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Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Glenn Martin 4 (glennmartin4-il)
Reynolds number: 50,000
Max Cl/Cd: 27.83 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-glennmartin4-il-50000-n5.txt
Download as CSV file: xf-glennmartin4-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3486   0.12003   0.11449  -0.0223   1.0000   0.1085
  -7.750  -0.3636   0.11789   0.11246  -0.0220   1.0000   0.1102
  -7.500  -0.3792   0.11511   0.10974  -0.0302   0.9920   0.1122
  -7.000  -0.3706   0.09992   0.09439  -0.0395   0.9774   0.0631
  -6.750  -0.3632   0.09563   0.09007  -0.0422   0.9691   0.0626
  -6.500  -0.3612   0.09085   0.08520  -0.0449   0.9589   0.0628
  -6.250  -0.3548   0.08658   0.08087  -0.0463   0.9486   0.0622
  -6.000  -0.3528   0.08151   0.07561  -0.0479   0.9370   0.0628
  -5.750  -0.3439   0.07733   0.07130  -0.0486   0.9260   0.0622
  -5.500  -0.3358   0.07284   0.06660  -0.0489   0.9149   0.0619
  -5.250  -0.3244   0.06840   0.06189  -0.0492   0.9045   0.0617
  -5.000  -0.3142   0.06412   0.05723  -0.0486   0.8932   0.0622
  -4.750  -0.3082   0.06013   0.05272  -0.0465   0.8800   0.0634
  -4.500  -0.2942   0.05757   0.05003  -0.0452   0.8679   0.0650
  -4.250  -0.2728   0.05470   0.04687  -0.0449   0.8588   0.0670
  -4.000  -0.2601   0.05202   0.04382  -0.0426   0.8460   0.0676
  -3.750  -0.2460   0.04969   0.04107  -0.0403   0.8331   0.0702
  -3.500  -0.2255   0.04693   0.03755  -0.0384   0.8239   0.0732
  -3.250  -0.2053   0.04478   0.03509  -0.0368   0.8121   0.0752
  -3.000  -0.1844   0.04308   0.03316  -0.0354   0.7995   0.0771
  -2.750  -0.1530   0.04116   0.03082  -0.0353   0.7913   0.0826
  -2.500  -0.1281   0.03952   0.02868  -0.0341   0.7790   0.0861
  -2.250  -0.0998   0.03798   0.02700  -0.0338   0.7664   0.0894
  -2.000  -0.0584   0.03623   0.02491  -0.0354   0.7586   0.0966
  -1.750  -0.0222   0.03493   0.02350  -0.0365   0.7462   0.1040
  -1.500   0.0235   0.03369   0.02196  -0.0393   0.7341   0.1131
  -1.250   0.0792   0.03236   0.02054  -0.0442   0.7254   0.1309
  -1.000   0.1227   0.03139   0.01946  -0.0469   0.7134   0.1522
  -0.750   0.1584   0.03059   0.01862  -0.0483   0.7005   0.1811
  -0.500   0.3853   0.02748   0.01787  -0.0874   0.6904   1.0000
  -0.250   0.4207   0.02718   0.01708  -0.0885   0.6760   1.0000
   0.000   0.4558   0.02696   0.01644  -0.0897   0.6623   1.0000
   0.250   0.4863   0.02691   0.01603  -0.0901   0.6470   1.0000
   0.500   0.5155   0.02696   0.01575  -0.0903   0.6326   1.0000
   0.750   0.5442   0.02705   0.01554  -0.0906   0.6184   1.0000
   1.000   0.5733   0.02719   0.01538  -0.0909   0.6050   1.0000
   1.250   0.6052   0.02732   0.01522  -0.0918   0.5929   1.0000
   1.500   0.6305   0.02759   0.01527  -0.0915   0.5798   1.0000
   1.750   0.6530   0.02793   0.01543  -0.0907   0.5674   1.0000
   2.000   0.6808   0.02821   0.01551  -0.0910   0.5566   1.0000
   2.250   0.7067   0.02853   0.01564  -0.0909   0.5455   1.0000
   2.500   0.7269   0.02896   0.01597  -0.0897   0.5346   1.0000
   2.750   0.7580   0.02924   0.01604  -0.0906   0.5253   1.0000
   3.000   0.7738   0.02975   0.01651  -0.0888   0.5152   1.0000
   3.250   0.8009   0.03012   0.01673  -0.0889   0.5064   1.0000
   3.500   0.8184   0.03064   0.01721  -0.0874   0.4977   1.0000
   3.750   0.8446   0.03105   0.01750  -0.0875   0.4898   1.0000
   4.000   0.8601   0.03166   0.01812  -0.0857   0.4822   1.0000
   4.250   0.8907   0.03200   0.01831  -0.0866   0.4756   1.0000
   4.500   0.8982   0.03275   0.01914  -0.0833   0.4680   1.0000
   4.750   0.9209   0.03322   0.01953  -0.0828   0.4613   1.0000
   5.000   0.9385   0.03384   0.02014  -0.0814   0.4555   1.0000
   5.250   0.9500   0.03459   0.02095  -0.0790   0.4489   1.0000
   5.500   0.9752   0.03507   0.02137  -0.0790   0.4440   1.0000
   5.750   0.9871   0.03588   0.02223  -0.0768   0.4388   1.0000
   6.000   0.9953   0.03679   0.02322  -0.0739   0.4332   1.0000
   6.250   1.0167   0.03734   0.02374  -0.0732   0.4286   1.0000
   6.500   1.0329   0.03809   0.02452  -0.0718   0.4240   1.0000
   6.750   1.0309   0.03936   0.02593  -0.0675   0.4188   1.0000
   7.000   1.0449   0.04018   0.02681  -0.0657   0.4142   1.0000
   7.250   1.0724   0.04063   0.02723  -0.0662   0.4105   1.0000
   7.500   1.0631   0.04227   0.02903  -0.0610   0.4060   1.0000
   7.750   1.0566   0.04393   0.03083  -0.0565   0.4014   1.0000
   8.000   1.0705   0.04479   0.03173  -0.0550   0.3972   1.0000
   8.250   1.1031   0.04501   0.03193  -0.0561   0.3939   1.0000
   8.500   1.0617   0.04837   0.03557  -0.0474   0.3892   1.0000
   8.750   1.0367   0.05143   0.03880  -0.0418   0.3844   1.0000
   9.000   1.0477   0.05259   0.04002  -0.0403   0.3808   1.0000
   9.250   1.0876   0.05218   0.03959  -0.0418   0.3780   1.0000
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