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Marsden (marsden-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Marsden (marsden-il)
Reynolds number: 500,000
Max Cl/Cd: 28.67 at α=0°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-marsden-il-500000.txt
Download as CSV file: xf-marsden-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Marsden                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500   0.4479   0.10722   0.10140  -0.1557   0.4562   0.0568
 -12.250   0.4595   0.10540   0.09960  -0.1565   0.4558   0.0573
 -12.000   0.2468   0.06369   0.05774  -0.1809   0.4573   0.0557
 -11.750   0.2686   0.06361   0.05774  -0.1798   0.4570   0.0561
 -11.500   0.2249   0.05482   0.04883  -0.1860   0.4570   0.0541
 -11.250   0.1571   0.04625   0.04000  -0.1913   0.4571   0.0531
 -11.000   0.1233   0.04192   0.03546  -0.1923   0.4570   0.0527
 -10.750   0.1100   0.03943   0.03283  -0.1920   0.4567   0.0527
 -10.500   0.1050   0.03769   0.03099  -0.1912   0.4565   0.0528
 -10.250   0.1023   0.03623   0.02944  -0.1899   0.4563   0.0530
 -10.000   0.0987   0.03518   0.02831  -0.1879   0.4561   0.0531
  -9.750   0.0933   0.03436   0.02740  -0.1851   0.4559   0.0532
  -9.500   0.0966   0.03346   0.02642  -0.1834   0.4556   0.0532
  -9.250   0.1053   0.03265   0.02552  -0.1823   0.4554   0.0533
  -9.000   0.1172   0.03192   0.02471  -0.1814   0.4551   0.0535
  -8.750   0.1317   0.03127   0.02399  -0.1806   0.4547   0.0536
  -8.500   0.1477   0.03069   0.02335  -0.1798   0.4544   0.0538
  -8.250   0.1650   0.03021   0.02280  -0.1790   0.4541   0.0540
  -8.000   0.1832   0.02978   0.02233  -0.1781   0.4537   0.0542
  -7.750   0.2020   0.02943   0.02193  -0.1773   0.4534   0.0544
  -7.500   0.2214   0.02912   0.02158  -0.1764   0.4530   0.0546
  -7.250   0.2416   0.02884   0.02127  -0.1756   0.4525   0.0548
  -7.000   0.2626   0.02857   0.02095  -0.1749   0.4520   0.0550
  -6.750   0.2844   0.02835   0.02069  -0.1743   0.4514   0.0553
  -6.500   0.3064   0.02820   0.02051  -0.1737   0.4509   0.0554
  -6.250   0.3240   0.02780   0.02014  -0.1720   0.4505   0.0558
  -6.000   0.3426   0.02756   0.01994  -0.1705   0.4502   0.0562
  -5.750   0.3629   0.02742   0.01984  -0.1695   0.4498   0.0566
  -5.500   0.3850   0.02731   0.01976  -0.1688   0.4493   0.0571
  -5.250   0.4075   0.02721   0.01968  -0.1682   0.4487   0.0577
  -5.000   0.4311   0.02714   0.01962  -0.1679   0.4482   0.0584
  -4.750   0.4550   0.02707   0.01956  -0.1676   0.4476   0.0591
  -4.500   0.4788   0.02707   0.01956  -0.1673   0.4472   0.0598
  -4.250   0.5028   0.02709   0.01959  -0.1670   0.4468   0.0604
  -4.000   0.5275   0.02714   0.01964  -0.1669   0.4463   0.0609
  -3.750   0.5530   0.02723   0.01973  -0.1670   0.4459   0.0614
  -3.500   0.5788   0.02716   0.01970  -0.1673   0.4455   0.0623
  -3.250   0.6067   0.02722   0.01980  -0.1680   0.4451   0.0633
  -3.000   0.6350   0.02738   0.01999  -0.1687   0.4446   0.0644
  -2.750   0.6636   0.02764   0.02026  -0.1695   0.4441   0.0657
  -2.500   0.6920   0.02801   0.02065  -0.1703   0.4436   0.0670
  -2.250   0.7192   0.02864   0.02129  -0.1711   0.4429   0.0685
  -2.000   0.7193   0.03124   0.02406  -0.1683   0.4409   0.0697
  -1.750   0.7479   0.03109   0.02397  -0.1691   0.4405   0.0721
  -1.500   0.7730   0.03120   0.02411  -0.1692   0.4401   0.0748
  -1.250   0.7992   0.03142   0.02443  -0.1699   0.4396   0.0795
  -1.000   0.8229   0.03176   0.02486  -0.1701   0.4390   0.0865
  -0.750   0.8455   0.03222   0.02548  -0.1705   0.4382   0.1046
  -0.500   0.8855   0.03259   0.02636  -0.1750   0.4373   0.2168
  -0.250   0.9179   0.03338   0.02754  -0.1780   0.4362   0.3140
   0.000   0.9801   0.03418   0.02905  -0.1870   0.4350   0.5126
   0.250   0.9754   0.03585   0.03095  -0.1833   0.4336   0.5548
   0.500   0.9549   0.03813   0.03339  -0.1780   0.4319   0.5695
   0.750   0.9350   0.04063   0.03601  -0.1734   0.4302   0.5812
   1.000   0.9277   0.04273   0.03819  -0.1706   0.4289   0.5930
   1.250   0.9357   0.04417   0.03964  -0.1694   0.4280   0.6073
   1.500   0.9503   0.04504   0.04053  -0.1684   0.4274   0.6179
   1.750   0.9665   0.04591   0.04137  -0.1677   0.4268   0.6278
   2.000   0.9835   0.04670   0.04215  -0.1670   0.4262   0.6362
   2.250   0.9946   0.04758   0.04305  -0.1653   0.4255   0.6441
   2.500   1.0051   0.04892   0.04438  -0.1640   0.4248   0.6523
   2.750   0.6505   0.09257   0.08859  -0.1639   0.3925   0.5862
   3.000   0.6808   0.09229   0.08830  -0.1635   0.3930   0.6118
   3.250   0.7090   0.09207   0.08808  -0.1628   0.3934   0.6264
   3.750   0.6252   0.10804   0.10423  -0.1634   0.3758   0.6223
   4.000   0.6910   0.10317   0.09926  -0.1625   0.3816   0.6410
   4.250   0.7119   0.10352   0.09959  -0.1617   0.3813   0.6504
   4.500   0.7341   0.10377   0.09981  -0.1611   0.3809   0.6599
   4.750   0.7482   0.10413   0.10021  -0.1591   0.3805   0.6677
   5.000   0.7029   0.11300   0.10916  -0.1602   0.3696   0.6656
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