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Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Glenn Martin 4 (glennmartin4-il)
Reynolds number: 100,000
Max Cl/Cd: 40.85 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-glennmartin4-il-100000-n5.txt
Download as CSV file: xf-glennmartin4-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2547   0.09723   0.09290  -0.0571   0.9613   0.0356
  -7.750  -0.2590   0.09273   0.08844  -0.0599   0.9540   0.0350
  -7.500  -0.2695   0.08817   0.08390  -0.0624   0.9455   0.0342
  -7.250  -0.2833   0.08376   0.07947  -0.0631   0.9359   0.0340
  -7.000  -0.2887   0.07907   0.07473  -0.0644   0.9268   0.0348
  -6.500  -0.2926   0.06872   0.06413  -0.0659   0.9086   0.0350
  -6.250  -0.2948   0.06407   0.05932  -0.0647   0.8979   0.0351
  -6.000  -0.2920   0.05837   0.05330  -0.0640   0.8897   0.0362
  -5.750  -0.2898   0.05397   0.04861  -0.0617   0.8795   0.0362
  -5.500  -0.2901   0.04921   0.04345  -0.0582   0.8688   0.0366
  -5.250  -0.2874   0.04338   0.03686  -0.0546   0.8615   0.0384
  -5.000  -0.2763   0.04178   0.03513  -0.0519   0.8502   0.0393
  -4.750  -0.2516   0.04009   0.03326  -0.0516   0.8442   0.0410
  -4.500  -0.2424   0.03775   0.03056  -0.0479   0.8321   0.0419
  -4.250  -0.2203   0.03496   0.02723  -0.0463   0.8265   0.0443
  -4.000  -0.2080   0.03266   0.02434  -0.0426   0.8138   0.0464
  -3.750  -0.1846   0.03157   0.02317  -0.0415   0.8022   0.0481
  -3.500  -0.1541   0.02994   0.02125  -0.0413   0.7932   0.0502
  -3.250  -0.1306   0.02861   0.01955  -0.0398   0.7786   0.0535
  -3.000  -0.1033   0.02743   0.01815  -0.0392   0.7639   0.0559
  -2.750  -0.0730   0.02637   0.01693  -0.0392   0.7492   0.0587
  -2.500  -0.0400   0.02536   0.01563  -0.0396   0.7361   0.0628
  -2.250  -0.0046   0.02439   0.01455  -0.0408   0.7215   0.0670
  -2.000   0.0338   0.02337   0.01330  -0.0424   0.7061   0.0719
  -1.750   0.0721   0.02243   0.01227  -0.0442   0.6901   0.0791
  -1.500   0.1095   0.02157   0.01127  -0.0459   0.6732   0.0887
  -1.250   0.1447   0.02094   0.01050  -0.0471   0.6573   0.0989
  -1.000   0.1793   0.02051   0.00994  -0.0484   0.6420   0.1112
  -0.750   0.2141   0.02023   0.00954  -0.0498   0.6269   0.1274
  -0.500   0.2485   0.02000   0.00925  -0.0513   0.6128   0.1485
   0.000   0.5771   0.01940   0.01037  -0.1107   0.5648   1.0000
   0.250   0.5994   0.01953   0.01029  -0.1098   0.5530   1.0000
   0.500   0.6229   0.01969   0.01021  -0.1091   0.5420   1.0000
   0.750   0.6426   0.01985   0.01021  -0.1077   0.5307   1.0000
   1.000   0.6628   0.02003   0.01023  -0.1064   0.5197   1.0000
   1.250   0.6839   0.02022   0.01023  -0.1053   0.5098   1.0000
   1.500   0.7020   0.02042   0.01033  -0.1036   0.4992   1.0000
   1.750   0.7225   0.02064   0.01039  -0.1024   0.4900   1.0000
   2.000   0.7415   0.02085   0.01051  -0.1009   0.4809   1.0000
   2.250   0.7612   0.02108   0.01062  -0.0995   0.4723   1.0000
   2.500   0.7793   0.02132   0.01077  -0.0978   0.4631   1.0000
   2.750   0.7987   0.02157   0.01092  -0.0964   0.4553   1.0000
   3.000   0.8167   0.02183   0.01110  -0.0948   0.4468   1.0000
