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FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 73-CL2-152 (fx73cl2152-il)
Reynolds number: 200,000
Max Cl/Cd: 66.32 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx73cl2152-il-200000.txt
Download as CSV file: xf-fx73cl2152-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.0407   0.09377   0.09044  -0.0687   0.9562   0.0804
  -7.500  -0.0557   0.08836   0.08507  -0.0795   0.9412   0.0851
  -7.250  -0.0258   0.08529   0.08200  -0.0783   0.9285   0.0860
  -7.000  -0.0025   0.08266   0.07938  -0.0782   0.9097   0.0875
  -6.750   0.0170   0.07967   0.07637  -0.0803   0.8823   0.0910
  -6.500  -0.0562   0.03738   0.03313  -0.1410   0.8630   0.0672
  -6.250   0.0013   0.02991   0.02512  -0.1543   0.8414   0.0664
  -6.000   0.1025   0.02365   0.01789  -0.1743   0.8036   0.0687
  -5.750   0.1991   0.02127   0.01474  -0.1894   0.7339   0.0712
  -5.500   0.2398   0.02030   0.01312  -0.1927   0.6847   0.0731
  -5.250   0.2732   0.01975   0.01198  -0.1942   0.6528   0.0753
  -5.000   0.3025   0.01891   0.01093  -0.1949   0.6304   0.0775
  -4.750   0.3320   0.01847   0.01030  -0.1954   0.6125   0.0797
  -4.500   0.3620   0.01804   0.00967  -0.1958   0.5975   0.0824
  -4.250   0.3931   0.01760   0.00902  -0.1965   0.5856   0.0858
  -4.000   0.4235   0.01726   0.00866  -0.1971   0.5753   0.0899
  -3.750   0.4551   0.01702   0.00825  -0.1978   0.5666   0.0944
  -3.500   0.4866   0.01664   0.00790  -0.1987   0.5585   0.1002
  -3.250   0.5204   0.01649   0.00762  -0.1999   0.5517   0.1090
  -3.000   0.5519   0.01624   0.00742  -0.2006   0.5448   0.1209
  -2.750   0.5846   0.01606   0.00729  -0.2017   0.5383   0.1429
  -2.500   0.6194   0.01610   0.00730  -0.2031   0.5327   0.1827
  -2.250   0.6499   0.01619   0.00743  -0.2036   0.5276   0.2124
  -2.000   0.6801   0.01633   0.00753  -0.2039   0.5226   0.2340
  -1.750   0.7106   0.01646   0.00762  -0.2044   0.5180   0.2521
  -1.500   0.7425   0.01667   0.00775  -0.2051   0.5136   0.2687
  -1.250   0.7721   0.01677   0.00787  -0.2053   0.5093   0.2845
  -1.000   0.8015   0.01687   0.00798  -0.2055   0.5051   0.3008
  -0.750   0.8313   0.01701   0.00812  -0.2058   0.5011   0.3199
  -0.500   0.8615   0.01718   0.00825  -0.2061   0.4972   0.3393
  -0.250   0.8937   0.01746   0.00844  -0.2069   0.4934   0.3573
   0.000   0.9220   0.01751   0.00861  -0.2069   0.4898   0.3744
   0.250   0.9508   0.01759   0.00876  -0.2069   0.4859   0.3940
   0.500   0.9802   0.01771   0.00892  -0.2071   0.4822   0.4167
   0.750   1.0102   0.01785   0.00909  -0.2074   0.4788   0.4417
   1.000   1.0408   0.01808   0.00934  -0.2079   0.4756   0.4698
   1.250   1.0708   0.01838   0.00968  -0.2082   0.4723   0.5009
   1.500   1.0974   0.01851   0.00996  -0.2078   0.4689   0.5307
   1.750   1.1251   0.01869   0.01024  -0.2076   0.4654   0.5632
   2.000   1.1532   0.01890   0.01051  -0.2075   0.4621   0.5959
   2.250   1.1813   0.01911   0.01076  -0.2074   0.4590   0.6274
   2.500   1.2106   0.01942   0.01107  -0.2075   0.4559   0.6609
   2.750   1.2376   0.01977   0.01149  -0.2072   0.4528   0.6944
   3.000   1.2613   0.01995   0.01184  -0.2061   0.4497   0.7263
   3.250   1.2855   0.02016   0.01216  -0.2052   0.4465   0.7610
   3.500   1.3088   0.02034   0.01243  -0.2040   0.4434   0.7994
   3.750   1.3290   0.02046   0.01263  -0.2022   0.4406   0.8452
   4.000   1.3391   0.02034   0.01259  -0.1981   0.4383   1.0000
