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Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Glenn Martin 4 (glennmartin4-il)
Reynolds number: 50,000
Max Cl/Cd: 22.01 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-glennmartin4-il-50000.txt
Download as CSV file: xf-glennmartin4-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3635   0.11483   0.10953  -0.0118   1.0000   0.2252
  -7.000  -0.3888   0.11373   0.10857  -0.0102   1.0000   0.2322
  -6.750  -0.4293   0.11336   0.10838  -0.0080   1.0000   0.2338
  -6.500  -0.4032   0.10914   0.10419  -0.0057   1.0000   0.2467
  -6.250  -0.4439   0.10877   0.10399  -0.0026   1.0000   0.2499
  -6.000  -0.4355   0.10562   0.10091   0.0000   1.0000   0.2617
  -5.750  -0.4665   0.10490   0.10033   0.0031   1.0000   0.2655
  -5.500  -0.5099   0.10454   0.10008   0.0046   1.0000   0.2683
  -5.250  -0.5015   0.10174   0.09739   0.0085   1.0000   0.2829
  -5.000  -0.5078   0.09974   0.09549   0.0115   1.0000   0.2924
  -4.750  -0.5470   0.09921   0.09499   0.0128   1.0000   0.3023
  -4.500  -0.5417   0.09691   0.09280   0.0167   1.0000   0.3169
  -4.250  -0.5164   0.09506   0.09090   0.0131   0.9833   0.3707
  -3.750   0.0169   0.08248   0.07747  -0.0179   1.0000   1.0000
  -3.500  -0.0274   0.07924   0.07443  -0.0115   0.9549   0.9008
  -3.250  -0.1149   0.07893   0.07431  -0.0008   0.9305   0.7991
  -3.000  -0.1994   0.07719   0.07275   0.0060   0.9108   0.7157
  -2.750  -0.2712   0.07538   0.07111   0.0136   0.8938   0.6800
  -2.500  -0.3375   0.07285   0.06867   0.0199   0.8784   0.6462
  -2.250  -0.3309   0.06078   0.05341  -0.0157   0.8632   0.1961
  -2.000  -0.3058   0.05801   0.05004  -0.0147   0.8498   0.1764
  -1.750  -0.2826   0.05658   0.04767  -0.0126   0.8370   0.1664
  -1.500  -0.2491   0.05431   0.04495  -0.0128   0.8257   0.1673
  -1.250  -0.2186   0.05272   0.04286  -0.0124   0.8126   0.1663
  -1.000  -0.1942   0.05137   0.04125  -0.0117   0.7989   0.1678
  -0.750  -0.1617   0.05000   0.03975  -0.0124   0.7850   0.1767
  -0.500   0.2480   0.04044   0.03262  -0.0802   0.7810   1.0000
  -0.250   0.2809   0.04029   0.03180  -0.0803   0.7662   1.0000
   0.000   0.3118   0.04013   0.03121  -0.0804   0.7521   1.0000
   0.250   0.3802   0.03817   0.02873  -0.0854   0.7458   1.0000
   0.500   0.4089   0.03800   0.02831  -0.0852   0.7311   1.0000
   0.750   0.4370   0.03796   0.02802  -0.0850   0.7169   1.0000
   1.000   0.4683   0.03779   0.02761  -0.0852   0.7036   1.0000
   1.250   0.5601   0.03510   0.02453  -0.0944   0.6974   1.0000
   1.500   0.5860   0.03537   0.02463  -0.0940   0.6830   1.0000
   1.750   0.6129   0.03569   0.02478  -0.0939   0.6692   1.0000
   2.000   0.6470   0.03581   0.02474  -0.0949   0.6568   1.0000
   2.250   0.7353   0.03450   0.02311  -0.1053   0.6462   1.0000
   2.500   0.7517   0.03534   0.02386  -0.1035   0.6338   1.0000
   2.750   0.7361   0.03718   0.02570  -0.0964   0.6223   1.0000
   3.000   0.8078   0.03670   0.02500  -0.1043   0.6126   1.0000
   3.250   0.7658   0.03932   0.02769  -0.0928   0.6027   1.0000
   3.500   0.7881   0.04031   0.02860  -0.0923   0.5946   1.0000
   3.750   0.7251   0.04448   0.03288  -0.0790   0.5852   1.0000
   4.000   0.5736   0.05631   0.04498  -0.0602   0.5717   1.0000
   4.250   0.6238   0.05506   0.04358  -0.0618   0.5666   1.0000
   4.500   0.7795   0.04801   0.03624  -0.0760   0.5639   1.0000
   4.750   0.4925   0.07151   0.06023  -0.0509   0.5558   1.0000
   5.000   0.4852   0.07505   0.06376  -0.0494   0.5529   1.0000
   5.250   0.5370   0.07428   0.06285  -0.0506   0.5468   1.0000
   5.500   0.5127   0.07935   0.06794  -0.0487   0.5464   1.0000
   5.750   0.5101   0.08301   0.07160  -0.0480   0.5470   1.0000
   6.000   0.3206   0.09973   0.08888  -0.0442   0.6915   1.0000
   6.250   0.3429   0.10209   0.09115  -0.0450   0.6827   1.0000
   6.500   0.3439   0.10370   0.09273  -0.0435   0.6743   1.0000
   6.750   0.3731   0.10647   0.09542  -0.0449   0.6653   1.0000
   7.000   0.3683   0.10759   0.09651  -0.0428   0.6551   1.0000
   7.250   0.4059   0.11130   0.10016  -0.0452   0.6478   1.0000
   7.500   0.3942   0.11166   0.10051  -0.0424   0.6365   1.0000
   7.750   0.4276   0.11555   0.10435  -0.0445   0.6310   1.0000
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