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FX 72-LS-160 (fx72ls160-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 72-LS-160 (fx72ls160-il)
Reynolds number: 200,000
Max Cl/Cd: 58.48 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx72ls160-il-200000-n5.txt
Download as CSV file: xf-fx72ls160-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.2007   0.09711   0.09135  -0.1369   0.6811   0.0268
  -9.750   0.2062   0.09464   0.08893  -0.1382   0.6797   0.0269
  -9.500   0.2090   0.09212   0.08645  -0.1397   0.6783   0.0270
  -9.250   0.2158   0.08944   0.08382  -0.1406   0.6770   0.0271
  -9.000   0.2263   0.08709   0.08148  -0.1410   0.6757   0.0273
  -8.750   0.2356   0.08485   0.07926  -0.1415   0.6743   0.0276
  -8.500   0.2423   0.08250   0.07694  -0.1424   0.6730   0.0277
  -8.250   0.2482   0.08009   0.07456  -0.1433   0.6716   0.0279
  -7.250   0.2499   0.06665   0.06118  -0.1479   0.6662   0.0172
  -7.000   0.2513   0.06420   0.05875  -0.1485   0.6650   0.0171
  -6.750   0.2503   0.06210   0.05667  -0.1490   0.6639   0.0169
  -6.500   0.2511   0.05934   0.05398  -0.1511   0.6625   0.0167
  -6.250   0.2542   0.05614   0.05082  -0.1540   0.6609   0.0165
  -6.000   0.2520   0.04909   0.04373  -0.1608   0.6590   0.0173
  -5.750   0.2595   0.04355   0.03805  -0.1648   0.6573   0.0173
  -5.500   0.2681   0.03677   0.03094  -0.1682   0.6556   0.0172
  -5.250   0.2823   0.03146   0.02511  -0.1701   0.6541   0.0169
  -5.000   0.3022   0.02720   0.02017  -0.1714   0.6527   0.0169
  -4.750   0.3266   0.02462   0.01701  -0.1720   0.6515   0.0170
  -4.500   0.3529   0.02300   0.01494  -0.1723   0.6503   0.0173
  -4.250   0.3800   0.02212   0.01389  -0.1727   0.6491   0.0177
  -4.000   0.4077   0.02140   0.01299  -0.1730   0.6479   0.0182
  -3.750   0.4358   0.02075   0.01216  -0.1734   0.6468   0.0189
  -3.500   0.4612   0.02028   0.01158  -0.1732   0.6451   0.0200
  -3.250   0.4860   0.02004   0.01134  -0.1731   0.6433   0.0214
  -3.000   0.5115   0.01977   0.01101  -0.1729   0.6416   0.0230
  -2.750   0.5375   0.01948   0.01069  -0.1729   0.6399   0.0241
  -2.500   0.5640   0.01926   0.01043  -0.1730   0.6383   0.0256
  -2.250   0.5911   0.01903   0.01015  -0.1731   0.6367   0.0278
  -2.000   0.6189   0.01880   0.00990  -0.1733   0.6352   0.0321
  -1.750   0.6472   0.01860   0.00970  -0.1736   0.6338   0.0423
  -1.500   0.6757   0.01848   0.00960  -0.1740   0.6325   0.0607
  -1.250   0.7045   0.01841   0.00953  -0.1745   0.6315   0.0777
  -1.000   0.7336   0.01835   0.00946  -0.1750   0.6305   0.0927
  -0.750   0.7625   0.01832   0.00942  -0.1755   0.6295   0.1120
  -0.500   0.7842   0.01847   0.00975  -0.1749   0.6273   0.1403
  -0.250   0.8074   0.01853   0.01002  -0.1747   0.6250   0.1925
   0.000   0.8324   0.01844   0.01025  -0.1749   0.6229   0.2967
   0.250   0.8589   0.01812   0.01048  -0.1753   0.6210   0.4881
   0.500   0.8732   0.01768   0.01080  -0.1725   0.6194   0.7455
   0.750   0.8787   0.01765   0.01094  -0.1674   0.6179   0.8871
