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GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il)
Reynolds number: 50,000
Max Cl/Cd: 31.65 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe188-il-50000.txt
Download as CSV file: xf-goe188-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4159   0.10264   0.09642  -0.0153   1.0000   0.1639
  -7.500  -0.4009   0.09795   0.09176  -0.0135   1.0000   0.1743
  -7.250  -0.4147   0.09677   0.09072  -0.0204   1.0000   0.1790
  -7.000  -0.4031   0.09251   0.08653  -0.0183   1.0000   0.1924
  -6.750  -0.3952   0.08883   0.08292  -0.0175   1.0000   0.2057
  -6.500  -0.3908   0.08564   0.07981  -0.0181   1.0000   0.2201
  -6.250  -0.3908   0.08303   0.07727  -0.0204   1.0000   0.2362
  -6.000  -0.3793   0.07905   0.07340  -0.0161   1.0000   0.2565
  -5.750  -0.3829   0.07700   0.07143  -0.0183   1.0000   0.2801
  -5.500  -0.3785   0.07403   0.06859  -0.0150   1.0000   0.3092
  -5.250  -0.3691   0.07086   0.06555  -0.0083   1.0000   0.3449
  -5.000  -0.0153   0.04767   0.04137  -0.0159   1.0000   1.0000
  -4.750  -0.0027   0.04536   0.03913  -0.0173   1.0000   1.0000
  -4.500   0.0098   0.04312   0.03695  -0.0188   1.0000   1.0000
  -4.250   0.0223   0.04095   0.03486  -0.0202   1.0000   1.0000
  -4.000  -0.0301   0.04312   0.03726  -0.0067   1.0000   0.9616
  -3.750  -0.0838   0.04483   0.03922   0.0050   1.0000   0.9134
  -3.500  -0.1313   0.04536   0.04004   0.0132   1.0000   0.8588
  -3.250  -0.1771   0.04569   0.04068   0.0212   1.0000   0.8283
  -3.000  -0.2209   0.04591   0.04115   0.0296   1.0000   0.8141
  -2.750  -0.2630   0.04594   0.04137   0.0378   1.0000   0.8043
  -2.500  -0.3063   0.04576   0.04137   0.0465   1.0000   0.8019
  -2.250  -0.2660   0.04026   0.03503  -0.0091   1.0000   0.4978
  -2.000  -0.1381   0.03629   0.02840  -0.0370   1.0000   0.2185
  -1.750  -0.1027   0.03486   0.02624  -0.0378   1.0000   0.1757
  -1.500  -0.0719   0.03399   0.02467  -0.0377   1.0000   0.1497
  -1.250  -0.0448   0.03294   0.02322  -0.0375   1.0000   0.1351
  -1.000  -0.0191   0.03172   0.02179  -0.0375   1.0000   0.1259
  -0.750   0.0300   0.03084   0.02045  -0.0410   0.9917   0.1192
  -0.500   0.0862   0.02981   0.01910  -0.0457   0.9790   0.1194
  -0.250   0.1419   0.02897   0.01802  -0.0501   0.9658   0.1187
   0.000   0.1952   0.02834   0.01718  -0.0545   0.9514   0.1225
   0.250   0.2480   0.02766   0.01647  -0.0593   0.9360   0.1454
   0.500   0.2954   0.02483   0.01612  -0.0621   0.9218   1.0000
   0.750   0.3489   0.02520   0.01571  -0.0660   0.9047   1.0000
   1.000   0.4053   0.02540   0.01540  -0.0710   0.8879   1.0000
   1.250   0.4438   0.02576   0.01551  -0.0728   0.8676   1.0000
   1.500   0.4867   0.02598   0.01553  -0.0751   0.8488   1.0000
   1.750   0.5297   0.02608   0.01548  -0.0770   0.8312   1.0000
   2.000   0.5572   0.02662   0.01591  -0.0767   0.8099   1.0000
   2.250   0.5898   0.02692   0.01613  -0.0767   0.7912   1.0000
   2.500   0.6220   0.02716   0.01631  -0.0764   0.7740   1.0000
   2.750   0.6426   0.02797   0.01709  -0.0752   0.7531   1.0000
   3.000   0.6688   0.02846   0.01754  -0.0744   0.7356   1.0000
   3.250   0.6951   0.02894   0.01799  -0.0735   0.7195   1.0000
   3.500   0.7208   0.02944   0.01847  -0.0726   0.7040   1.0000
   3.750   0.7460   0.02997   0.01904  -0.0716   0.6891   1.0000
   4.000   0.7687   0.03073   0.01983  -0.0707   0.6738   1.0000
   4.250   0.7910   0.03153   0.02067  -0.0698   0.6588   1.0000
   4.500   0.8141   0.03226   0.02145  -0.0689   0.6444   1.0000
   4.750   0.8370   0.03296   0.02227  -0.0678   0.6300   1.0000
   5.000   0.8601   0.03363   0.02301  -0.0668   0.6157   1.0000
   5.250   0.8835   0.03426   0.02372  -0.0657   0.6019   1.0000
   5.500   0.9078   0.03482   0.02437  -0.0647   0.5886   1.0000
   5.750   0.9321   0.03540   0.02505  -0.0637   0.5757   1.0000
   6.000   0.9527   0.03648   0.02634  -0.0628   0.5622   1.0000
   6.250   0.9726   0.03763   0.02766  -0.0619   0.5489   1.0000
   6.750   1.0104   0.04026   0.03066  -0.0601   0.5225   1.0000
   7.000   1.0280   0.04178   0.03238  -0.0592   0.5095   1.0000
   7.250   1.0445   0.04348   0.03434  -0.0583   0.4967   1.0000
   7.500   1.0611   0.04513   0.03621  -0.0573   0.4838   1.0000
   7.750   1.0761   0.04701   0.03831  -0.0562   0.4710   1.0000
   8.000   1.0921   0.04869   0.04022  -0.0550   0.4577   1.0000
   8.250   1.1470   0.04400   0.03566  -0.0517   0.4336   1.0000
   8.500   1.1837   0.04144   0.03312  -0.0490   0.4062   1.0000
   8.750   1.2048   0.04143   0.03330  -0.0469   0.3821   1.0000
   9.000   1.2268   0.04120   0.03326  -0.0446   0.3552   1.0000
   9.250   1.2514   0.04033   0.03238  -0.0420   0.3209   1.0000
   9.500   1.2649   0.03997   0.03197  -0.0385   0.2784   1.0000
   9.750   1.2750   0.04069   0.03253  -0.0350   0.2377   1.0000
  10.000   1.2808   0.04211   0.03390  -0.0318   0.2060   1.0000
  10.250   1.2865   0.04375   0.03539  -0.0289   0.1790   1.0000
  10.500   1.2872   0.04567   0.03716  -0.0260   0.1548   1.0000
  10.750   1.2914   0.04808   0.03926  -0.0236   0.1326   1.0000
  11.000   1.2890   0.05102   0.04242  -0.0208   0.1181   1.0000
  11.250   1.2941   0.05451   0.04599  -0.0187   0.1059   1.0000
  11.500   1.3026   0.05807   0.04952  -0.0172   0.0952   1.0000
  11.750   1.2878   0.06158   0.05353  -0.0141   0.0927   1.0000
  12.000   1.2755   0.06548   0.05778  -0.0120   0.0900   1.0000
  12.250   1.2690   0.06964   0.06218  -0.0108   0.0871   1.0000
  12.500   1.0263   0.11724   0.11064  -0.0433   0.1808   1.0000
  12.750   1.0015   0.12781   0.12103  -0.0484   0.1826   1.0000
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