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Glenn Martin 3 (glennmartin3-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Glenn Martin 3 (glennmartin3-il)
Reynolds number: 50,000
Max Cl/Cd: 29.07 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-glennmartin3-il-50000-n5.txt
Download as CSV file: xf-glennmartin3-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Glenn Martin 3                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4980   0.09662   0.09051  -0.0215   1.0000   0.0716
  -7.500  -0.5106   0.09377   0.08768  -0.0192   1.0000   0.0712
  -7.250  -0.5236   0.09063   0.08454  -0.0168   1.0000   0.0707
  -7.000  -0.5353   0.08748   0.08137  -0.0143   1.0000   0.0702
  -6.750  -0.5463   0.08416   0.07800  -0.0117   1.0000   0.0696
  -6.500  -0.5513   0.08060   0.07436  -0.0100   0.9986   0.0684
  -6.250  -0.5468   0.07614   0.06970  -0.0104   0.9929   0.0670
  -6.000  -0.5433   0.07161   0.06489  -0.0100   0.9870   0.0659
  -5.750  -0.5384   0.06801   0.06102  -0.0086   0.9811   0.0663
  -5.500  -0.5310   0.06480   0.05753  -0.0071   0.9752   0.0670
  -5.250  -0.5228   0.06170   0.05411  -0.0051   0.9694   0.0675
  -5.000  -0.5172   0.05866   0.05070  -0.0022   0.9630   0.0686
  -4.750  -0.5073   0.05578   0.04742   0.0003   0.9573   0.0687
  -4.500  -0.4976   0.05325   0.04449   0.0033   0.9509   0.0688
  -4.250  -0.4867   0.05087   0.04158   0.0064   0.9448   0.0706
  -4.000  -0.4722   0.04871   0.03883   0.0091   0.9386   0.0720
  -3.750  -0.4558   0.04686   0.03658   0.0113   0.9323   0.0733
  -3.500  -0.4313   0.04521   0.03468   0.0120   0.9260   0.0746
  -3.250  -0.4064   0.04387   0.03310   0.0126   0.9179   0.0762
  -3.000  -0.3697   0.04254   0.03145   0.0112   0.9106   0.0799
  -2.750  -0.3370   0.04106   0.02954   0.0107   0.9000   0.0825
  -2.500  -0.2900   0.03959   0.02773   0.0074   0.8908   0.0848
  -2.250  -0.2429   0.03849   0.02661   0.0037   0.8823   0.0907
  -2.000  -0.1851   0.03748   0.02536  -0.0020   0.8754   0.0971
  -1.750  -0.1236   0.03670   0.02455  -0.0089   0.8685   0.1050
  -1.500  -0.0612   0.03604   0.02386  -0.0157   0.8632   0.1197
  -1.250   0.1916   0.03411   0.02520  -0.0619   0.8743   1.0000
  -1.000   0.2282   0.03386   0.02459  -0.0633   0.8642   1.0000
  -0.750   0.2546   0.03368   0.02414  -0.0628   0.8509   1.0000
  -0.500   0.2859   0.03340   0.02362  -0.0632   0.8383   1.0000
  -0.250   0.3281   0.03281   0.02279  -0.0652   0.8277   1.0000
   0.000   0.3572   0.03235   0.02215  -0.0648   0.8116   1.0000
   0.250   0.3876   0.03178   0.02144  -0.0646   0.7948   1.0000
   0.500   0.4179   0.03112   0.02063  -0.0641   0.7770   1.0000
   1.000   0.4639   0.03033   0.01961  -0.0609   0.7331   1.0000
   1.250   0.4904   0.02986   0.01903  -0.0599   0.7103   1.0000
   1.500   0.5156   0.02947   0.01852  -0.0586   0.6830   1.0000
   1.750   0.5535   0.02868   0.01755  -0.0594   0.6580   1.0000
   2.000   0.5905   0.02807   0.01670  -0.0601   0.6278   1.0000
   2.250   0.6301   0.02754   0.01586  -0.0613   0.5931   1.0000
   2.500   0.6626   0.02743   0.01542  -0.0617   0.5574   1.0000
   2.750   0.6893   0.02759   0.01528  -0.0612   0.5244   1.0000
   3.000   0.7134   0.02791   0.01529  -0.0604   0.4959   1.0000
   3.250   0.7355   0.02834   0.01543  -0.0594   0.4711   1.0000
   3.500   0.7576   0.02883   0.01565  -0.0584   0.4507   1.0000
   3.750   0.7796   0.02936   0.01598  -0.0575   0.4324   1.0000
   4.000   0.8018   0.02991   0.01637  -0.0568   0.4158   1.0000
   4.250   0.8241   0.03048   0.01681  -0.0561   0.4003   1.0000
   4.500   0.8470   0.03106   0.01728  -0.0555   0.3860   1.0000
   4.750   0.8729   0.03161   0.01770  -0.0555   0.3744   1.0000
   5.000   0.8960   0.03220   0.01828  -0.0550   0.3623   1.0000
   5.250   0.9216   0.03278   0.01882  -0.0550   0.3526   1.0000
   5.500   0.9464   0.03336   0.01934  -0.0548   0.3430   1.0000
   5.750   0.9690   0.03399   0.01998  -0.0543   0.3343   1.0000
   6.000   0.9936   0.03461   0.02058  -0.0542   0.3267   1.0000
   6.250   1.0162   0.03527   0.02123  -0.0537   0.3195   1.0000
   6.500   1.0388   0.03599   0.02203  -0.0533   0.3132   1.0000
   6.750   1.0651   0.03664   0.02262  -0.0535   0.3078   1.0000
   7.000   1.0882   0.03748   0.02354  -0.0533   0.3028   1.0000
   7.250   1.1070   0.03832   0.02450  -0.0523   0.2976   1.0000
   7.500   1.1300   0.03912   0.02532  -0.0520   0.2931   1.0000
   7.750   1.1551   0.03990   0.02608  -0.0521   0.2890   1.0000
   8.000   1.1665   0.04098   0.02736  -0.0500   0.2845   1.0000
   8.250   1.1816   0.04199   0.02852  -0.0484   0.2804   1.0000
   8.500   1.2006   0.04293   0.02953  -0.0476   0.2770   1.0000
   8.750   1.2260   0.04386   0.03047  -0.0479   0.2742   1.0000
   9.000   1.2392   0.04513   0.03190  -0.0463   0.2715   1.0000
   9.250   1.2420   0.04666   0.03370  -0.0430   0.2684   1.0000
   9.500   1.2473   0.04812   0.03536  -0.0402   0.2655   1.0000
   9.750   1.2552   0.04948   0.03687  -0.0380   0.2627   1.0000
  10.000   1.2682   0.05068   0.03816  -0.0364   0.2600   1.0000
  10.250   1.2880   0.05181   0.03933  -0.0360   0.2576   1.0000
  10.500   1.2871   0.05361   0.04134  -0.0327   0.2553   1.0000
  10.750   1.2694   0.05619   0.04421  -0.0275   0.2534   1.0000
  11.000   1.2485   0.05918   0.04748  -0.0225   0.2513   1.0000
  11.250   1.2235   0.06267   0.05122  -0.0178   0.2493   1.0000
  11.500   1.1919   0.06705   0.05584  -0.0135   0.2474   1.0000
  11.750   1.1547   0.07240   0.06136  -0.0100   0.2453   1.0000
  12.000   1.1438   0.07592   0.06499  -0.0085   0.2427   1.0000
  12.250   1.1293   0.08021   0.06942  -0.0073   0.2410   1.0000
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