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MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MARSKE MONARCH AIRFOIL (NACA 43012A) (marske5-il)
Reynolds number: 50,000
Max Cl/Cd: 15.75 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-marske5-il-50000.txt
Download as CSV file: xf-marske5-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MARSKE MONARCH AIRFOIL (NACA 43012A)            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4468   0.10823   0.10172   0.0210   1.0000   0.3287
  -9.250  -0.4396   0.10533   0.09890   0.0221   1.0000   0.3508
  -9.000  -0.4516   0.10363   0.09730   0.0229   1.0000   0.3734
  -8.750  -0.4181   0.09924   0.09293   0.0250   1.0000   0.4012
  -8.500  -0.4110   0.09649   0.09026   0.0268   1.0000   0.4302
  -8.250  -0.4081   0.09440   0.08826   0.0290   1.0000   0.4621
  -8.000  -0.3841   0.09110   0.08499   0.0311   1.0000   0.4981
  -7.750  -0.3510   0.08755   0.08147   0.0327   1.0000   0.5398
  -7.500  -0.3420   0.08572   0.07972   0.0355   1.0000   0.5828
  -7.000  -0.2913   0.07831   0.07240   0.0358   1.0000   0.6423
  -6.750  -0.2795   0.07582   0.06999   0.0368   1.0000   0.6688
  -6.000  -0.5528   0.05299   0.04671   0.0125   1.0000   0.2597
  -5.750  -0.5445   0.04813   0.04082   0.0131   1.0000   0.1936
  -5.500  -0.5315   0.04495   0.03720   0.0155   1.0000   0.1756
  -5.250  -0.5204   0.04281   0.03437   0.0188   1.0000   0.1630
  -5.000  -0.5041   0.04002   0.03153   0.0207   1.0000   0.1594
  -4.750  -0.4895   0.03771   0.02894   0.0232   1.0000   0.1538
  -4.500  -0.4771   0.03664   0.02723   0.0268   1.0000   0.1475
  -4.250  -0.4629   0.03497   0.02540   0.0292   1.0000   0.1466
  -4.000  -0.4505   0.03370   0.02393   0.0317   1.0000   0.1471
  -3.750  -0.4363   0.03219   0.02235   0.0337   1.0000   0.1480
  -3.500  -0.4202   0.03093   0.02100   0.0354   1.0000   0.1488
  -3.250  -0.4024   0.02986   0.01987   0.0368   1.0000   0.1495
  -3.000  -0.3336   0.02818   0.01828   0.0294   0.9828   0.1581
  -2.750   0.1272   0.02320   0.01513  -0.0260   0.6907   1.0000
  -2.500   0.1440   0.02357   0.01482  -0.0234   0.6080   1.0000
  -2.250   0.1636   0.02375   0.01447  -0.0217   0.5617   1.0000
  -2.000   0.1850   0.02393   0.01420  -0.0205   0.5314   1.0000
  -1.750   0.2075   0.02414   0.01410  -0.0196   0.5061   1.0000
  -1.500   0.2302   0.02437   0.01406  -0.0188   0.4867   1.0000
  -1.250   0.2525   0.02466   0.01412  -0.0180   0.4703   1.0000
  -1.000   0.2745   0.02502   0.01428  -0.0170   0.4579   1.0000
  -0.750   0.2969   0.02541   0.01447  -0.0162   0.4468   1.0000
  -0.500   0.3201   0.02588   0.01487  -0.0157   0.4362   1.0000
  -0.250   0.3423   0.02635   0.01510  -0.0147   0.4276   1.0000
   0.000   0.3648   0.02691   0.01570  -0.0141   0.4183   1.0000
   0.250   0.3867   0.02747   0.01608  -0.0132   0.4112   1.0000
   0.500   0.4092   0.02824   0.01691  -0.0127   0.4055   1.0000
   0.750   0.4313   0.02904   0.01775  -0.0121   0.3998   1.0000
   1.000   0.4531   0.02979   0.01841  -0.0113   0.3949   1.0000
   1.250   0.4744   0.03077   0.01942  -0.0106   0.3902   1.0000
   1.500   0.4949   0.03189   0.02070  -0.0102   0.3851   1.0000
   1.750   0.5150   0.03293   0.02178  -0.0094   0.3803   1.0000
   2.000   0.5352   0.03399   0.02280  -0.0085   0.3770   1.0000
   2.250   0.5548   0.03534   0.02415  -0.0077   0.3746   1.0000
   2.500   0.5714   0.03729   0.02637  -0.0075   0.3728   1.0000
   2.750   0.5863   0.03948   0.02880  -0.0073   0.3711   1.0000
   3.000   0.5989   0.04188   0.03142  -0.0071   0.3693   1.0000
   3.250   0.6089   0.04453   0.03426  -0.0068   0.3675   1.0000
   3.500   0.6151   0.04771   0.03763  -0.0067   0.3673   1.0000
   3.750   0.6164   0.05155   0.04165  -0.0068   0.3698   1.0000
   4.000   0.6188   0.05508   0.04526  -0.0065   0.3728   1.0000
   4.250   0.6242   0.05819   0.04841  -0.0058   0.3753   1.0000
   4.500   0.3167   0.08102   0.07161  -0.0161   0.6054   1.0000
   4.750   0.3152   0.08228   0.07278  -0.0136   0.5910   1.0000
   5.000   0.3209   0.08412   0.07454  -0.0119   0.5781   1.0000
   5.250   0.3519   0.08762   0.07800  -0.0126   0.5689   1.0000
   5.500   0.3429   0.08827   0.07857  -0.0097   0.5548   1.0000
   5.750   0.3454   0.09013   0.08035  -0.0081   0.5434   1.0000
   6.000   0.3772   0.09381   0.08401  -0.0086   0.5337   1.0000
   6.250   0.3693   0.09451   0.08463  -0.0062   0.5191   1.0000
   6.500   0.3709   0.09627   0.08633  -0.0047   0.5065   1.0000
   6.750   0.4065   0.10058   0.09062  -0.0054   0.4981   1.0000
   7.000   0.3920   0.10081   0.09078  -0.0030   0.4846   1.0000
   7.250   0.3969   0.10310   0.09302  -0.0021   0.4751   1.0000
   7.500   0.4212   0.10631   0.09623  -0.0018   0.4639   1.0000
   7.750   0.4121   0.10728   0.09714  -0.0003   0.4514   1.0000
   8.000   0.4530   0.11274   0.10261  -0.0010   0.4449   1.0000
   8.250   0.4297   0.11205   0.10185   0.0009   0.4322   1.0000
   8.500   0.4506   0.11609   0.10587   0.0009   0.4263   1.0000
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