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Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Glenn Martin 4 (glennmartin4-il)
Reynolds number: 200,000
Max Cl/Cd: 49.71 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-glennmartin4-il-200000-n5.txt
Download as CSV file: xf-glennmartin4-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Glenn Martin 4                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2160   0.09486   0.09151  -0.0698   0.9544   0.0192
  -8.750  -0.2129   0.08959   0.08625  -0.0743   0.9515   0.0192
  -8.500  -0.2193   0.08535   0.08205  -0.0756   0.9442   0.0189
  -8.250  -0.2638   0.07510   0.07181  -0.0817   0.9336   0.0198
  -7.750  -0.2865   0.06610   0.06270  -0.0818   0.9189   0.0194
  -7.250  -0.3206   0.05399   0.05024  -0.0774   0.8983   0.0203
  -7.000  -0.3071   0.05143   0.04754  -0.0771   0.8936   0.0209
  -6.750  -0.3178   0.04635   0.04218  -0.0729   0.8835   0.0212
  -6.500  -0.3294   0.03834   0.03352  -0.0682   0.8776   0.0220
  -6.250  -0.3410   0.03364   0.02820  -0.0616   0.8673   0.0228
  -6.000  -0.3339   0.02964   0.02331  -0.0577   0.8619   0.0250
  -5.750  -0.3218   0.02828   0.02178  -0.0547   0.8532   0.0254
  -5.500  -0.2999   0.02757   0.02105  -0.0535   0.8470   0.0267
  -5.250  -0.2783   0.02630   0.01954  -0.0521   0.8403   0.0282
  -5.000  -0.2596   0.02492   0.01785  -0.0499   0.8305   0.0293
  -4.750  -0.2343   0.02367   0.01625  -0.0489   0.8200   0.0312
  -4.500  -0.2018   0.02223   0.01468  -0.0496   0.8100   0.0327
  -4.250  -0.1715   0.02133   0.01364  -0.0497   0.7962   0.0344
  -4.000  -0.1346   0.02025   0.01233  -0.0512   0.7809   0.0366
  -3.750  -0.0966   0.01927   0.01112  -0.0529   0.7668   0.0387
  -3.500  -0.0549   0.01839   0.01016  -0.0556   0.7488   0.0409
  -3.250  -0.0105   0.01770   0.00929  -0.0588   0.7249   0.0441
  -3.000   0.0320   0.01704   0.00837  -0.0617   0.6946   0.0463
  -2.750   0.0649   0.01678   0.00794  -0.0627   0.6645   0.0493
  -2.500   0.0912   0.01662   0.00760  -0.0623   0.6423   0.0524
  -2.250   0.1148   0.01652   0.00735  -0.0613   0.6232   0.0562
  -2.000   0.1372   0.01645   0.00714  -0.0601   0.6075   0.0607
  -1.750   0.1588   0.01639   0.00694  -0.0588   0.5925   0.0665
  -1.500   0.1806   0.01637   0.00678  -0.0575   0.5799   0.0746
  -1.250   0.2012   0.01625   0.00659  -0.0561   0.5680   0.0813
  -1.000   0.2226   0.01620   0.00643  -0.0549   0.5576   0.0873
  -0.750   0.2436   0.01613   0.00631  -0.0536   0.5473   0.0933
  -0.500   0.2651   0.01613   0.00622  -0.0523   0.5374   0.0981
  -0.250   0.2869   0.01612   0.00617  -0.0512   0.5286   0.1055
   0.000   0.3082   0.01611   0.00616  -0.0500   0.5188   0.1164
   0.250   0.3295   0.01616   0.00616  -0.0488   0.5093   0.1298
   0.500   0.3516   0.01611   0.00617  -0.0478   0.4999   0.1599
   0.750   0.3744   0.01589   0.00619  -0.0472   0.4911   0.2439
   1.250   0.6831   0.01644   0.00833  -0.1049   0.4512   1.0000
   1.500   0.7000   0.01661   0.00838  -0.1029   0.4419   1.0000
   1.750   0.7177   0.01677   0.00845  -0.1010   0.4315   1.0000
   2.000   0.7352   0.01696   0.00853  -0.0992   0.4232   1.0000
   2.250   0.7527   0.01715   0.00863  -0.0974   0.4139   1.0000
   2.500   0.7707   0.01735   0.00875  -0.0956   0.4059   1.0000
   2.750   0.7890   0.01756   0.00888  -0.0940   0.3985   1.0000
