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Glenn Martin 2 (glennmartin2-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Glenn Martin 2 (glennmartin2-il)
Reynolds number: 50,000
Max Cl/Cd: 24.69 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-glennmartin2-il-50000.txt
Download as CSV file: xf-glennmartin2-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3283   0.11611   0.11082  -0.0130   1.0000   0.1950
  -8.000  -0.3581   0.11655   0.11140  -0.0110   1.0000   0.1966
  -7.750  -0.3931   0.11717   0.11219  -0.0083   1.0000   0.1972
  -7.500  -0.3589   0.11081   0.10582  -0.0064   1.0000   0.2059
  -7.250  -0.3817   0.11024   0.10536  -0.0038   1.0000   0.2095
  -7.000  -0.4136   0.11033   0.10556  -0.0019   1.0000   0.2121
  -6.750  -0.4417   0.11032   0.10561  -0.0022   1.0000   0.2134
  -6.500  -0.4221   0.10509   0.10045   0.0024   1.0000   0.2213
  -6.250  -0.4406   0.10401   0.09942   0.0029   1.0000   0.2276
  -6.000  -0.4577   0.10250   0.09795   0.0020   1.0000   0.2308
  -5.750  -0.4493   0.09873   0.09425   0.0061   1.0000   0.2382
  -5.500  -0.4675   0.09817   0.09364   0.0031   1.0000   0.2464
  -5.250  -0.4603   0.09387   0.08944   0.0076   1.0000   0.2518
  -5.000  -0.4588   0.09164   0.08715   0.0046   0.9973   0.2634
  -4.750  -0.4182   0.08687   0.08232  -0.0010   0.9817   0.2816
  -4.500  -0.3905   0.08330   0.07867  -0.0047   0.9672   0.3047
  -4.250  -0.3669   0.07961   0.07491  -0.0081   0.9530   0.3273
  -4.000  -0.3439   0.07670   0.07188  -0.0112   0.9380   0.3564
  -3.750  -0.3198   0.07268   0.06789  -0.0110   0.9237   0.3831
  -3.500  -0.3035   0.06931   0.06456  -0.0091   0.9093   0.4310
  -3.250  -0.2888   0.06606   0.06134  -0.0066   0.8947   0.4822
  -3.000  -0.1657   0.06059   0.05391  -0.0384   0.8749   0.2281
  -2.750  -0.1231   0.05594   0.04849  -0.0417   0.8599   0.1957
  -2.500  -0.0859   0.05296   0.04512  -0.0433   0.8431   0.1906
  -2.250  -0.0468   0.05055   0.04218  -0.0448   0.8257   0.1944
  -2.000  -0.0054   0.04808   0.03903  -0.0461   0.8086   0.1978
  -1.750   0.0373   0.04634   0.03709  -0.0476   0.7909   0.2115
  -1.500   0.0829   0.04448   0.03489  -0.0493   0.7739   0.2279
  -1.250   0.1289   0.04277   0.03300  -0.0511   0.7574   0.2512
  -1.000   0.1751   0.04107   0.03101  -0.0527   0.7415   0.2799
  -0.750   0.2120   0.04009   0.02980  -0.0536   0.7204   0.3085
  -0.500   0.3229   0.03570   0.02561  -0.0655   0.7120   0.4154
  -0.250   0.5615   0.03041   0.02123  -0.1009   0.6986   1.0000
   0.000   0.6078   0.02984   0.02027  -0.1030   0.6827   1.0000
   0.250   0.6481   0.02957   0.01967  -0.1043   0.6671   1.0000
   0.500   0.6796   0.02972   0.01955  -0.1045   0.6523   1.0000
   0.750   0.7049   0.03020   0.01981  -0.1039   0.6389   1.0000
   1.000   0.7378   0.03051   0.01988  -0.1045   0.6281   1.0000
   1.250   0.7604   0.03119   0.02039  -0.1037   0.6173   1.0000
   1.500   0.7655   0.03253   0.02167  -0.1003   0.6069   1.0000
   1.750   0.8055   0.03263   0.02153  -0.1021   0.5989   1.0000
   2.000   0.7899   0.03478   0.02375  -0.0958   0.5893   1.0000
   2.250   0.8293   0.03491   0.02368  -0.0974   0.5827   1.0000
   2.500   0.7949   0.03804   0.02693  -0.0890   0.5747   1.0000
   2.750   0.8097   0.03928   0.02809  -0.0874   0.5689   1.0000
   3.000   0.8126   0.04112   0.02990  -0.0844   0.5635   1.0000
   3.250   0.6662   0.05129   0.04030  -0.0661   0.5552   1.0000
   3.500   0.7285   0.04961   0.03846  -0.0688   0.5513   1.0000
   3.750   0.6083   0.06178   0.05079  -0.0601   0.5468   1.0000
   4.000   0.5805   0.06710   0.05612  -0.0581   0.5465   1.0000
   4.250   0.5662   0.07128   0.06028  -0.0567   0.5463   1.0000
   4.500   0.5580   0.07499   0.06397  -0.0557   0.5465   1.0000
   4.750   0.5601   0.07827   0.06722  -0.0554   0.5481   1.0000
   5.000   0.4141   0.09424   0.08367  -0.0568   0.6946   1.0000
   5.250   0.4080   0.09499   0.08438  -0.0543   0.6849   1.0000
   5.500   0.4410   0.09854   0.08783  -0.0563   0.6794   1.0000
   5.750   0.4331   0.09918   0.08845  -0.0537   0.6687   1.0000
   6.000   0.4589   0.10243   0.09162  -0.0549   0.6626   1.0000
   6.250   0.4602   0.10357   0.09274  -0.0533   0.6513   1.0000
   6.500   0.4726   0.10617   0.09529  -0.0532   0.6447   1.0000
   6.750   0.4893   0.10836   0.09744  -0.0532   0.6335   1.0000
   7.000   0.4898   0.11020   0.09926  -0.0520   0.6249   1.0000
   7.250   0.5163   0.11334   0.10237  -0.0531   0.6162   1.0000
   7.500   0.5118   0.11476   0.10378  -0.0515   0.6055   1.0000
   7.750   0.5486   0.11916   0.10816  -0.0535   0.5986   1.0000
   8.000   0.5344   0.11961   0.10861  -0.0512   0.5873   1.0000
   8.250   0.5590   0.12353   0.11251  -0.0523   0.5811   1.0000
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