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Glenn Martin 2 (glennmartin2-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Glenn Martin 2 (glennmartin2-il)
Reynolds number: 50,000
Max Cl/Cd: 31.65 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-glennmartin2-il-50000-n5.txt
Download as CSV file: xf-glennmartin2-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2858   0.11453   0.10896  -0.0286   0.9909   0.1099
  -8.500  -0.2912   0.11214   0.10662  -0.0349   0.9815   0.1117
  -8.250  -0.2942   0.10921   0.10373  -0.0395   0.9717   0.1122
  -7.750  -0.2818   0.09362   0.08798  -0.0501   0.9539   0.0664
  -7.500  -0.2707   0.08950   0.08383  -0.0525   0.9455   0.0661
  -7.250  -0.2545   0.08695   0.08132  -0.0525   0.9384   0.0698
  -7.000  -0.2465   0.08327   0.07759  -0.0546   0.9287   0.0704
  -6.750  -0.2327   0.07895   0.07317  -0.0581   0.9207   0.0709
  -6.500  -0.2272   0.07488   0.06900  -0.0596   0.9094   0.0705
  -6.250  -0.2140   0.07031   0.06426  -0.0621   0.9001   0.0703
  -6.000  -0.1967   0.06675   0.06053  -0.0639   0.8905   0.0729
  -5.750  -0.1847   0.06305   0.05662  -0.0645   0.8791   0.0751
  -5.500  -0.1643   0.05823   0.05144  -0.0664   0.8701   0.0762
  -5.250  -0.1481   0.05367   0.04644  -0.0668   0.8593   0.0775
  -5.000  -0.1354   0.04918   0.04119  -0.0659   0.8474   0.0805
  -4.750  -0.1097   0.04695   0.03891  -0.0660   0.8367   0.0836
  -4.500  -0.0822   0.04408   0.03564  -0.0661   0.8268   0.0859
  -4.250  -0.0633   0.04199   0.03319  -0.0646   0.8143   0.0897
  -4.000  -0.0395   0.03946   0.02998  -0.0637   0.8044   0.0949
  -3.750  -0.0108   0.03721   0.02728  -0.0635   0.7962   0.0981
  -3.500   0.0105   0.03601   0.02590  -0.0622   0.7853   0.1017
  -3.250   0.0480   0.03431   0.02376  -0.0632   0.7788   0.1107
  -3.000   0.0702   0.03331   0.02263  -0.0620   0.7668   0.1165
  -2.750   0.1008   0.03221   0.02130  -0.0619   0.7565   0.1246
  -2.500   0.1419   0.03107   0.02004  -0.0636   0.7481   0.1377
  -2.250   0.1741   0.03044   0.01932  -0.0640   0.7356   0.1506
  -2.000   0.2088   0.02982   0.01860  -0.0647   0.7236   0.1665
  -1.750   0.2462   0.02914   0.01779  -0.0656   0.7120   0.1869
  -1.500   0.2882   0.02832   0.01689  -0.0673   0.7008   0.2098
  -1.250   0.3215   0.02776   0.01624  -0.0676   0.6865   0.2402
  -1.000   0.3570   0.02707   0.01546  -0.0683   0.6719   0.2771
  -0.750   0.3926   0.02635   0.01466  -0.0692   0.6564   0.3202
  -0.500   0.4265   0.02567   0.01396  -0.0698   0.6401   0.3609
  -0.250   0.5850   0.02377   0.01337  -0.0950   0.6116   1.0000
   0.000   0.6099   0.02395   0.01320  -0.0942   0.5927   1.0000
   0.250   0.6321   0.02420   0.01313  -0.0929   0.5740   1.0000
   0.500   0.6524   0.02449   0.01314  -0.0914   0.5565   1.0000
   0.750   0.6703   0.02483   0.01325  -0.0895   0.5396   1.0000
   1.000   0.6897   0.02515   0.01334  -0.0879   0.5249   1.0000
   1.250   0.7085   0.02551   0.01350  -0.0863   0.5119   1.0000
   1.500   0.7283   0.02588   0.01369  -0.0849   0.5006   1.0000
   1.750   0.7503   0.02622   0.01381  -0.0839   0.4916   1.0000
   2.000   0.7715   0.02661   0.01402  -0.0828   0.4827   1.0000
   2.250   0.7934   0.02701   0.01424  -0.0819   0.4750   1.0000
   2.500   0.8156   0.02742   0.01450  -0.0810   0.4677   1.0000
   2.750   0.8395   0.02784   0.01476  -0.0805   0.4613   1.0000
   3.000   0.8607   0.02835   0.01519  -0.0796   0.4549   1.0000
   3.250   0.8875   0.02876   0.01547  -0.0796   0.4498   1.0000
   3.500   0.9100   0.02933   0.01598  -0.0789   0.4449   1.0000
   3.750   0.9309   0.02994   0.01656  -0.0781   0.4400   1.0000
   4.000   0.9562   0.03046   0.01701  -0.0779   0.4354   1.0000
   4.250   0.9819   0.03102   0.01748  -0.0779   0.4313   1.0000
   4.500   0.9974   0.03179   0.01831  -0.0762   0.4266   1.0000
   4.750   1.0176   0.03248   0.01900  -0.0753   0.4223   1.0000
   5.000   1.0432   0.03309   0.01958  -0.0753   0.4187   1.0000
   5.250   1.0677   0.03380   0.02026  -0.0751   0.4155   1.0000
   5.500   1.0776   0.03482   0.02142  -0.0727   0.4118   1.0000
   5.750   1.0916   0.03575   0.02245  -0.0709   0.4080   1.0000
   6.000   1.1119   0.03655   0.02326  -0.0702   0.4043   1.0000
   6.250   1.1397   0.03721   0.02389  -0.0706   0.4010   1.0000
   6.500   1.1462   0.03841   0.02523  -0.0678   0.3976   1.0000
   6.750   1.1474   0.03979   0.02679  -0.0642   0.3940   1.0000
   7.000   1.1563   0.04098   0.02808  -0.0619   0.3902   1.0000
   7.250   1.1785   0.04175   0.02887  -0.0615   0.3865   1.0000
   7.500   1.1993   0.04260   0.02974  -0.0609   0.3826   1.0000
   7.750   1.1743   0.04469   0.03206  -0.0538   0.3784   1.0000
   8.000   1.1675   0.04634   0.03382  -0.0496   0.3738   1.0000
   8.250   1.1942   0.04684   0.03436  -0.0498   0.3694   1.0000
   8.500   1.2015   0.04814   0.03573  -0.0476   0.3654   1.0000
   8.750   1.1406   0.05275   0.04060  -0.0387   0.3605   1.0000
   9.000   1.1222   0.05587   0.04384  -0.0352   0.3555   1.0000
   9.250   1.1632   0.05524   0.04324  -0.0361   0.3520   1.0000
   9.500   0.9759   0.07496   0.06320  -0.0288   0.3377   1.0000
   9.750   1.0094   0.07380   0.06210  -0.0280   0.3355   1.0000
  10.000   1.0509   0.07191   0.06027  -0.0272   0.3338   1.0000
  10.500   0.8958   0.09867   0.08719  -0.0301   0.3051   1.0000
  10.750   0.9154   0.09919   0.08777  -0.0294   0.3023   1.0000
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