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FX 72-LS-160 (fx72ls160-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 72-LS-160 (fx72ls160-il)
Reynolds number: 1,000,000
Max Cl/Cd: 175.13 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx72ls160-il-1000000.txt
Download as CSV file: xf-fx72ls160-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.2339   0.08603   0.08260  -0.1315   0.6478   0.0106
 -10.250   0.2404   0.08313   0.07970  -0.1326   0.6464   0.0109
 -10.000   0.2468   0.08019   0.07677  -0.1336   0.6460   0.0111
  -9.750   0.2529   0.07718   0.07377  -0.1347   0.6454   0.0114
  -9.500   0.2549   0.07351   0.07013  -0.1360   0.6449   0.0117
  -9.250   0.2558   0.06971   0.06635  -0.1375   0.6442   0.0118
  -9.000   0.2597   0.06641   0.06306  -0.1386   0.6434   0.0119
  -8.750   0.2634   0.06313   0.05980  -0.1397   0.6425   0.0119
  -8.500   0.2667   0.05994   0.05663  -0.1404   0.6415   0.0120
  -8.250   0.2728   0.05743   0.05413  -0.1410   0.6405   0.0121
  -8.000   0.2799   0.05509   0.05181  -0.1417   0.6394   0.0122
  -7.750   0.2850   0.05249   0.04922  -0.1425   0.6384   0.0123
  -7.500   0.2915   0.05027   0.04701  -0.1431   0.6374   0.0125
  -7.250   0.2950   0.04758   0.04434  -0.1440   0.6364   0.0127
  -7.000   0.2975   0.04491   0.04168  -0.1449   0.6353   0.0130
  -6.750   0.2972   0.04208   0.03887  -0.1457   0.6342   0.0132
  -6.500   0.2910   0.03932   0.03613  -0.1462   0.6329   0.0135
  -6.250   0.2890   0.03602   0.03283  -0.1493   0.6314   0.0135
  -6.000   0.2382   0.02165   0.01723  -0.1770   0.6337   0.0123
  -5.750   0.2568   0.01749   0.01245  -0.1775   0.6323   0.0110
  -5.500   0.2829   0.01618   0.01081  -0.1779   0.6305   0.0113
  -5.250   0.3104   0.01534   0.00975  -0.1782   0.6293   0.0116
  -5.000   0.3384   0.01469   0.00893  -0.1786   0.6287   0.0118
  -4.500   0.3944   0.01320   0.00716  -0.1792   0.6270   0.0120
  -4.250   0.4225   0.01240   0.00628  -0.1796   0.6259   0.0122
  -4.000   0.4509   0.01189   0.00574  -0.1800   0.6247   0.0126
  -3.750   0.4797   0.01154   0.00536  -0.1804   0.6235   0.0132
  -3.500   0.5088   0.01123   0.00501  -0.1809   0.6224   0.0137
  -3.250   0.5380   0.01093   0.00467  -0.1813   0.6212   0.0141
  -3.000   0.5673   0.01070   0.00440  -0.1817   0.6201   0.0145
  -2.750   0.5968   0.01033   0.00399  -0.1823   0.6190   0.0153
  -2.500   0.6262   0.01014   0.00379  -0.1828   0.6179   0.0160
  -2.250   0.6556   0.01002   0.00363  -0.1832   0.6166   0.0166
  -2.000   0.6851   0.00995   0.00352  -0.1837   0.6151   0.0172
  -1.750   0.7147   0.00994   0.00349  -0.1843   0.6131   0.0187
  -1.500   0.7440   0.00981   0.00339  -0.1847   0.6124   0.0217
  -1.250   0.7734   0.00965   0.00331  -0.1853   0.6115   0.0413
  -1.000   0.8027   0.00956   0.00329  -0.1858   0.6105   0.0619
  -0.750   0.8319   0.00949   0.00328  -0.1863   0.6094   0.0754
  -0.500   0.8612   0.00943   0.00327  -0.1868   0.6082   0.0927
  -0.250   0.8906   0.00935   0.00326  -0.1874   0.6069   0.1180
   0.000   0.9203   0.00921   0.00327  -0.1881   0.6057   0.1753
   0.250   0.9507   0.00897   0.00330  -0.1891   0.6043   0.2860
   0.500   0.9825   0.00857   0.00338  -0.1906   0.6030   0.4912
   0.750   1.0153   0.00807   0.00353  -0.1922   0.6017   0.7581
   1.000   1.0393   0.00801   0.00369  -0.1913   0.6003   0.8715
   1.250   1.0640   0.00811   0.00380  -0.1907   0.5987   0.9043
   1.500   1.0895   0.00824   0.00392  -0.1903   0.5970   0.9198
   1.750   1.1136   0.00826   0.00396  -0.1896   0.5961   0.9324
   2.000   1.1352   0.00827   0.00399  -0.1884   0.5950   0.9457
   2.250   1.1501   0.00822   0.00398  -0.1856   0.5937   0.9639