   1.000   0.8955   0.01765   0.01092  -0.1650   0.6166   0.9472
   1.250   0.9282   0.01767   0.01084  -0.1662   0.6155   1.0000
   1.500   0.9579   0.01780   0.01086  -0.1668   0.6145   1.0000
   1.750   0.9883   0.01793   0.01086  -0.1676   0.6135   1.0000
   2.000   1.0045   0.01851   0.01148  -0.1662   0.6107   1.0000
   2.250   1.0198   0.01912   0.01211  -0.1647   0.6076   1.0000
   2.500   1.0403   0.01955   0.01252  -0.1639   0.6053   1.0000
   2.750   1.0634   0.01988   0.01282  -0.1636   0.6035   1.0000
   3.000   1.0884   0.02014   0.01304  -0.1635   0.6019   1.0000
   3.250   1.1150   0.02034   0.01319  -0.1637   0.6006   1.0000
   3.500   1.1431   0.02047   0.01328  -0.1641   0.5995   1.0000
   3.750   1.1733   0.02055   0.01330  -0.1648   0.5985   1.0000
   4.000   1.2047   0.02060   0.01330  -0.1658   0.5975   1.0000
   4.250   1.1686   0.02284   0.01576  -0.1566   0.5904   1.0000
   4.500   1.1774   0.02364   0.01659  -0.1542   0.5875   1.0000
   4.750   1.1986   0.02399   0.01693  -0.1537   0.5858   1.0000
   5.000   1.2251   0.02413   0.01705  -0.1538   0.5846   1.0000
   5.250   1.2547   0.02414   0.01705  -0.1544   0.5835   1.0000
   5.500   1.2860   0.02411   0.01700  -0.1553   0.5826   1.0000
   5.750   1.3185   0.02409   0.01697  -0.1563   0.5819   1.0000
   6.250   1.2559   0.03000   0.02308  -0.1431   0.5675   1.0000
   6.500   1.2870   0.02981   0.02289  -0.1437   0.5669   1.0000
   8.500   1.2963   0.04577   0.03923  -0.1288   0.5221   1.0000
   9.000   1.2972   0.05041   0.04398  -0.1258   0.5082   1.0000
   9.250   1.3268   0.04990   0.04349  -0.1260   0.5074   1.0000
   9.500   1.3577   0.04925   0.04289  -0.1263   0.5068   1.0000
  10.500   1.3735   0.05738   0.05128  -0.1216   0.4789   1.0000
  11.000   1.3905   0.06068   0.05471  -0.1201   0.4655   1.0000
  11.250   1.4195   0.06006   0.05416  -0.1202   0.4636   1.0000
  11.500   1.4524   0.05900   0.05315  -0.1205   0.4619   1.0000
  12.000   1.4785   0.06123   0.05551  -0.1193   0.4466   1.0000
  12.500   1.4802   0.06645   0.06087  -0.1174   0.4231   1.0000
  12.750   1.5129   0.06527   0.05971  -0.1176   0.4168   1.0000
  13.000   1.5199   0.06720   0.06169  -0.1169   0.4044   1.0000
  13.250   1.5390   0.06764   0.06214  -0.1166   0.3922   1.0000
  13.500   1.5635   0.06731   0.06174  -0.1164   0.3752   1.0000
  13.750   1.5842   0.06731   0.06156  -0.1160   0.3517   1.0000
  14.000   1.5904   0.06912   0.06322  -0.1151   0.3271   1.0000
  14.250   1.5919   0.07158   0.06555  -0.1142   0.3056   1.0000
  14.500   1.5911   0.07448   0.06839  -0.1134   0.2864   1.0000
  14.750   1.5896   0.07751   0.07135  -0.1126   0.2680   1.0000
  15.000   1.5865   0.08082   0.07460  -0.1120   0.2502   1.0000
  15.250   1.5832   0.08423   0.07795  -0.1114   0.2329   1.0000
  15.500   1.5789   0.08783   0.08149  -0.1109   0.2162   1.0000
  15.750   1.5757   0.09136   0.08499  -0.1106   0.2005   1.0000
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