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Glenn Martin 2 (glennmartin2-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Glenn Martin 2 (glennmartin2-il)
Reynolds number: 100,000
Max Cl/Cd: 45.79 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-glennmartin2-il-100000-n5.txt
Download as CSV file: xf-glennmartin2-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Glenn Martin 2                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1874   0.09686   0.09240  -0.0616   0.9650   0.0365
  -9.250  -0.1871   0.09203   0.08760  -0.0656   0.9576   0.0368
  -8.750  -0.1830   0.08328   0.07889  -0.0726   0.9421   0.0368
  -8.500  -0.1776   0.07831   0.07389  -0.0774   0.9352   0.0368
  -8.250  -0.1823   0.07312   0.06869  -0.0800   0.9231   0.0369
  -8.000  -0.1736   0.06952   0.06506  -0.0819   0.9140   0.0375
  -7.750  -0.1467   0.06835   0.06386  -0.0832   0.9071   0.0401
  -7.500  -0.1417   0.06421   0.05964  -0.0850   0.8968   0.0411
  -7.250  -0.1303   0.05825   0.05351  -0.0888   0.8894   0.0420
  -7.000  -0.1311   0.05320   0.04828  -0.0887   0.8775   0.0423
  -6.750  -0.1328   0.04511   0.03974  -0.0893   0.8684   0.0439
  -6.500  -0.1334   0.03827   0.03217  -0.0879   0.8590   0.0461
  -6.250  -0.1173   0.03700   0.03079  -0.0862   0.8488   0.0476
  -6.000  -0.0918   0.03463   0.02809  -0.0864   0.8426   0.0499
  -5.750  -0.0821   0.03226   0.02525  -0.0835   0.8311   0.0529
  -5.500  -0.0563   0.02910   0.02130  -0.0832   0.8256   0.0555
  -5.250  -0.0411   0.02824   0.02039  -0.0808   0.8138   0.0572
  -5.000  -0.0162   0.02740   0.01941  -0.0801   0.8049   0.0604
  -4.750   0.0108   0.02601   0.01764  -0.0796   0.7958   0.0638
  -4.500   0.0316   0.02484   0.01608  -0.0778   0.7841   0.0660
  -4.250   0.0591   0.02379   0.01493  -0.0775   0.7737   0.0692
  -4.000   0.0900   0.02301   0.01401  -0.0778   0.7632   0.0739
  -3.750   0.1147   0.02221   0.01297  -0.0767   0.7499   0.0779
  -3.500   0.1421   0.02138   0.01195  -0.0762   0.7377   0.0819
  -3.250   0.1712   0.02068   0.01122  -0.0762   0.7255   0.0881
  -3.000   0.2033   0.02013   0.01042  -0.0766   0.7126   0.0964
  -2.750   0.2348   0.01941   0.00969  -0.0771   0.6989   0.1046
  -2.500   0.2673   0.01890   0.00904  -0.0778   0.6849   0.1150
  -2.250   0.2982   0.01852   0.00855  -0.0781   0.6704   0.1276
  -2.000   0.3287   0.01819   0.00819  -0.0784   0.6550   0.1419
  -1.750   0.3588   0.01797   0.00797  -0.0787   0.6388   0.1597
  -1.500   0.3875   0.01787   0.00785  -0.0786   0.6219   0.1827
  -1.250   0.4133   0.01790   0.00781  -0.0780   0.6043   0.2172
  -1.000   0.4352   0.01798   0.00781  -0.0767   0.5853   0.2465
  -0.750   0.4556   0.01808   0.00777  -0.0751   0.5639   0.2683
  -0.500   0.4762   0.01814   0.00771  -0.0736   0.5403   0.2858
  -0.250   0.4958   0.01820   0.00766  -0.0719   0.5135   0.3022
   0.000   0.5157   0.01826   0.00757  -0.0703   0.4887   0.3209
   0.250   0.5352   0.01835   0.00750  -0.0688   0.4690   0.3415
   0.500   0.5549   0.01843   0.00748  -0.0673   0.4540   0.3647
   0.750   0.5742   0.01846   0.00752  -0.0658   0.4420   0.4014
   1.250   0.7769   0.01896   0.00863  -0.0972   0.4132   1.0000
   1.500   0.7968   0.01925   0.00880  -0.0958   0.4075   1.0000
   1.750   0.8172   0.01957   0.00896  -0.0945   0.4029   1.0000
