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GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il)
Reynolds number: 50,000
Max Cl/Cd: 39.15 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe188-il-50000-n5.txt
Download as CSV file: xf-goe188-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3471   0.10805   0.10165  -0.0246   1.0000   0.0736
  -8.000  -0.3523   0.10663   0.10037  -0.0276   1.0000   0.0746
  -7.750  -0.3542   0.10489   0.09874  -0.0325   1.0000   0.0751
  -7.500  -0.3382   0.09845   0.09234  -0.0267   1.0000   0.0788
  -7.250  -0.3334   0.09540   0.08936  -0.0271   1.0000   0.0823
  -7.000  -0.3315   0.09278   0.08684  -0.0294   1.0000   0.0860
  -6.750  -0.3326   0.09120   0.08535  -0.0354   1.0000   0.0890
  -6.500  -0.3297   0.08773   0.08199  -0.0362   1.0000   0.0906
  -6.250  -0.3241   0.08402   0.07838  -0.0323   1.0000   0.0948
  -6.000  -0.3226   0.08161   0.07605  -0.0328   1.0000   0.0998
  -5.750  -0.3245   0.08135   0.07568  -0.0390   1.0000   0.1042
  -5.500  -0.3257   0.07695   0.07154  -0.0331   1.0000   0.1072
  -5.250  -0.3269   0.07482   0.06947  -0.0311   1.0000   0.1123
  -5.000  -0.3119   0.07147   0.06607  -0.0351   0.9954   0.1221
  -4.750  -0.2839   0.06731   0.06184  -0.0398   0.9863   0.1384
  -4.500  -0.2549   0.06344   0.05781  -0.0453   0.9766   0.1651
  -4.250  -0.2314   0.05983   0.05422  -0.0472   0.9679   0.1976
  -3.500  -0.1784   0.05124   0.04585  -0.0442   0.9417   0.3828
  -3.000  -0.0041   0.04073   0.03274  -0.0738   0.9273   0.0719
  -2.750   0.0348   0.03804   0.02957  -0.0755   0.9185   0.0578
  -2.500   0.0790   0.03535   0.02631  -0.0781   0.9124   0.0500
  -2.250   0.1157   0.03359   0.02407  -0.0791   0.9020   0.0457
  -2.000   0.1534   0.03143   0.02152  -0.0806   0.8922   0.0439
  -1.750   0.1942   0.02963   0.01928  -0.0821   0.8833   0.0444
  -1.500   0.2290   0.02823   0.01751  -0.0826   0.8717   0.0452
  -1.250   0.2624   0.02691   0.01591  -0.0827   0.8602   0.0451
  -1.000   0.2949   0.02579   0.01451  -0.0824   0.8492   0.0452
  -0.750   0.3277   0.02488   0.01330  -0.0823   0.8387   0.0463
  -0.500   0.3585   0.02395   0.01218  -0.0822   0.8280   0.0512
  -0.250   0.3865   0.02341   0.01141  -0.0818   0.8157   0.0563
   0.000   0.4147   0.02303   0.01077  -0.0813   0.8035   0.0611
   0.250   0.4429   0.02256   0.01024  -0.0810   0.7915   0.0792
   0.500   0.4710   0.01989   0.00989  -0.0802   0.7806   1.0000
   0.750   0.4986   0.02006   0.00954  -0.0795   0.7686   1.0000
   1.000   0.5250   0.02024   0.00937  -0.0789   0.7559   1.0000
   1.250   0.5507   0.02045   0.00931  -0.0782   0.7424   1.0000
   1.500   0.5764   0.02067   0.00930  -0.0776   0.7289   1.0000
   1.750   0.6020   0.02088   0.00932  -0.0770   0.7152   1.0000
   2.000   0.6276   0.02108   0.00937  -0.0763   0.7013   1.0000
   2.250   0.6532   0.02129   0.00945  -0.0757   0.6874   1.0000