   4.250   1.3740   0.02101   0.01310  -0.1998   0.4351   1.0000
   4.500   1.3998   0.02131   0.01348  -0.1995   0.4319   1.0000
   4.750   1.4258   0.02166   0.01387  -0.1992   0.4282   1.0000
   5.000   1.4529   0.02201   0.01421  -0.1992   0.4248   1.0000
   5.250   1.4812   0.02237   0.01454  -0.1993   0.4218   1.0000
   5.500   1.5108   0.02278   0.01486  -0.1997   0.4190   1.0000
   5.750   1.5410   0.02347   0.01547  -0.2003   0.4161   1.0000
   6.000   1.5627   0.02386   0.01600  -0.1992   0.4130   1.0000
   6.250   1.5855   0.02428   0.01651  -0.1983   0.4094   1.0000
   6.500   1.6099   0.02466   0.01692  -0.1977   0.4059   1.0000
   6.750   1.6365   0.02499   0.01723  -0.1975   0.4028   1.0000
   7.000   1.6653   0.02540   0.01757  -0.1977   0.4001   1.0000
   7.250   1.6932   0.02611   0.01826  -0.1979   0.3972   1.0000
   7.500   1.7116   0.02662   0.01894  -0.1963   0.3940   1.0000
   7.750   1.7320   0.02715   0.01959  -0.1950   0.3905   1.0000
   8.000   1.7545   0.02758   0.02008  -0.1941   0.3872   1.0000
   8.250   1.7800   0.02792   0.02041  -0.1938   0.3843   1.0000
   8.500   1.8086   0.02830   0.02075  -0.1940   0.3816   1.0000
   8.750   1.8342   0.02905   0.02151  -0.1938   0.3789   1.0000
   9.000   1.8483   0.02973   0.02241  -0.1915   0.3756   1.0000
   9.250   1.8653   0.03036   0.02318  -0.1898   0.3722   1.0000
   9.500   1.8857   0.03080   0.02369  -0.1886   0.3690   1.0000
   9.750   1.9112   0.03094   0.02380  -0.1882   0.3658   1.0000
  10.000   1.9419   0.03095   0.02368  -0.1887   0.3616   1.0000
  10.250   1.9443   0.03135   0.02433  -0.1843   0.3564   1.0000
  10.500   1.9588   0.03133   0.02436  -0.1819   0.3514   1.0000
  10.750   1.9830   0.03126   0.02423  -0.1811   0.3477   1.0000
  11.000   2.0070   0.03161   0.02456  -0.1806   0.3444   1.0000
  11.250   2.0069   0.03238   0.02559  -0.1761   0.3405   1.0000
  11.500   2.0129   0.03291   0.02625  -0.1725   0.3368   1.0000
  11.750   2.0265   0.03317   0.02654  -0.1702   0.3332   1.0000
  12.000   2.0485   0.03327   0.02660  -0.1692   0.3299   1.0000
  12.250   2.0531   0.03406   0.02752  -0.1657   0.3264   1.0000
  12.500   2.0490   0.03510   0.02877  -0.1610   0.3225   1.0000
  12.750   2.0547   0.03579   0.02956  -0.1579   0.3186   1.0000
  13.000   2.0688   0.03613   0.02990  -0.1560   0.3149   1.0000
  13.250   2.0793   0.03685   0.03066  -0.1538   0.3111   1.0000
  13.500   2.0690   0.03855   0.03261  -0.1492   0.3069   1.0000
  13.750   2.0694   0.03978   0.03395  -0.1462   0.3026   1.0000
  14.000   2.0806   0.04043   0.03460  -0.1443   0.2984   1.0000
  14.250   2.0780   0.04213   0.03643  -0.1415   0.2941   1.0000
  14.500   2.0661   0.04457   0.03907  -0.1382   0.2892   1.0000
  14.750   2.0665   0.04622   0.04079  -0.1361   0.2843   1.0000
  15.000   2.0693   0.04790   0.04250  -0.1344   0.2794   1.0000
  15.250   2.0490   0.05178   0.04661  -0.1320   0.2741   1.0000
  15.500   2.0453   0.05432   0.04921  -0.1307   0.2685   1.0000
  15.750   2.0366   0.05764   0.05262  -0.1296   0.2628   1.0000
  16.000   2.0128   0.06300   0.05818  -0.1290   0.2564   1.0000
  16.250   2.0148   0.06540   0.06053  -0.1285   0.2496   1.0000
  16.500   1.9770   0.07340   0.06881  -0.1293   0.2424   1.0000
  16.750   1.9725   0.07695   0.07231  -0.1294   0.2345   1.0000
  17.000   1.9314   0.08632   0.08193  -0.1316   0.2257   1.0000
  17.250   1.9099   0.09292   0.08859  -0.1332   0.2162   1.0000
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