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FX 72-LS-160 (fx72ls160-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: FX 72-LS-160 (fx72ls160-il)
Reynolds number: 1,000,000
Max Cl/Cd: 174.27 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx72ls160-il-1000000-n5.txt
Download as CSV file: xf-fx72ls160-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 72-LS-160                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.2030   0.09385   0.09004  -0.1401   0.6292   0.0080
 -10.250   0.2094   0.09100   0.08721  -0.1413   0.6287   0.0079
 -10.000   0.2101   0.08667   0.08289  -0.1427   0.6282   0.0068
  -9.750   0.2190   0.08454   0.08078  -0.1437   0.6275   0.0067
  -9.500   0.2258   0.08204   0.07830  -0.1447   0.6267   0.0066
  -9.250   0.2317   0.07940   0.07568  -0.1457   0.6258   0.0064
  -8.250  -0.0019   0.02292   0.01863  -0.1730   0.6224   0.0060
  -8.000   0.0158   0.02055   0.01595  -0.1736   0.6213   0.0062
  -7.750   0.0372   0.01891   0.01405  -0.1740   0.6202   0.0063
  -7.500   0.0609   0.01770   0.01263  -0.1742   0.6192   0.0065
  -7.250   0.0859   0.01675   0.01149  -0.1745   0.6180   0.0067
  -7.000   0.1119   0.01600   0.01059  -0.1747   0.6167   0.0068
  -6.750   0.1383   0.01535   0.00979  -0.1750   0.6154   0.0069
  -6.500   0.1652   0.01479   0.00909  -0.1752   0.6140   0.0070
  -6.250   0.1925   0.01429   0.00848  -0.1755   0.6129   0.0070
  -6.000   0.2197   0.01353   0.00760  -0.1759   0.6122   0.0072
  -5.750   0.2475   0.01297   0.00695  -0.1763   0.6114   0.0073
  -5.500   0.2758   0.01256   0.00648  -0.1767   0.6104   0.0075
  -5.250   0.3042   0.01221   0.00609  -0.1770   0.6093   0.0076
  -5.000   0.3328   0.01188   0.00571  -0.1774   0.6082   0.0078
  -4.750   0.3615   0.01160   0.00538  -0.1778   0.6071   0.0081
  -4.500   0.3903   0.01135   0.00509  -0.1782   0.6060   0.0084
  -4.250   0.4192   0.01112   0.00481  -0.1786   0.6049   0.0088
  -4.000   0.4481   0.01090   0.00454  -0.1789   0.6037   0.0091
  -3.750   0.4770   0.01070   0.00430  -0.1793   0.6024   0.0093
  -3.500   0.5059   0.01039   0.00394  -0.1798   0.6011   0.0097
  -3.250   0.5348   0.01015   0.00367  -0.1802   0.5998   0.0100
  -3.000   0.5637   0.00999   0.00348  -0.1806   0.5985   0.0104
  -2.750   0.5926   0.00987   0.00332  -0.1810   0.5972   0.0107
  -2.500   0.6220   0.00972   0.00317  -0.1815   0.5964   0.0111
  -2.250   0.6513   0.00960   0.00304  -0.1819   0.5956   0.0114
  -2.000   0.6806   0.00950   0.00294  -0.1824   0.5945   0.0118
  -1.750   0.7099   0.00938   0.00281  -0.1829   0.5934   0.0126
  -1.500   0.7393   0.00929   0.00271  -0.1833   0.5920   0.0134
  -1.250   0.7685   0.00922   0.00264  -0.1838   0.5906   0.0143
  -0.750   0.8270   0.00904   0.00254  -0.1848   0.5880   0.0388
  -0.500   0.8561   0.00898   0.00253  -0.1853   0.5867   0.0530
  -0.250   0.8850   0.00896   0.00252  -0.1857   0.5855   0.0637
   0.000   0.9138   0.00893   0.00253  -0.1862   0.5841   0.0777
   0.250   0.9426   0.00890   0.00255  -0.1866   0.5827   0.1010
   0.500   0.9718   0.00883   0.00258  -0.1872   0.5813   0.1447
   0.750   1.0016   0.00870   0.00263  -0.1880   0.5802   0.2115
   1.000   1.0315   0.00857   0.00269  -0.1888   0.5789   0.2932
   1.250   1.0626   0.00831   0.00279  -0.1901   0.5775   0.4466
   1.500   1.0936   0.00812   0.00289  -0.1912   0.5761   0.5703
   1.750   1.1251   0.00790   0.00301  -0.1924   0.5746   0.7153
   2.000   1.1509   0.00776   0.00319  -0.1921   0.5731   0.8564
   2.250   1.1755   0.00780   0.00329  -0.1916   0.5716   0.8917
