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FX 72-LS-160 (fx72ls160-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 72-LS-160 (fx72ls160-il)
Reynolds number: 500,000
Max Cl/Cd: 125.74 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx72ls160-il-500000-n5.txt
Download as CSV file: xf-fx72ls160-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.2157   0.08874   0.08422  -0.1403   0.6454   0.0124
  -9.500   0.2236   0.08642   0.08191  -0.1412   0.6446   0.0126
  -9.250   0.2303   0.08384   0.07936  -0.1423   0.6437   0.0127
  -9.000   0.2373   0.08141   0.07695  -0.1433   0.6427   0.0128
  -8.500   0.2358   0.07331   0.06891  -0.1459   0.6407   0.0093
  -8.250   0.2428   0.07118   0.06679  -0.1467   0.6394   0.0091
  -8.000   0.2475   0.06864   0.06428  -0.1477   0.6382   0.0090
  -7.750   0.2530   0.06637   0.06202  -0.1485   0.6370   0.0088
  -7.500   0.2521   0.06312   0.05881  -0.1495   0.6359   0.0088
  -7.250   0.2512   0.06017   0.05589  -0.1504   0.6349   0.0087
  -7.000   0.2433   0.05714   0.05290  -0.1509   0.6338   0.0087
  -6.500   0.1685   0.02215   0.01656  -0.1731   0.6317   0.0088
  -6.250   0.1912   0.02013   0.01410  -0.1737   0.6305   0.0090
  -6.000   0.2164   0.01889   0.01254  -0.1740   0.6292   0.0092
  -5.750   0.2428   0.01800   0.01141  -0.1743   0.6282   0.0094
  -5.500   0.2687   0.01693   0.01022  -0.1747   0.6272   0.0097
  -5.250   0.2958   0.01637   0.00958  -0.1751   0.6261   0.0101
  -5.000   0.3233   0.01584   0.00895  -0.1754   0.6249   0.0106
  -4.750   0.3510   0.01529   0.00829  -0.1757   0.6236   0.0109
  -4.500   0.3789   0.01476   0.00765  -0.1760   0.6223   0.0112
  -4.250   0.4070   0.01429   0.00708  -0.1763   0.6209   0.0115
  -4.000   0.4353   0.01390   0.00660  -0.1766   0.6197   0.0117
  -3.750   0.4636   0.01349   0.00613  -0.1769   0.6186   0.0121
  -3.500   0.4921   0.01312   0.00572  -0.1773   0.6175   0.0125
  -3.250   0.5208   0.01285   0.00541  -0.1777   0.6164   0.0130
  -3.000   0.5497   0.01264   0.00514  -0.1781   0.6152   0.0135
  -2.750   0.5786   0.01247   0.00491  -0.1785   0.6139   0.0140
  -2.500   0.6074   0.01231   0.00471  -0.1789   0.6127   0.0150
  -2.250   0.6360   0.01215   0.00455  -0.1793   0.6115   0.0161
  -2.000   0.6646   0.01203   0.00442  -0.1796   0.6103   0.0172
  -1.750   0.6934   0.01191   0.00431  -0.1800   0.6091   0.0189
  -1.500   0.7222   0.01179   0.00422  -0.1804   0.6078   0.0261
  -1.250   0.7509   0.01168   0.00418  -0.1808   0.6065   0.0427
  -1.000   0.7796   0.01162   0.00416  -0.1812   0.6052   0.0571
  -0.750   0.8083   0.01157   0.00413  -0.1816   0.6038   0.0684
  -0.500   0.8370   0.01151   0.00411  -0.1821   0.6025   0.0841
  -0.250   0.8657   0.01146   0.00409  -0.1825   0.6011   0.1018
   0.000   0.8947   0.01138   0.00409  -0.1830   0.5999   0.1339
   0.250   0.9241   0.01125   0.00412  -0.1838   0.5987   0.2035
   0.500   0.9544   0.01103   0.00420  -0.1848   0.5975   0.3322
   0.750   0.9848   0.01074   0.00434  -0.1860   0.5963   0.4999
   1.000   1.0149   0.01042   0.00451  -0.1869   0.5951   0.6807
   1.250   1.0347   0.01024   0.00474  -0.1852   0.5936   0.8396
   1.500   1.0565   0.01029   0.00484  -0.1839   0.5921   0.8835
   1.750   1.0765   0.01033   0.00491  -0.1823   0.5904   0.9151
   2.000   1.0932   0.01032   0.00494  -0.1799   0.5888   0.9424
   2.250   1.1107   0.01027   0.00490  -0.1778   0.5872   0.9770
   2.500   1.1414   0.01033   0.00492  -0.1787   0.5859   1.0000
