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FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 73-CL2-152 (fx73cl2152-il)
Reynolds number: 200,000
Max Cl/Cd: 74.88 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx73cl2152-il-200000-n5.txt
Download as CSV file: xf-fx73cl2152-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.1033   0.09271   0.08894  -0.0717   0.9332   0.0361
  -8.500  -0.1217   0.07941   0.07564  -0.0788   0.9051   0.0369
  -8.000  -0.2331   0.03131   0.02635  -0.1391   0.8610   0.0388
  -7.750  -0.1804   0.02737   0.02191  -0.1495   0.8413   0.0399
  -7.500  -0.1051   0.02364   0.01738  -0.1629   0.8132   0.0417
  -7.250  -0.0161   0.02204   0.01545  -0.1761   0.7640   0.0433
  -7.000   0.0442   0.02106   0.01394  -0.1837   0.7075   0.0449
  -6.750   0.0779   0.02035   0.01279  -0.1856   0.6665   0.0460
  -6.500   0.1071   0.01976   0.01181  -0.1865   0.6353   0.0470
  -6.250   0.1341   0.01931   0.01121  -0.1867   0.6110   0.0481
  -6.000   0.1617   0.01897   0.01072  -0.1870   0.5913   0.0494
  -5.750   0.1902   0.01858   0.01017  -0.1874   0.5750   0.0509
  -5.500   0.2194   0.01819   0.00958  -0.1879   0.5613   0.0525
  -5.250   0.2486   0.01780   0.00905  -0.1884   0.5495   0.0538
  -5.000   0.2783   0.01747   0.00866  -0.1890   0.5386   0.0554
  -4.750   0.3081   0.01721   0.00829  -0.1896   0.5295   0.0575
  -4.500   0.3384   0.01696   0.00791  -0.1901   0.5206   0.0599
  -4.000   0.4001   0.01649   0.00730  -0.1916   0.5054   0.0652
  -3.750   0.4314   0.01628   0.00701  -0.1924   0.4988   0.0686
  -3.250   0.4943   0.01596   0.00657  -0.1939   0.4883   0.0788
  -3.000   0.5260   0.01581   0.00638  -0.1947   0.4833   0.0865
  -2.750   0.5576   0.01567   0.00624  -0.1955   0.4787   0.0997
  -2.500   0.5889   0.01560   0.00616  -0.1963   0.4744   0.1219
  -2.250   0.6199   0.01554   0.00615  -0.1969   0.4702   0.1488
  -2.000   0.6502   0.01553   0.00617  -0.1973   0.4659   0.1713
  -1.750   0.6800   0.01558   0.00620  -0.1976   0.4621   0.1898
  -1.500   0.7097   0.01566   0.00623  -0.1979   0.4587   0.2056
  -1.250   0.7393   0.01577   0.00628  -0.1981   0.4556   0.2207
  -1.000   0.7690   0.01587   0.00634  -0.1983   0.4525   0.2359
  -0.750   0.7986   0.01592   0.00644  -0.1986   0.4490   0.2541
  -0.500   0.8281   0.01599   0.00654  -0.1988   0.4456   0.2735
  -0.250   0.8576   0.01608   0.00664  -0.1990   0.4424   0.2889
   0.000   0.8868   0.01619   0.00672  -0.1992   0.4394   0.3021
   0.500   0.9455   0.01646   0.00696  -0.1995   0.4335   0.3341
   0.750   0.9744   0.01655   0.00711  -0.1996   0.4304   0.3518
   1.000   1.0031   0.01665   0.00726  -0.1997   0.4273   0.3721
   1.250   1.0316   0.01678   0.00742  -0.1997   0.4244   0.3938
   1.500   1.0601   0.01692   0.00759  -0.1997   0.4217   0.4163
   1.750   1.0887   0.01710   0.00777  -0.1998   0.4190   0.4410
   2.000   1.1178   0.01732   0.00799  -0.1999   0.4164   0.4668
   2.250   1.1456   0.01745   0.00822  -0.1998   0.4137   0.4930
   2.500   1.1734   0.01760   0.00846  -0.1997   0.4110   0.5207
   2.750   1.2009   0.01776   0.00871  -0.1995   0.4082   0.5486
   3.000   1.2282   0.01794   0.00894  -0.1992   0.4053   0.5765
   3.250   1.2552   0.01812   0.00917  -0.1990   0.4026   0.6044
   3.500   1.2824   0.01834   0.00941  -0.1987   0.4001   0.6339
   3.750   1.3100   0.01860   0.00969  -0.1986   0.3979   0.6640