   2.500   0.6788   0.02150   0.00955  -0.0751   0.6733   1.0000
   2.750   0.7043   0.02172   0.00968  -0.0744   0.6589   1.0000
   3.000   0.7298   0.02196   0.00985  -0.0738   0.6445   1.0000
   3.250   0.7551   0.02221   0.01005  -0.0732   0.6300   1.0000
   3.500   0.7804   0.02249   0.01029  -0.0726   0.6154   1.0000
   3.750   0.8056   0.02279   0.01059  -0.0720   0.6008   1.0000
   4.000   0.8306   0.02312   0.01092  -0.0715   0.5865   1.0000
   4.250   0.8554   0.02347   0.01128  -0.0709   0.5722   1.0000
   4.500   0.8802   0.02385   0.01172  -0.0704   0.5584   1.0000
   4.750   0.9048   0.02425   0.01216  -0.0699   0.5449   1.0000
   5.000   0.9294   0.02466   0.01262  -0.0693   0.5318   1.0000
   5.250   0.9540   0.02507   0.01313  -0.0688   0.5192   1.0000
   5.500   0.9785   0.02547   0.01359  -0.0681   0.5064   1.0000
   5.750   1.0028   0.02586   0.01404  -0.0675   0.4935   1.0000
   6.000   1.0268   0.02629   0.01460  -0.0668   0.4806   1.0000
   6.250   1.0500   0.02682   0.01526  -0.0662   0.4676   1.0000
   6.500   1.0732   0.02743   0.01602  -0.0655   0.4554   1.0000
   6.750   1.0965   0.02807   0.01682  -0.0649   0.4442   1.0000
   7.000   1.1203   0.02869   0.01764  -0.0643   0.4336   1.0000
   7.250   1.1444   0.02934   0.01846  -0.0638   0.4231   1.0000
   7.500   1.1658   0.03019   0.01958  -0.0631   0.4118   1.0000
   7.750   1.1878   0.03105   0.02070  -0.0624   0.4011   1.0000
   8.000   1.2108   0.03184   0.02178  -0.0617   0.3908   1.0000
   8.250   1.2330   0.03262   0.02281  -0.0609   0.3791   1.0000
   8.500   1.2522   0.03333   0.02376  -0.0596   0.3641   1.0000
   8.750   1.2661   0.03411   0.02484  -0.0577   0.3458   1.0000
   9.000   1.2788   0.03478   0.02577  -0.0557   0.3262   1.0000
   9.250   1.2920   0.03552   0.02677  -0.0537   0.3087   1.0000
   9.500   1.3044   0.03638   0.02793  -0.0517   0.2924   1.0000
   9.750   1.3111   0.03743   0.02939  -0.0493   0.2735   1.0000
  10.000   1.3075   0.03855   0.03066  -0.0459   0.2459   1.0000
  10.250   1.2970   0.04018   0.03230  -0.0422   0.2144   1.0000
  10.500   1.2859   0.04249   0.03447  -0.0395   0.1821   1.0000
  10.750   1.2751   0.04555   0.03741  -0.0378   0.1524   1.0000
  11.000   1.2633   0.04931   0.04110  -0.0369   0.1201   1.0000
  11.250   1.2480   0.05380   0.04542  -0.0367   0.0961   1.0000
  11.500   1.2318   0.05878   0.05028  -0.0370   0.0810   1.0000
  11.750   1.2161   0.06399   0.05547  -0.0377   0.0713   1.0000
  12.000   1.2022   0.06924   0.06081  -0.0385   0.0626   1.0000
  12.250   1.1863   0.07488   0.06646  -0.0397   0.0574   1.0000
  12.500   1.1742   0.08018   0.07189  -0.0408   0.0507   1.0000
  12.750   1.1610   0.08571   0.07748  -0.0422   0.0466   1.0000
  13.000   1.1501   0.09097   0.08280  -0.0434   0.0425   1.0000
  13.250   1.1414   0.09602   0.08796  -0.0446   0.0387   1.0000
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