   2.500   1.1693   0.00816   0.00394  -0.1838   0.5922   0.9869
   2.750   1.2008   0.00819   0.00396  -0.1849   0.5907   1.0000
   3.000   1.2309   0.00825   0.00400  -0.1858   0.5891   1.0000
   3.250   1.2609   0.00832   0.00406  -0.1866   0.5877   1.0000
   3.500   1.2908   0.00839   0.00412  -0.1874   0.5863   1.0000
   3.750   1.3205   0.00849   0.00419  -0.1881   0.5848   1.0000
   4.000   1.3504   0.00863   0.00430  -0.1890   0.5830   1.0000
   4.250   1.3799   0.00878   0.00445  -0.1897   0.5813   1.0000
   4.500   1.4083   0.00885   0.00454  -0.1903   0.5800   1.0000
   4.750   1.4366   0.00892   0.00464  -0.1908   0.5784   1.0000
   5.000   1.4649   0.00900   0.00474  -0.1913   0.5768   1.0000
   5.250   1.4931   0.00909   0.00485  -0.1918   0.5751   1.0000
   5.500   1.5212   0.00917   0.00494  -0.1923   0.5733   1.0000
   5.750   1.5488   0.00924   0.00501  -0.1927   0.5713   1.0000
   6.000   1.5763   0.00933   0.00510  -0.1931   0.5688   1.0000
   6.250   1.6040   0.00948   0.00524  -0.1935   0.5660   1.0000
   6.500   1.6292   0.00955   0.00536  -0.1935   0.5637   1.0000
   6.750   1.6543   0.00960   0.00546  -0.1934   0.5605   1.0000
   7.000   1.6790   0.00966   0.00553  -0.1932   0.5568   1.0000
   7.250   1.7033   0.00978   0.00563  -0.1930   0.5526   1.0000
   7.500   1.7264   0.00990   0.00579  -0.1925   0.5487   1.0000
   7.750   1.7478   0.00998   0.00592  -0.1917   0.5430   1.0000
   8.000   1.7655   0.01017   0.00607  -0.1903   0.5370   1.0000
   8.250   1.7839   0.01032   0.00628  -0.1889   0.5312   1.0000
   8.500   1.8009   0.01053   0.00651  -0.1873   0.5258   1.0000
   8.750   1.8160   0.01084   0.00681  -0.1855   0.5212   1.0000
   9.000   1.8342   0.01108   0.00711  -0.1843   0.5156   1.0000
   9.250   1.8446   0.01152   0.00754  -0.1817   0.5080   1.0000
   9.500   1.8583   0.01193   0.00799  -0.1798   0.5006   1.0000
   9.750   1.8661   0.01256   0.00861  -0.1771   0.4928   1.0000
  10.000   1.8756   0.01320   0.00929  -0.1747   0.4838   1.0000
  10.250   1.8778   0.01420   0.01028  -0.1714   0.4737   1.0000
  10.500   1.8770   0.01547   0.01154  -0.1680   0.4618   1.0000
  10.750   1.8782   0.01680   0.01288  -0.1651   0.4501   1.0000
  11.000   1.8702   0.01880   0.01487  -0.1613   0.4350   1.0000
  11.250   1.8556   0.02142   0.01745  -0.1571   0.4178   1.0000
  11.500   1.8347   0.02467   0.02065  -0.1526   0.3989   1.0000
  11.750   1.8102   0.02836   0.02427  -0.1480   0.3775   1.0000
  12.000   1.7864   0.03221   0.02805  -0.1439   0.3574   1.0000
  12.250   1.7650   0.03610   0.03186  -0.1402   0.3384   1.0000
  12.500   1.7497   0.03965   0.03535  -0.1373   0.3196   1.0000
  12.750   1.7368   0.04314   0.03878  -0.1348   0.3008   1.0000
  13.000   1.7245   0.04668   0.04223  -0.1325   0.2802   1.0000
  13.500   1.7014   0.05404   0.04942  -0.1286   0.2403   1.0000
  13.750   1.6923   0.05761   0.05289  -0.1269   0.2188   1.0000
  14.000   1.6848   0.06115   0.05635  -0.1255   0.2011   1.0000
  14.250   1.6782   0.06464   0.05972  -0.1243   0.1800   1.0000
  14.500   1.6757   0.06777   0.06281  -0.1234   0.1664   1.0000
  14.750   1.6727   0.07101   0.06597  -0.1225   0.1491   1.0000
  15.000   1.6689   0.07444   0.06932  -0.1218   0.1337   1.0000
  15.250   1.6669   0.07767   0.07248  -0.1211   0.1195   1.0000
  15.750   1.6651   0.08407   0.07878  -0.1202   0.0953   1.0000
  16.000   1.6656   0.08714   0.08180  -0.1199   0.0841   1.0000
  16.250   1.6645   0.09049   0.08511  -0.1196   0.0737   1.0000
  16.500   1.6642   0.09371   0.08829  -0.1195   0.0630   1.0000
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