  -0.0136   1.0000   0.3238
  -5.500  -0.3928   0.05400   0.04755  -0.0587   1.0000   0.1258
  -5.250  -0.3675   0.04684   0.03987  -0.0654   1.0000   0.1160
  -5.000  -0.3358   0.04152   0.03381  -0.0706   1.0000   0.1111
  -4.750  -0.3061   0.03753   0.02929  -0.0733   1.0000   0.1092
  -4.500  -0.2746   0.03405   0.02526  -0.0754   1.0000   0.1072
  -4.250  -0.2437   0.03134   0.02202  -0.0765   1.0000   0.1070
  -4.000  -0.2144   0.02927   0.01952  -0.0769   1.0000   0.1096
  -3.750  -0.1873   0.02758   0.01764  -0.0769   1.0000   0.1170
  -3.500  -0.1609   0.02627   0.01613  -0.0764   1.0000   0.1267
  -3.250  -0.1362   0.02492   0.01481  -0.0756   1.0000   0.1399
  -3.000  -0.1062   0.02338   0.01356  -0.0764   1.0000   0.1805
  -2.750  -0.0833   0.02285   0.01487  -0.0739   1.0000   0.5006
  -2.500  -0.0809   0.02410   0.01634  -0.0670   1.0000   0.5702
  -2.250  -0.0851   0.02508   0.01757  -0.0584   1.0000   0.6298
  -2.000  -0.0751   0.02516   0.01756  -0.0543   1.0000   0.6697
  -1.750  -0.0584   0.02494   0.01719  -0.0524   1.0000   0.6986
  -1.500  -0.0403   0.02472   0.01681  -0.0510   1.0000   0.7267
  -1.250  -0.0235   0.02450   0.01647  -0.0495   1.0000   0.7530
  -1.000  -0.0062   0.02429   0.01615  -0.0482   1.0000   0.7799
  -0.750   0.0112   0.02410   0.01585  -0.0471   1.0000   0.8079
  -0.500   0.0279   0.02392   0.01561  -0.0460   1.0000   0.8383
  -0.250   0.0431   0.02370   0.01538  -0.0447   1.0000   0.8738
   0.000   0.0603   0.02336   0.01513  -0.0443   1.0000   0.9321
   0.250   0.0919   0.02359   0.01522  -0.0489   1.0000   1.0000
   0.500   0.1330   0.02441   0.01575  -0.0550   1.0000   1.0000
   0.750   0.1685   0.02532   0.01640  -0.0596   1.0000   1.0000
   1.000   0.2285   0.02679   0.01759  -0.0684   0.9853   1.0000
   1.250   0.2862   0.02821   0.01878  -0.0760   0.9698   1.0000
   1.500   0.3354   0.02939   0.01979  -0.0817   0.9532   1.0000
   1.750   0.3798   0.03045   0.02074  -0.0862   0.9360   1.0000
   2.000   0.4234   0.03146   0.02167  -0.0903   0.9187   1.0000
   2.250   0.4669   0.03240   0.02257  -0.0940   0.9014   1.0000
   2.500   0.5115   0.03324   0.02340  -0.0976   0.8844   1.0000
   2.750   0.5565   0.03397   0.02415  -0.1010   0.8674   1.0000
   3.000   0.5878   0.03472   0.02495  -0.1023   0.8480   1.0000
   3.250   0.6273   0.03529   0.02558  -0.1044   0.8295   1.0000
   3.500   0.6721   0.03563   0.02601  -0.1068   0.8119   1.0000
   3.750   0.7137   0.03586   0.02638  -0.1085   0.7936   1.0000
   4.000   0.7468   0.03621   0.02685  -0.1090   0.7731   1.0000
   4.250   0.7975   0.03569   0.02651  -0.1109   0.7547   1.0000
   4.500   0.8481   0.03470   0.02576  -0.1119   0.7363   1.0000
   4.750   0.8826   0.03426   0.02548  -0.1110   0.7134   1.0000
   5.000   0.9339   0.03240   0.02386  -0.1107   0.6920   1.0000
   5.250   0.9776   0.03069   0.02231  -0.1093   0.6661   1.0000
   5.500   1.0161   0.02923   0.02096  -0.1074   0.6367   1.0000
   5.750   1.0464   0.02843   0.02025  -0.1050   0.6026   1.0000
   6.000   1.0774   0.02762   0.01941  -0.1026   0.5645   1.0000
   6.250   1.1027   0.02736   0.01905  -0.0999   0.5205   1.0000
   6.500   1.1231   0.02764   0.01917  -0.0970   0.4697   1.0000
   6.750   1.1426   0.02829   0.01950  -0.0942   0.4154   1.0000
   7.000   1.1600   0.02954   0.02045  -0.0917   0.3637   1.0000
   7.250   1.1787   0.03106   0.02170  -0.0897   0.3211   1.0000
   7.500   1.2003   0.03273   0.02311  -0.0883   0.2884   1.0000
   7.750   1.2221   0.03470   0.02509  -0.0872   0.2633   1.0000
   8.000   1.2453   0.03662   0.02693  -0.0863   0.2424   1.0000
   8.250   1.2670   0.03889   0.02937  -0.0853   0.2261   1.0000
   8.500   1.2885   0.04129   0.03192  -0.0844   0.2121   1.0000
   8.750   1.3078   0.04368   0.03446  -0.0833   0.1986   1.0000
   9.000   1.3316   0.04649   0.03731  -0.0827   0.1876   1.0000
   9.250   1.3396   0.04953   0.04095  -0.0804   0.1782   1.0000
   9.500   1.3506   0.05282   0.04456  -0.0787   0.1691   1.0000
   9.750   1.3706   0.05607   0.04784  -0.0779   0.1593   1.0000
  10.000   1.3604   0.06021   0.05274  -0.0745   0.1545   1.0000
  10.250   1.3774   0.06368   0.05619  -0.0736   0.1451   1.0000
  10.500   1.3594   0.06847   0.06160  -0.0704   0.1432   1.0000
  10.750   1.3381   0.07342   0.06698  -0.0676   0.1419   1.0000
  11.000   1.3117   0.07847   0.07234  -0.0651   0.1420   1.0000
  11.250   1.2822   0.08376   0.07783  -0.0633   0.1430   1.0000
  11.500   1.2532   0.08986   0.08408  -0.0631   0.1442   1.0000
  11.750   1.2264   0.09682   0.09115  -0.0644   0.1453   1.0000
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