   2.000   0.8386   0.01990   0.00914  -0.0934   0.3988   1.0000
   2.250   0.8594   0.02019   0.00937  -0.0923   0.3945   1.0000
   2.500   0.8807   0.02050   0.00960  -0.0912   0.3907   1.0000
   2.750   0.9027   0.02084   0.00983  -0.0903   0.3870   1.0000
   3.250   0.9470   0.02154   0.01038  -0.0886   0.3802   1.0000
   3.500   0.9681   0.02188   0.01069  -0.0876   0.3766   1.0000
   3.750   0.9901   0.02224   0.01102  -0.0867   0.3735   1.0000
   4.000   1.0132   0.02262   0.01134  -0.0862   0.3707   1.0000
   4.250   1.0379   0.02303   0.01167  -0.0859   0.3683   1.0000
   4.500   1.0617   0.02345   0.01207  -0.0855   0.3660   1.0000
   4.750   1.0822   0.02385   0.01253  -0.0844   0.3635   1.0000
   5.000   1.1028   0.02426   0.01298  -0.0834   0.3608   1.0000
   5.250   1.1239   0.02470   0.01345  -0.0825   0.3581   1.0000
   5.500   1.1458   0.02513   0.01388  -0.0818   0.3553   1.0000
   5.750   1.1694   0.02559   0.01432  -0.0814   0.3529   1.0000
   6.000   1.1956   0.02611   0.01481  -0.0816   0.3507   1.0000
   6.250   1.2119   0.02659   0.01540  -0.0799   0.3479   1.0000
   6.500   1.2265   0.02706   0.01598  -0.0778   0.3445   1.0000
   6.750   1.2421   0.02749   0.01648  -0.0760   0.3405   1.0000
   7.000   1.2614   0.02792   0.01691  -0.0749   0.3367   1.0000
   7.250   1.2856   0.02839   0.01733  -0.0747   0.3335   1.0000
   7.500   1.2945   0.02893   0.01806  -0.0718   0.3303   1.0000
   7.750   1.3068   0.02950   0.01875  -0.0695   0.3272   1.0000
   8.000   1.3206   0.03002   0.01938  -0.0674   0.3241   1.0000
   8.250   1.3375   0.03054   0.01997  -0.0660   0.3213   1.0000
   8.500   1.3584   0.03100   0.02044  -0.0653   0.3184   1.0000
   8.750   1.3613   0.03149   0.02106  -0.0614   0.3141   1.0000
   9.000   1.3609   0.03201   0.02174  -0.0570   0.3093   1.0000
   9.250   1.3676   0.03217   0.02185  -0.0538   0.3027   1.0000
   9.500   1.3652   0.03273   0.02253  -0.0495   0.2967   1.0000
   9.750   1.3658   0.03336   0.02332  -0.0459   0.2911   1.0000
  10.000   1.3739   0.03375   0.02371  -0.0434   0.2858   1.0000
  10.250   1.3732   0.03469   0.02484  -0.0401   0.2808   1.0000
  10.500   1.3732   0.03559   0.02589  -0.0370   0.2748   1.0000
  10.750   1.3758   0.03633   0.02666  -0.0344   0.2688   1.0000
  11.000   1.3699   0.03776   0.02830  -0.0312   0.2609   1.0000
  11.250   1.3719   0.03879   0.02938  -0.0290   0.2549   1.0000
  11.500   1.3678   0.04057   0.03142  -0.0266   0.2468   1.0000
  11.750   1.3660   0.04219   0.03313  -0.0246   0.2392   1.0000
  12.000   1.3609   0.04430   0.03540  -0.0228   0.2299   1.0000
  12.250   1.3560   0.04662   0.03786  -0.0213   0.2209   1.0000
  12.500   1.3493   0.04924   0.04057  -0.0200   0.2113   1.0000
  12.750   1.3384   0.05247   0.04386  -0.0189   0.1993   1.0000
  13.000   1.3235   0.05638   0.04779  -0.0182   0.1876   1.0000
  13.250   1.3051   0.06102   0.05247  -0.0179   0.1779   1.0000
  13.500   1.2834   0.06639   0.05791  -0.0180   0.1712   1.0000
  13.750   1.2636   0.07192   0.06360  -0.0185   0.1683   1.0000
  14.000   1.2377   0.07857   0.07039  -0.0195   0.1640   1.0000
  14.250   1.2165   0.08486   0.07683  -0.0207   0.1620   1.0000
  14.500   1.1970   0.09099   0.08306  -0.0220   0.1581   1.0000
  14.750   1.1794   0.09698   0.08919  -0.0233   0.1544   1.0000
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