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FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX60-100 10.0% smoothed (fx60100sm-il)
Reynolds number: 200,000
Max Cl/Cd: 85.21 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60100sm-il-200000.txt
Download as CSV file: xf-fx60100sm-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3759   0.10095   0.09737  -0.0411   1.0000   0.0465
  -9.250  -0.3789   0.09754   0.09402  -0.0432   1.0000   0.0467
  -9.000  -0.3856   0.09235   0.08893  -0.0442   1.0000   0.0473
  -8.750  -0.3720   0.09022   0.08678  -0.0403   1.0000   0.0488
  -8.500  -0.3676   0.08809   0.08468  -0.0390   1.0000   0.0500
  -8.250  -0.3682   0.08577   0.08241  -0.0383   1.0000   0.0513
  -8.000  -0.3739   0.08345   0.08016  -0.0373   1.0000   0.0526
  -7.750  -0.3856   0.08139   0.07818  -0.0356   1.0000   0.0537
  -7.500  -0.4039   0.07973   0.07662  -0.0328   1.0000   0.0544
  -7.250  -0.4237   0.07810   0.07508  -0.0300   1.0000   0.0548
  -7.000  -0.4388   0.07516   0.07222  -0.0304   1.0000   0.0559
  -6.500  -0.4414   0.05553   0.05223  -0.0597   0.9964   0.0605
  -6.250  -0.4158   0.05411   0.05097  -0.0590   0.9937   0.0630
  -6.000  -0.3765   0.04564   0.04184  -0.0746   0.9875   0.0737
  -5.750  -0.3461   0.04320   0.03954  -0.0765   0.9844   0.0778
  -5.500  -0.3098   0.03895   0.03498  -0.0832   0.9801   0.0900
  -5.250  -0.2750   0.03587   0.03168  -0.0876   0.9753   0.1041
  -5.000  -0.2368   0.03328   0.02894  -0.0918   0.9719   0.1208
  -4.750  -0.1706   0.02313   0.01635  -0.0954   0.9715   0.0357
  -4.500  -0.1294   0.02099   0.01393  -0.0981   0.9695   0.0357
  -4.250  -0.0977   0.01918   0.01198  -0.0989   0.9640   0.0355
  -4.000  -0.0603   0.01761   0.01035  -0.1007   0.9602   0.0361
  -3.750  -0.0194   0.01606   0.00883  -0.1036   0.9574   0.0388
  -3.500   0.0234   0.01530   0.00804  -0.1067   0.9546   0.0457
  -3.250   0.0571   0.01449   0.00715  -0.1080   0.9477   0.0559
  -3.000   0.1002   0.01260   0.00654  -0.1123   0.9448   0.3737
  -2.750   0.1433   0.01258   0.00659  -0.1151   0.9417   0.4444
  -2.500   0.1759   0.01269   0.00675  -0.1157   0.9346   0.4864
  -2.250   0.2144   0.01265   0.00669  -0.1174   0.9298   0.5129
  -2.000   0.2554   0.01247   0.00647  -0.1197   0.9265   0.5303
  -1.750   0.2848   0.01239   0.00637  -0.1197   0.9178   0.5453
  -1.500   0.3222   0.01219   0.00614  -0.1212   0.9130   0.5611
  -1.250   0.3519   0.01207   0.00603  -0.1212   0.9046   0.5750
  -1.000   0.3860   0.01186   0.00582  -0.1219   0.8985   0.5892
  -0.750   0.4143   0.01174   0.00570  -0.1217   0.8892   0.6024
  -0.500   0.4467   0.01152   0.00548  -0.1220   0.8827   0.6164
  -0.250   0.4735   0.01141   0.00540  -0.1214   0.8719   0.6301
   0.000   0.5017   0.01127   0.00528  -0.1210   0.8623   0.6445
   0.250   0.5310   0.01109   0.00510  -0.1207   0.8536   0.6596
   0.500   0.5574   0.01098   0.00504  -0.1200   0.8417   0.6752
   0.750   0.5842   0.01086   0.00496  -0.1193   0.8298   0.6920
   1.000   0.6111   0.01074   0.00488  -0.1186   0.8176   0.7103
   1.250   0.6376   0.01061   0.00480  -0.1179   0.8050   0.7295
   1.500   0.6637   0.01049   0.00474  -0.1170   0.7916   0.7512
   1.750   0.6892   0.01037   0.00469  -0.1161   0.7774   0.7762
   2.000   0.7134   0.01024   0.00464  -0.1148   0.7622   0.8076
   2.250   0.7353   0.01005   0.00456  -0.1130   0.7459   0.8553
   2.500   0.7605   0.00982   0.00442  -0.1119   0.7283   1.0000
   2.750   0.7897   0.00992   0.00440  -0.1120   0.7097   1.0000
   3.000   0.8172   0.01004   0.00443  -0.1117   0.6876   1.0000