   3.250   0.8356   0.02211   0.01127  -0.0933   0.4392   1.0000
   3.500   0.8536   0.02238   0.01150  -0.0917   0.4315   1.0000
   3.750   0.8730   0.02268   0.01168  -0.0904   0.4250   1.0000
   4.000   0.8923   0.02298   0.01198  -0.0891   0.4186   1.0000
   4.250   0.9113   0.02329   0.01222  -0.0877   0.4127   1.0000
   4.500   0.9311   0.02362   0.01248  -0.0866   0.4074   1.0000
   4.750   0.9497   0.02396   0.01281  -0.0852   0.4014   1.0000
   5.000   0.9683   0.02429   0.01309  -0.0838   0.3962   1.0000
   5.250   0.9886   0.02466   0.01341  -0.0828   0.3916   1.0000
   5.500   1.0067   0.02503   0.01381  -0.0814   0.3865   1.0000
   5.750   1.0256   0.02541   0.01418  -0.0802   0.3821   1.0000
   6.000   1.0472   0.02579   0.01449  -0.0795   0.3786   1.0000
   6.250   1.0662   0.02621   0.01493  -0.0784   0.3747   1.0000
   6.500   1.0835   0.02665   0.01544  -0.0769   0.3700   1.0000
   6.750   1.1023   0.02708   0.01588  -0.0757   0.3663   1.0000
   7.000   1.1231   0.02749   0.01625  -0.0750   0.3627   1.0000
   7.250   1.1426   0.02797   0.01676  -0.0741   0.3594   1.0000
   7.500   1.1592   0.02849   0.01737  -0.0726   0.3559   1.0000
   7.750   1.1755   0.02899   0.01796  -0.0711   0.3521   1.0000
   8.000   1.1942   0.02947   0.01845  -0.0701   0.3488   1.0000
   8.250   1.2171   0.02994   0.01892  -0.0698   0.3459   1.0000
   8.500   1.2320   0.03053   0.01962  -0.0682   0.3428   1.0000
   8.750   1.2435   0.03118   0.02041  -0.0660   0.3391   1.0000
   9.000   1.2576   0.03178   0.02110  -0.0642   0.3358   1.0000
   9.250   1.2752   0.03234   0.02172  -0.0631   0.3326   1.0000
   9.500   1.2963   0.03284   0.02224  -0.0627   0.3298   1.0000
   9.750   1.3085   0.03356   0.02308  -0.0608   0.3267   1.0000
  10.000   1.3152   0.03442   0.02413  -0.0580   0.3235   1.0000
  10.250   1.3249   0.03521   0.02506  -0.0558   0.3202   1.0000
  10.500   1.3381   0.03590   0.02586  -0.0541   0.3170   1.0000
  10.750   1.3573   0.03646   0.02647  -0.0535   0.3141   1.0000
  11.000   1.3666   0.03726   0.02737  -0.0513   0.3107   1.0000
  11.250   1.3602   0.03851   0.02886  -0.0469   0.3066   1.0000
  11.500   1.3600   0.03935   0.02979  -0.0435   0.3007   1.0000
  11.750   1.3709   0.03983   0.03025  -0.0417   0.2953   1.0000
  12.000   1.3577   0.04158   0.03226  -0.0370   0.2906   1.0000
  12.250   1.3533   0.04286   0.03366  -0.0337   0.2848   1.0000
  12.500   1.3571   0.04374   0.03457  -0.0314   0.2790   1.0000
  12.750   1.3429   0.04606   0.03715  -0.0277   0.2743   1.0000
  13.000   1.3362   0.04795   0.03918  -0.0250   0.2688   1.0000
  13.250   1.3355   0.04945   0.04074  -0.0230   0.2633   1.0000
  13.500   1.3144   0.05293   0.04447  -0.0201   0.2573   1.0000
  13.750   1.3049   0.05547   0.04708  -0.0182   0.2500   1.0000
  14.000   1.2854   0.05948   0.05130  -0.0166   0.2445   1.0000
  14.250   1.2664   0.06379   0.05580  -0.0156   0.2393   1.0000
  14.500   1.2529   0.06757   0.05965  -0.0150   0.2327   1.0000
  14.750   1.2194   0.07431   0.06664  -0.0148   0.2290   1.0000
  15.000   1.1810   0.08211   0.07464  -0.0152   0.2266   1.0000
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