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Marsden (marsden-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Marsden (marsden-il)
Reynolds number: 200,000
Max Cl/Cd: 17.05 at α=-2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-marsden-il-200000-n5.txt
Download as CSV file: xf-marsden-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750   0.4137   0.11253   0.10463  -0.1479   0.4567   0.0535
 -12.500   0.4197   0.10974   0.10187  -0.1491   0.4564   0.0529
 -12.000   0.4268   0.10348   0.09565  -0.1518   0.4559   0.0520
 -11.500   0.1554   0.05328   0.04482  -0.1813   0.4574   0.0509
 -11.250   0.1324   0.04926   0.04064  -0.1834   0.4572   0.0509
 -11.000   0.1227   0.04675   0.03802  -0.1840   0.4570   0.0511
 -10.750   0.1176   0.04476   0.03593  -0.1840   0.4568   0.0512
 -10.500   0.1160   0.04315   0.03424  -0.1835   0.4565   0.0513
 -10.250   0.1163   0.04176   0.03278  -0.1828   0.4562   0.0515
 -10.000   0.1179   0.04054   0.03150  -0.1817   0.4559   0.0517
  -9.750   0.1203   0.03950   0.03039  -0.1803   0.4556   0.0519
  -9.500   0.1222   0.03867   0.02951  -0.1786   0.4553   0.0521
  -9.250   0.1232   0.03802   0.02881  -0.1763   0.4549   0.0523
  -9.000   0.1238   0.03746   0.02820  -0.1737   0.4544   0.0525
  -8.750   0.1289   0.03688   0.02757  -0.1718   0.4539   0.0528
  -8.500   0.1368   0.03632   0.02696  -0.1701   0.4533   0.0531
  -8.250   0.1464   0.03582   0.02640  -0.1687   0.4528   0.0536
  -8.000   0.1578   0.03535   0.02587  -0.1673   0.4524   0.0540
  -7.750   0.1706   0.03493   0.02538  -0.1661   0.4520   0.0545
  -7.500   0.1845   0.03454   0.02492  -0.1649   0.4515   0.0549
  -7.250   0.1995   0.03422   0.02452  -0.1637   0.4511   0.0553
  -7.000   0.2151   0.03392   0.02423  -0.1622   0.4507   0.0556
  -6.750   0.2309   0.03369   0.02403  -0.1607   0.4502   0.0560
  -6.500   0.2468   0.03350   0.02387  -0.1593   0.4498   0.0563
  -6.250   0.2630   0.03335   0.02376  -0.1579   0.4493   0.0567
  -6.000   0.2792   0.03323   0.02366  -0.1565   0.4489   0.0571
  -5.750   0.2958   0.03312   0.02358  -0.1552   0.4484   0.0576
  -5.500   0.3129   0.03301   0.02348  -0.1539   0.4478   0.0581
  -5.250   0.3308   0.03288   0.02335  -0.1527   0.4472   0.0586
  -5.000   0.3493   0.03277   0.02323  -0.1517   0.4466   0.0592
  -4.750   0.3682   0.03268   0.02314  -0.1507   0.4461   0.0598
  -4.500   0.3874   0.03265   0.02311  -0.1497   0.4456   0.0605
  -4.250   0.4069   0.03267   0.02312  -0.1489   0.4451   0.0611
  -4.000   0.4269   0.03268   0.02315  -0.1482   0.4447   0.0618
  -3.750   0.4481   0.03271   0.02323  -0.1479   0.4442   0.0626
  -3.500   0.4706   0.03280   0.02335  -0.1477   0.4438   0.0636
  -3.250   0.4952   0.03290   0.02347  -0.1479   0.4433   0.0649
  -3.000   0.5209   0.03306   0.02361  -0.1483   0.4427   0.0665
  -2.750   0.5476   0.03330   0.02384  -0.1489   0.4421   0.0682
  -2.500   0.5746   0.03371   0.02428  -0.1498   0.4414   0.0699
  -2.000   0.2744   0.05152   0.04325  -0.1183   0.4282   0.0633
  -1.750   0.2907   0.05303   0.04479  -0.1193   0.4269   0.0643
  -1.500   0.3107   0.05419   0.04594  -0.1203   0.4259   0.0656
  -1.250   0.3342   0.05503   0.04677  -0.1214   0.4252   0.0673
  -1.000   0.3613   0.05564   0.04739  -0.1227   0.4246   0.0689
  -0.750   0.3889   0.05624   0.04801  -0.1241   0.4241   0.0709
  -0.500   0.4166   0.05684   0.04860  -0.1253   0.4237   0.0731
   0.750   0.3093   0.08359   0.07570  -0.1271   0.3967   0.0739
   1.750   0.3618   0.09244   0.08469  -0.1314   0.3879   0.0846
   3.250   0.5504   0.10129   0.09559  -0.1499   0.3812   0.5381
   3.500   0.5683   0.10197   0.09635  -0.1488   0.3807   0.5875
   3.750   0.5881   0.10274   0.09711  -0.1483   0.3803   0.6129
   4.250   0.5713   0.11125   0.10571  -0.1489   0.3699   0.6332
   4.500   0.5825   0.11178   0.10626  -0.1465   0.3691   0.6493
   4.750   0.5947   0.11234   0.10682  -0.1443   0.3684   0.6646
   5.000   0.6115   0.11304   0.10749  -0.1431   0.3679   0.6787
   5.250   0.6246   0.11343   0.10788  -0.1410   0.3674   0.6859
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