   2.500   1.2002   0.00786   0.00336  -0.1911   0.5701   0.9108
   2.750   1.2240   0.00792   0.00342  -0.1904   0.5685   0.9261
   3.000   1.2442   0.00798   0.00349  -0.1889   0.5666   0.9447
   3.250   1.2564   0.00792   0.00350  -0.1855   0.5653   0.9704
   3.500   1.2828   0.00793   0.00352  -0.1855   0.5638   1.0000
   3.750   1.3122   0.00801   0.00361  -0.1862   0.5622   1.0000
   4.000   1.3413   0.00810   0.00370  -0.1869   0.5605   1.0000
   4.250   1.3701   0.00819   0.00380  -0.1875   0.5588   1.0000
   4.500   1.3985   0.00829   0.00390  -0.1880   0.5569   1.0000
   4.750   1.4264   0.00840   0.00400  -0.1884   0.5550   1.0000
   5.000   1.4537   0.00853   0.00411  -0.1888   0.5530   1.0000
   5.250   1.4808   0.00866   0.00424  -0.1891   0.5511   1.0000
   5.500   1.5086   0.00876   0.00437  -0.1895   0.5496   1.0000
   5.750   1.5360   0.00886   0.00450  -0.1899   0.5474   1.0000
   6.000   1.5624   0.00898   0.00464  -0.1901   0.5443   1.0000
   6.250   1.5876   0.00911   0.00478  -0.1900   0.5406   1.0000
   6.500   1.6111   0.00929   0.00494  -0.1896   0.5369   1.0000
   6.750   1.6363   0.00941   0.00510  -0.1896   0.5329   1.0000
   7.000   1.6589   0.00958   0.00528  -0.1891   0.5271   1.0000
   7.250   1.6762   0.00982   0.00549  -0.1875   0.5208   1.0000
   7.500   1.6964   0.01001   0.00572  -0.1865   0.5145   1.0000
   7.750   1.7091   0.01037   0.00604  -0.1842   0.5060   1.0000
   8.000   1.7251   0.01070   0.00637  -0.1825   0.4968   1.0000
   8.250   1.7341   0.01122   0.00687  -0.1797   0.4846   1.0000
   8.500   1.7402   0.01190   0.00751  -0.1765   0.4722   1.0000
   8.750   1.7442   0.01273   0.00831  -0.1732   0.4598   1.0000
   9.000   1.7513   0.01355   0.00912  -0.1706   0.4489   1.0000
   9.250   1.7539   0.01464   0.01021  -0.1675   0.4369   1.0000
   9.500   1.7448   0.01648   0.01200  -0.1631   0.4187   1.0000
   9.750   1.7278   0.01908   0.01453  -0.1583   0.3977   1.0000
  10.000   1.7050   0.02236   0.01773  -0.1534   0.3737   1.0000
  10.250   1.6813   0.02593   0.02122  -0.1487   0.3524   1.0000
  10.500   1.6662   0.02900   0.02425  -0.1451   0.3349   1.0000
  10.750   1.6441   0.03276   0.02792  -0.1412   0.3110   1.0000
  11.000   1.6316   0.03597   0.03106  -0.1383   0.2930   1.0000
  11.250   1.6205   0.03919   0.03421  -0.1357   0.2746   1.0000
  11.500   1.6119   0.04231   0.03725  -0.1335   0.2556   1.0000
  11.750   1.6055   0.04532   0.04019  -0.1316   0.2364   1.0000
  12.000   1.5963   0.04870   0.04348  -0.1296   0.2162   1.0000
  12.250   1.5940   0.05150   0.04619  -0.1281   0.1994   1.0000
  12.500   1.5914   0.05442   0.04906  -0.1268   0.1839   1.0000
  12.750   1.5910   0.05713   0.05170  -0.1257   0.1683   1.0000
  13.000   1.5910   0.05990   0.05442  -0.1247   0.1545   1.0000
  13.250   1.5918   0.06263   0.05709  -0.1238   0.1408   1.0000
  13.500   1.5939   0.06524   0.05965  -0.1230   0.1278   1.0000
  13.750   1.5951   0.06804   0.06242  -0.1222   0.1168   1.0000
  14.000   1.5977   0.07067   0.06501  -0.1216   0.1054   1.0000
  14.250   1.5982   0.07363   0.06790  -0.1210   0.0924   1.0000
  14.500   1.6020   0.07624   0.07051  -0.1206   0.0852   1.0000
  14.750   1.6052   0.07891   0.07314  -0.1201   0.0758   1.0000
  15.000   1.6073   0.08178   0.07598  -0.1198   0.0666   1.0000
  15.250   1.6092   0.08471   0.07888  -0.1194   0.0569   1.0000
  15.500   1.6130   0.08741   0.08155  -0.1192   0.0494   1.0000
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