   3.250   0.8441   0.01019   0.00445  -0.1113   0.6642   1.0000
   3.500   0.8704   0.01037   0.00456  -0.1108   0.6388   1.0000
   3.750   0.8964   0.01058   0.00468  -0.1103   0.6138   1.0000
   4.000   0.9222   0.01084   0.00483  -0.1097   0.5884   1.0000
   4.250   0.9475   0.01112   0.00501  -0.1091   0.5623   1.0000
   4.500   0.9726   0.01143   0.00525  -0.1085   0.5350   1.0000
   4.750   0.9973   0.01176   0.00550  -0.1078   0.5073   1.0000
   5.000   1.0215   0.01214   0.00578  -0.1071   0.4774   1.0000
   5.250   1.0450   0.01255   0.00609  -0.1063   0.4451   1.0000
   5.500   1.0683   0.01300   0.00646  -0.1055   0.4110   1.0000
   5.750   1.0905   0.01354   0.00685  -0.1045   0.3742   1.0000
   6.000   1.1117   0.01417   0.00731  -0.1035   0.3307   1.0000
   6.250   1.1317   0.01494   0.00786  -0.1023   0.2806   1.0000
   6.500   1.1499   0.01592   0.00856  -0.1010   0.2301   1.0000
   6.750   1.1680   0.01698   0.00936  -0.0997   0.1891   1.0000
   7.000   1.1865   0.01801   0.01022  -0.0984   0.1621   1.0000
   7.250   1.2052   0.01903   0.01112  -0.0971   0.1445   1.0000
   7.500   1.2238   0.02005   0.01206  -0.0958   0.1319   1.0000
   7.750   1.2443   0.02087   0.01295  -0.0948   0.1219   1.0000
   8.000   1.2636   0.02184   0.01395  -0.0936   0.1134   1.0000
   8.250   1.2818   0.02297   0.01501  -0.0923   0.1060   1.0000
   8.500   1.3020   0.02379   0.01597  -0.0912   0.0992   1.0000
   8.750   1.3196   0.02506   0.01716  -0.0900   0.0924   1.0000
   9.000   1.3390   0.02576   0.01808  -0.0887   0.0862   1.0000
   9.250   1.3556   0.02699   0.01925  -0.0875   0.0798   1.0000
   9.500   1.3727   0.02774   0.02021  -0.0860   0.0739   1.0000
   9.750   1.3868   0.02884   0.02129  -0.0844   0.0679   1.0000
  10.000   1.3998   0.02976   0.02241  -0.0824   0.0621   1.0000
  10.250   1.4091   0.03077   0.02343  -0.0801   0.0565   1.0000
  10.500   1.4185   0.03192   0.02477  -0.0779   0.0505   1.0000
  10.750   1.4242   0.03323   0.02607  -0.0755   0.0452   1.0000
  11.000   1.4316   0.03460   0.02767  -0.0733   0.0398   1.0000
  11.250   1.4352   0.03626   0.02934  -0.0712   0.0357   1.0000
  11.500   1.4397   0.03839   0.03167  -0.0690   0.0320   1.0000
  11.750   1.4442   0.04012   0.03350  -0.0673   0.0291   1.0000
  12.000   1.4430   0.04298   0.03637  -0.0655   0.0267   1.0000
  12.250   1.4460   0.04526   0.03891  -0.0640   0.0249   1.0000
  12.500   1.4476   0.04781   0.04165  -0.0628   0.0233   1.0000
  12.750   1.4480   0.05054   0.04452  -0.0617   0.0221   1.0000
  13.000   1.4471   0.05351   0.04760  -0.0610   0.0212   1.0000
  13.250   1.4434   0.05721   0.05143  -0.0603   0.0204   1.0000
  13.500   1.4348   0.06223   0.05667  -0.0597   0.0198   1.0000
  13.750   1.4276   0.06642   0.06113  -0.0599   0.0195   1.0000
  14.000   1.4182   0.07115   0.06612  -0.0605   0.0192   1.0000
  14.250   1.4064   0.07644   0.07168  -0.0617   0.0190   1.0000
  14.500   1.3926   0.08228   0.07777  -0.0636   0.0189   1.0000
  14.750   1.3769   0.08876   0.08452  -0.0662   0.0188   1.0000
  15.000   1.3595   0.09593   0.09192  -0.0696   0.0188   1.0000
  15.250   1.3405   0.10381   0.10005  -0.0738   0.0188   1.0000
  15.500   1.3205   0.11244   0.10889  -0.0789   0.0189   1.0000
  15.750   1.2994   0.12185   0.11852  -0.0849   0.0190   1.0000
  16.000   1.2769   0.13216   0.12902  -0.0917   0.0192   1.0000
  16.250   1.2536   0.14337   0.14040  -0.0994   0.0195   1.0000
  16.500   1.2272   0.15618   0.15334  -0.1081   0.0198   1.0000
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