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FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 73-CL2-152 (fx73cl2152-il)
Reynolds number: 100,000
Max Cl/Cd: 41.31 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx73cl2152-il-100000.txt
Download as CSV file: xf-fx73cl2152-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1993   0.13423   0.12948  -0.0291   1.0000   0.1001
  -9.750  -0.1993   0.13240   0.12771  -0.0287   1.0000   0.1034
  -9.500  -0.2187   0.13276   0.12817  -0.0298   1.0000   0.1059
  -9.000  -0.2078   0.12655   0.12211  -0.0272   1.0000   0.1086
  -8.750  -0.2039   0.12457   0.12021  -0.0254   1.0000   0.1105
  -8.500  -0.2065   0.12322   0.11896  -0.0238   1.0000   0.1125
  -8.250  -0.1964   0.12081   0.11659  -0.0298   0.9957   0.1176
  -8.000  -0.1797   0.11652   0.11232  -0.0389   0.9873   0.1199
  -7.750  -0.1331   0.11090   0.10666  -0.0417   0.9810   0.1240
  -7.500   0.0454   0.08905   0.08499  -0.0696   0.9133   0.1407
  -7.250   0.0335   0.08717   0.08313  -0.0765   0.8953   0.1471
  -7.000   0.0664   0.08053   0.07647  -0.0783   0.8786   0.1494
  -6.750   0.1073   0.07545   0.07131  -0.0810   0.8558   0.1556
  -6.500   0.0869   0.07411   0.06991  -0.0909   0.8307   0.1634
  -6.250   0.0171   0.08591   0.08169  -0.0731   0.8884   0.1530
  -6.000   0.0176   0.08401   0.07976  -0.0817   0.8607   0.1628
  -5.750   0.0645   0.07774   0.07340  -0.0851   0.8395   0.1664
  -5.500   0.1244   0.07260   0.06802  -0.0941   0.8120   0.1747
  -5.250   0.1691   0.06712   0.06225  -0.1092   0.7795   0.1832
  -5.000   0.1826   0.04299   0.03755  -0.1514   0.7675   0.1200
  -4.750   0.2488   0.03253   0.02616  -0.1722   0.7416   0.1139
  -4.500   0.3195   0.02698   0.01934  -0.1868   0.7173   0.1180
  -4.250   0.3652   0.02510   0.01699  -0.1916   0.6974   0.1216
  -4.000   0.4033   0.02435   0.01597  -0.1940   0.6807   0.1274
  -3.750   0.4435   0.02333   0.01450  -0.1970   0.6667   0.1349
  -3.500   0.4776   0.02287   0.01387  -0.1983   0.6542   0.1428
  -3.250   0.5102   0.02246   0.01336  -0.1994   0.6434   0.1536
  -3.000   0.5452   0.02212   0.01286  -0.2008   0.6342   0.1685
  -2.750   0.5770   0.02201   0.01275  -0.2016   0.6258   0.1894
  -2.500   0.6099   0.02191   0.01260  -0.2026   0.6175   0.2207
  -2.250   0.6443   0.02210   0.01266  -0.2038   0.6105   0.2570
  -2.000   0.6702   0.02225   0.01298  -0.2034   0.6030   0.2824
  -1.750   0.6999   0.02250   0.01320  -0.2036   0.5967   0.3073
  -1.500   0.7324   0.02284   0.01341  -0.2044   0.5916   0.3320
  -1.250   0.7574   0.02308   0.01376  -0.2038   0.5855   0.3535
  -1.000   0.7852   0.02331   0.01399  -0.2037   0.5795   0.3748
  -0.750   0.8159   0.02350   0.01411  -0.2041   0.5745   0.3943
  -0.500   0.8451   0.02375   0.01434  -0.2043   0.5699   0.4122
  -0.250   0.8705   0.02395   0.01464  -0.2038   0.5646   0.4299
   0.000   0.8982   0.02416   0.01486  -0.2037   0.5595   0.4497
   0.250   0.9282   0.02440   0.01506  -0.2040   0.5550   0.4722
   0.500   0.9581   0.02478   0.01540  -0.2043   0.5508   0.4980
   0.750   0.9813   0.02511   0.01591  -0.2034   0.5460   0.5222
   1.000   1.0060   0.02544   0.01636  -0.2027   0.5411   0.5497
   1.250   1.0336   0.02577   0.01670  -0.2024   0.5368   0.5822
   1.500   1.0629   0.02619   0.01710  -0.2024   0.5332   0.6182
   1.750   1.0831   0.02670   0.01780  -0.2009   0.5292   0.6505
   2.000   1.1027   0.02716   0.01844  -0.1992   0.5245   0.6851
   2.250   1.1237   0.02755   0.01891  -0.1976   0.5202   0.7230
   2.500   1.1456   0.02786   0.01926  -0.1961   0.5165   0.7646
   2.750   1.1654   0.02821   0.01961  -0.1940   0.5134   0.8095
   3.000   1.1718   0.02865   0.02027  -0.1898   0.5099   0.8597
   3.250   1.1742   0.02884   0.02069  -0.1849   0.5057   1.0000
   3.500   1.2118   0.02965   0.02140  -0.1877   0.5008   1.0000
   3.750   1.2474   0.03030   0.02188  -0.1896   0.4967   1.0000
   4.000   1.2828   0.03108   0.02247  -0.1912   0.4935   1.0000
   4.250   1.2975   0.03240   0.02397  -0.1897   0.4891   1.0000
   4.500   1.3154   0.03361   0.02526  -0.1886   0.4845   1.0000
   4.750   1.3405   0.03444   0.02606  -0.1884   0.4803   1.0000
   5.000   1.3710   0.03503   0.02655  -0.1890   0.4768   1.0000
   5.250   1.4049   0.03578   0.02715  -0.1900   0.4736   1.0000
   5.500   1.4016   0.03787   0.02957  -0.1860   0.4683   1.0000
   5.750   1.4124   0.03948   0.03131  -0.1839   0.4638   1.0000
   6.000   1.4346   0.04051   0.03235  -0.1833   0.4602   1.0000
   6.250   1.4659   0.04109   0.03286  -0.1839   0.4573   1.0000
   6.500   1.5003   0.04179   0.03343  -0.1849   0.4545   1.0000
   6.750   1.4613   0.04607   0.03820  -0.1769   0.4480   1.0000
   7.000   1.4538   0.04878   0.04107  -0.1730   0.4431   1.0000
   7.250   1.4751   0.04987   0.04218  -0.1724   0.4399   1.0000
   7.500   1.5152   0.04997   0.04220  -0.1738   0.4376   1.0000
   7.750   1.5574   0.05027   0.04241  -0.1756   0.4355   1.0000
   8.000   1.1836   0.08772   0.08082  -0.1553   0.4165   1.0000
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