   4.000   1.3357   0.01878   0.00999  -0.1980   0.3955   0.6951
   4.250   1.3606   0.01895   0.01028  -0.1973   0.3929   0.7280
   4.500   1.3843   0.01912   0.01056  -0.1963   0.3903   0.7634
   4.750   1.4062   0.01926   0.01080  -0.1950   0.3877   0.8052
   5.000   1.4219   0.01929   0.01094  -0.1922   0.3852   0.8722
   5.250   1.4405   0.01937   0.01103  -0.1902   0.3828   1.0000
   5.500   1.4678   0.01971   0.01130  -0.1902   0.3803   1.0000
   5.750   1.4936   0.02002   0.01164  -0.1898   0.3777   1.0000
   6.000   1.5187   0.02033   0.01200  -0.1893   0.3750   1.0000
   6.250   1.5435   0.02064   0.01236  -0.1888   0.3721   1.0000
   6.500   1.5682   0.02095   0.01270  -0.1883   0.3694   1.0000
   6.750   1.5926   0.02127   0.01303  -0.1876   0.3669   1.0000
   7.000   1.6171   0.02160   0.01334  -0.1871   0.3644   1.0000
   7.250   1.6422   0.02198   0.01367  -0.1866   0.3619   1.0000
   7.500   1.6637   0.02232   0.01414  -0.1855   0.3589   1.0000
   7.750   1.6855   0.02269   0.01459  -0.1845   0.3557   1.0000
   8.000   1.7072   0.02305   0.01502  -0.1834   0.3529   1.0000
   8.250   1.7283   0.02341   0.01542  -0.1823   0.3502   1.0000
   8.500   1.7495   0.02378   0.01580  -0.1811   0.3478   1.0000
   8.750   1.7715   0.02418   0.01618  -0.1802   0.3455   1.0000
   9.000   1.7894   0.02462   0.01674  -0.1785   0.3425   1.0000
   9.250   1.8065   0.02507   0.01731  -0.1767   0.3392   1.0000
   9.500   1.8239   0.02553   0.01786  -0.1750   0.3362   1.0000
   9.750   1.8415   0.02599   0.01838  -0.1734   0.3335   1.0000
  10.000   1.8594   0.02644   0.01886  -0.1718   0.3309   1.0000
  10.250   1.8742   0.02692   0.01936  -0.1697   0.3272   1.0000
  10.500   1.8834   0.02748   0.02009  -0.1668   0.3213   1.0000
  10.750   1.8931   0.02799   0.02062  -0.1640   0.3155   1.0000
  11.000   1.9033   0.02862   0.02129  -0.1614   0.3102   1.0000
  11.250   1.9135   0.02938   0.02217  -0.1590   0.3046   1.0000
  11.500   1.9236   0.03016   0.02301  -0.1566   0.3001   1.0000
  11.750   1.9337   0.03100   0.02386  -0.1543   0.2964   1.0000
  12.000   1.9432   0.03199   0.02502  -0.1521   0.2919   1.0000
  12.250   1.9512   0.03306   0.02618  -0.1499   0.2873   1.0000
  12.500   1.9580   0.03423   0.02740  -0.1476   0.2831   1.0000
  12.750   1.9641   0.03552   0.02878  -0.1453   0.2790   1.0000
  13.000   1.9689   0.03700   0.03039  -0.1432   0.2741   1.0000
  13.250   1.9717   0.03864   0.03211  -0.1410   0.2694   1.0000
  13.500   1.9733   0.04046   0.03397  -0.1390   0.2652   1.0000
  13.750   1.9742   0.04253   0.03621  -0.1372   0.2602   1.0000
  14.000   1.9724   0.04491   0.03869  -0.1354   0.2552   1.0000
  14.250   1.9689   0.04755   0.04136  -0.1339   0.2505   1.0000
  14.500   1.9647   0.05055   0.04454  -0.1327   0.2452   1.0000
  14.750   1.9571   0.05406   0.04817  -0.1318   0.2396   1.0000
  15.000   1.9477   0.05796   0.05214  -0.1312   0.2343   1.0000
  15.250   1.9362   0.06244   0.05679  -0.1311   0.2280   1.0000
  15.500   1.9210   0.06755   0.06198  -0.1313   0.2216   1.0000
  15.750   1.9044   0.07318   0.06777  -0.1319   0.2150   1.0000
  16.000   1.8840   0.07951   0.07420  -0.1330   0.2075   1.0000
  16.250   1.8632   0.08615   0.08097  -0.1344   0.1996   1.0000
  16.500   1.8404   0.09322   0.08810  -0.1361   0.1914   1.0000
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