   2.750   1.1704   0.01043   0.00499  -0.1793   0.5846   1.0000
   3.000   1.1994   0.01054   0.00506  -0.1799   0.5833   1.0000
   3.250   1.2286   0.01067   0.00514  -0.1805   0.5820   1.0000
   3.500   1.2562   0.01080   0.00529  -0.1809   0.5805   1.0000
   3.750   1.2833   0.01093   0.00544  -0.1812   0.5788   1.0000
   4.000   1.3104   0.01106   0.00559  -0.1815   0.5769   1.0000
   4.250   1.3375   0.01120   0.00574  -0.1817   0.5751   1.0000
   4.500   1.3645   0.01133   0.00589  -0.1820   0.5734   1.0000
   4.750   1.3914   0.01146   0.00603  -0.1823   0.5718   1.0000
   5.000   1.4183   0.01159   0.00616  -0.1825   0.5702   1.0000
   5.250   1.4454   0.01172   0.00627  -0.1828   0.5686   1.0000
   5.500   1.4727   0.01185   0.00640  -0.1831   0.5670   1.0000
   5.750   1.4979   0.01203   0.00661  -0.1831   0.5652   1.0000
   6.000   1.5221   0.01222   0.00686  -0.1829   0.5633   1.0000
   6.250   1.5460   0.01240   0.00710  -0.1827   0.5612   1.0000
   6.500   1.5695   0.01258   0.00732  -0.1824   0.5589   1.0000
   6.750   1.5925   0.01273   0.00749  -0.1819   0.5562   1.0000
   7.000   1.6158   0.01285   0.00763  -0.1815   0.5533   1.0000
   7.250   1.6369   0.01302   0.00781  -0.1807   0.5504   1.0000
   7.500   1.6528   0.01327   0.00815  -0.1790   0.5470   1.0000
   7.750   1.6693   0.01353   0.00846  -0.1774   0.5432   1.0000
   8.000   1.6864   0.01375   0.00870  -0.1759   0.5392   1.0000
   8.250   1.7002   0.01407   0.00904  -0.1740   0.5338   1.0000
   8.500   1.7117   0.01450   0.00953  -0.1718   0.5281   1.0000
   8.750   1.7232   0.01495   0.00995  -0.1696   0.5216   1.0000
   9.000   1.7305   0.01563   0.01072  -0.1670   0.5143   1.0000
   9.250   1.7356   0.01645   0.01152  -0.1641   0.5056   1.0000
   9.500   1.7374   0.01756   0.01267  -0.1611   0.4951   1.0000
   9.750   1.7401   0.01878   0.01391  -0.1584   0.4857   1.0000
  10.000   1.7400   0.02027   0.01539  -0.1556   0.4760   1.0000
  10.250   1.7422   0.02178   0.01695  -0.1532   0.4663   1.0000
  10.500   1.7408   0.02360   0.01877  -0.1506   0.4556   1.0000
  10.750   1.7316   0.02602   0.02118  -0.1474   0.4403   1.0000
  11.000   1.7203   0.02872   0.02385  -0.1441   0.4234   1.0000
  11.250   1.7022   0.03205   0.02711  -0.1405   0.4026   1.0000
  11.500   1.6828   0.03570   0.03068  -0.1370   0.3812   1.0000
  11.750   1.6612   0.03973   0.03460  -0.1336   0.3576   1.0000
  12.000   1.6439   0.04359   0.03837  -0.1308   0.3367   1.0000
  12.250   1.6302   0.04730   0.04199  -0.1284   0.3149   1.0000
  12.500   1.6179   0.05103   0.04563  -0.1264   0.2945   1.0000
  12.750   1.6068   0.05475   0.04926  -0.1245   0.2741   1.0000
  13.000   1.6009   0.05805   0.05250  -0.1231   0.2561   1.0000
  13.250   1.5961   0.06133   0.05573  -0.1219   0.2392   1.0000
  13.500   1.5927   0.06451   0.05885  -0.1208   0.2225   1.0000
  13.750   1.5899   0.06771   0.06200  -0.1199   0.2069   1.0000
  14.000   1.5879   0.07086   0.06510  -0.1191   0.1913   1.0000
  14.250   1.5866   0.07401   0.06820  -0.1184   0.1766   1.0000
  14.500   1.5854   0.07718   0.07132  -0.1178   0.1620   1.0000
  14.750   1.5846   0.08034   0.07443  -0.1172   0.1471   1.0000
  15.000   1.5839   0.08355   0.07760  -0.1168   0.1339   1.0000
  15.250   1.5849   0.08657   0.08058  -0.1165   0.1215   1.0000
  15.500   1.5857   0.08968   0.08367  -0.1162   0.1103   1.0000
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