   3.000   0.8070   0.01779   0.00902  -0.0923   0.3919   1.0000
   3.250   0.8259   0.01801   0.00918  -0.0908   0.3849   1.0000
   3.500   0.8439   0.01826   0.00936  -0.0892   0.3793   1.0000
   3.750   0.8627   0.01851   0.00955  -0.0878   0.3733   1.0000
   4.000   0.8820   0.01875   0.00975  -0.0864   0.3684   1.0000
   4.250   0.8997   0.01904   0.00997  -0.0848   0.3632   1.0000
   4.500   0.9186   0.01931   0.01020  -0.0834   0.3585   1.0000
   4.750   0.9381   0.01957   0.01044  -0.0822   0.3542   1.0000
   5.000   0.9572   0.01985   0.01069  -0.0809   0.3504   1.0000
   5.250   0.9758   0.02017   0.01097  -0.0796   0.3468   1.0000
   5.500   0.9953   0.02047   0.01124  -0.0784   0.3437   1.0000
   5.750   1.0149   0.02074   0.01154  -0.0773   0.3400   1.0000
   6.000   1.0343   0.02104   0.01184  -0.0762   0.3367   1.0000
   6.250   1.0527   0.02136   0.01215  -0.0749   0.3333   1.0000
   6.500   1.0714   0.02173   0.01250  -0.0737   0.3304   1.0000
   6.750   1.0910   0.02207   0.01283  -0.0727   0.3280   1.0000
   7.000   1.1102   0.02239   0.01320  -0.0716   0.3250   1.0000
   7.250   1.1286   0.02272   0.01359  -0.0704   0.3218   1.0000
   7.500   1.1472   0.02308   0.01397  -0.0692   0.3191   1.0000
   7.750   1.1652   0.02346   0.01438  -0.0680   0.3164   1.0000
   8.000   1.1836   0.02387   0.01477  -0.0669   0.3138   1.0000
   8.250   1.2016   0.02429   0.01522  -0.0658   0.3109   1.0000
   8.500   1.2192   0.02467   0.01570  -0.0646   0.3086   1.0000
   8.750   1.2366   0.02508   0.01619  -0.0633   0.3060   1.0000
   9.000   1.2533   0.02550   0.01668  -0.0620   0.3035   1.0000
   9.250   1.2686   0.02597   0.01720  -0.0605   0.3003   1.0000
   9.500   1.2854   0.02645   0.01770  -0.0593   0.2979   1.0000
   9.750   1.3003   0.02696   0.01826  -0.0578   0.2946   1.0000
  10.000   1.3078   0.02756   0.01900  -0.0551   0.2888   1.0000
  10.250   1.3176   0.02818   0.01967  -0.0528   0.2840   1.0000
  10.500   1.3272   0.02886   0.02036  -0.0506   0.2793   1.0000
  10.750   1.3369   0.02954   0.02121  -0.0485   0.2743   1.0000
  11.000   1.3462   0.03027   0.02202  -0.0465   0.2695   1.0000
  11.250   1.3520   0.03117   0.02293  -0.0440   0.2638   1.0000
  11.500   1.3615   0.03197   0.02389  -0.0422   0.2583   1.0000
  11.750   1.3679   0.03295   0.02495  -0.0400   0.2521   1.0000
  12.000   1.3715   0.03413   0.02621  -0.0377   0.2426   1.0000
  12.250   1.3726   0.03553   0.02764  -0.0352   0.2342   1.0000
  12.500   1.3728   0.03711   0.02928  -0.0329   0.2201   1.0000
  12.750   1.3673   0.03920   0.03135  -0.0303   0.2011   1.0000
  13.000   1.3547   0.04198   0.03405  -0.0274   0.1796   1.0000
  13.250   1.3425   0.04495   0.03699  -0.0249   0.1633   1.0000
  13.500   1.3219   0.04892   0.04089  -0.0225   0.1423   1.0000
  13.750   1.3016   0.05317   0.04512  -0.0206   0.1256   1.0000
  14.250   1.2538   0.06325   0.05519  -0.0184   0.0769   1.0000
  14.500   1.2304   0.06862   0.06059  -0.0180   0.0622   1.0000
  14.750   1.1984   0.07527   0.06726  -0.0178   0.0500   1.0000
  15.000   1.1776   0.08074   0.07284  -0.0180   0.0430   1.0000
  15.250   1.1609   0.08583   0.07805  -0.0183   0.0372   1.0000
  15.500   1.1457   0.09079   0.08312  -0.0189   0.0331   1.0000
  15.750   1.1299   0.09598   0.08841  -0.0195   0.0292   1.0000
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