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FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 73-CL2-152 (fx73cl2152-il)
Reynolds number: 50,000
Max Cl/Cd: 32.64 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx73cl2152-il-50000-n5.txt
Download as CSV file: xf-fx73cl2152-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 73-CL2-152                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.1221   0.10425   0.09785  -0.0552   0.9515   0.0939
  -7.250  -0.1046   0.10038   0.09399  -0.0577   0.9345   0.0917
  -7.000  -0.0930   0.09638   0.09000  -0.0608   0.9152   0.0896
  -6.750  -0.0842   0.09222   0.08586  -0.0643   0.8955   0.0881
  -6.500  -0.0777   0.08883   0.08250  -0.0663   0.8717   0.0883
  -6.250  -0.0692   0.08527   0.07894  -0.0686   0.8500   0.0890
  -6.000  -0.0579   0.08111   0.07476  -0.0723   0.8297   0.0893
  -5.750  -0.0431   0.07613   0.06972  -0.0776   0.8103   0.0889
  -5.500  -0.0262   0.07038   0.06388  -0.0846   0.7917   0.0884
  -5.250  -0.0042   0.06447   0.05783  -0.0930   0.7738   0.0892
  -5.000   0.0231   0.05588   0.04899  -0.1072   0.7570   0.0914
  -4.750   0.0894   0.03962   0.03146  -0.1396   0.7433   0.0945
  -4.500   0.1392   0.03734   0.02890  -0.1457   0.7254   0.0988
  -4.250   0.2020   0.03344   0.02414  -0.1562   0.7084   0.1053
  -4.000   0.2458   0.03201   0.02241  -0.1602   0.6919   0.1104
  -3.750   0.2904   0.03040   0.02025  -0.1647   0.6761   0.1186
  -3.500   0.3265   0.02977   0.01952  -0.1666   0.6621   0.1250
  -3.250   0.3678   0.02893   0.01833  -0.1696   0.6500   0.1357
  -3.000   0.4036   0.02832   0.01748  -0.1716   0.6376   0.1483
  -2.750   0.4401   0.02795   0.01695  -0.1735   0.6276   0.1644
  -2.500   0.4742   0.02775   0.01672  -0.1749   0.6178   0.1843
  -2.250   0.5115   0.02763   0.01648  -0.1769   0.6098   0.2106
  -2.000   0.5444   0.02763   0.01640  -0.1781   0.6008   0.2386
  -1.750   0.5797   0.02775   0.01645  -0.1795   0.5935   0.2668
  -1.500   0.6123   0.02792   0.01652  -0.1806   0.5859   0.2962
  -1.250   0.6429   0.02811   0.01672  -0.1811   0.5789   0.3202
  -1.000   0.6773   0.02824   0.01674  -0.1822   0.5733   0.3430
  -0.750   0.7070   0.02841   0.01687  -0.1827   0.5672   0.3627
  -0.500   0.7366   0.02859   0.01699  -0.1831   0.5609   0.3818
  -0.250   0.7684   0.02876   0.01706  -0.1837   0.5555   0.4022
   0.000   0.8000   0.02897   0.01717  -0.1844   0.5507   0.4229
   0.250   0.8253   0.02930   0.01758  -0.1840   0.5449   0.4435
   0.500   0.8530   0.02961   0.01789  -0.1840   0.5398   0.4659
   0.750   0.8826   0.02988   0.01812  -0.1842   0.5353   0.4918
   1.000   0.9123   0.03021   0.01841  -0.1844   0.5310   0.5205
   1.250   0.9330   0.03071   0.01906  -0.1833   0.5257   0.5467
   1.750   0.9831   0.03150   0.01994  -0.1820   0.5166   0.6118
   2.000   1.0105   0.03180   0.02022  -0.1816   0.5131   0.6493
   2.250   1.0261   0.03243   0.02102  -0.1795   0.5083   0.6842
   2.500   1.0419   0.03297   0.02172  -0.1773   0.5035   0.7233
   2.750   1.0590   0.03335   0.02218  -0.1751   0.4994   0.7696
   3.000   1.0734   0.03349   0.02239  -0.1722   0.4960   0.8273
   3.250   1.0923   0.03347   0.02233  -0.1701   0.4930   1.0000
   3.500   1.1098   0.03480   0.02373  -0.1696   0.4876   1.0000
   3.750   1.1330   0.03586   0.02475  -0.1696   0.4827   1.0000
   4.000   1.1609   0.03670   0.02548  -0.1701   0.4787   1.0000
   4.250   1.1934   0.03733   0.02594  -0.1711   0.4753   1.0000
   4.500   1.2133   0.03848   0.02709  -0.1704   0.4712   1.0000
   4.750   1.2210   0.04014   0.02889  -0.1682   0.4660   1.0000
   5.000   1.2382   0.04139   0.03015  -0.1672   0.4617   1.0000
   5.250   1.2632   0.04226   0.03097  -0.1671   0.4581   1.0000
   5.500   1.2954   0.04283   0.03143  -0.1678   0.4552   1.0000
   5.750   1.2886   0.04527   0.03408  -0.1640   0.4499   1.0000
   6.000   1.2830   0.04770   0.03667  -0.1605   0.4446   1.0000
   6.250   1.2950   0.04926   0.03826  -0.1590   0.4407   1.0000
   6.500   1.3198   0.05018   0.03915  -0.1588   0.4377   1.0000
   6.750   1.3546   0.05061   0.03950  -0.1596   0.4354   1.0000
   7.000   1.2165   0.06175   0.05122  -0.1463   0.4231   1.0000
   7.250   1.2371   0.06289   0.05234  -0.1458   0.4198   1.0000
   7.500   1.2685   0.06315   0.05257  -0.1458   0.4176   1.0000
   8.000   1.1404   0.08450   0.07434  -0.1446   0.3961   1.0000
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