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GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il)
Reynolds number: 50,000
Max Cl/Cd: 40.29 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe187-il-50000-n5.txt
Download as CSV file: xf-goe187-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 187 (SCHTTE-LANZ 2U10) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3098   0.10560   0.09926  -0.0248   1.0000   0.0579
  -7.750  -0.3113   0.10398   0.09777  -0.0265   1.0000   0.0590
  -7.500  -0.3108   0.10241   0.09632  -0.0298   1.0000   0.0597
  -7.250  -0.3076   0.10067   0.09468  -0.0338   1.0000   0.0601
  -6.750  -0.2972   0.09210   0.08629  -0.0297   1.0000   0.0630
  -6.500  -0.2938   0.08926   0.08354  -0.0292   1.0000   0.0652
  -6.250  -0.2914   0.08678   0.08115  -0.0295   1.0000   0.0675
  -6.000  -0.2896   0.08455   0.07901  -0.0304   1.0000   0.0700
  -5.750  -0.2864   0.08301   0.07751  -0.0334   1.0000   0.0730
  -5.500  -0.2783   0.08230   0.07671  -0.0385   1.0000   0.0742
  -5.250  -0.2832   0.07795   0.07253  -0.0336   1.0000   0.0760
  -5.000  -0.2767   0.07487   0.06951  -0.0324   0.9977   0.0805
  -4.750  -0.2369   0.07041   0.06490  -0.0422   0.9880   0.0909
  -4.500  -0.2023   0.06629   0.06065  -0.0489   0.9788   0.1051
  -4.250  -0.1737   0.06228   0.05660  -0.0528   0.9696   0.1216
  -4.000  -0.1404   0.05870   0.05288  -0.0584   0.9599   0.1491
  -3.750  -0.1130   0.05509   0.04925  -0.0609   0.9513   0.1813
  -2.750   0.0933   0.04044   0.03256  -0.0839   0.9144   0.0727
  -2.500   0.1357   0.03769   0.02928  -0.0861   0.9030   0.0590
  -2.250   0.1740   0.03492   0.02618  -0.0882   0.8919   0.0567
  -2.000   0.2137   0.03258   0.02339  -0.0899   0.8816   0.0537
  -1.750   0.2520   0.03066   0.02096  -0.0908   0.8706   0.0498
  -1.500   0.2870   0.02933   0.01908  -0.0909   0.8582   0.0477
  -1.250   0.3198   0.02777   0.01719  -0.0911   0.8459   0.0483
  -1.000   0.3508   0.02643   0.01563  -0.0911   0.8334   0.0528
  -0.750   0.3824   0.02536   0.01424  -0.0907   0.8211   0.0550
  -0.500   0.4140   0.02442   0.01297  -0.0903   0.8088   0.0571
  -0.250   0.4439   0.02356   0.01189  -0.0899   0.7963   0.0653
   0.000   0.4735   0.02295   0.01100  -0.0895   0.7837   0.0730
   0.250   0.5023   0.02238   0.01026  -0.0891   0.7704   0.0846
   0.500   0.5312   0.02148   0.00978  -0.0892   0.7567   0.1824
   1.000   0.5853   0.01993   0.00910  -0.0874   0.7285   1.0000
   1.250   0.6117   0.02013   0.00896  -0.0867   0.7140   1.0000
   1.500   0.6381   0.02034   0.00892  -0.0861   0.6994   1.0000
   1.750   0.6643   0.02058   0.00893  -0.0855   0.6846   1.0000
   2.000   0.6903   0.02083   0.00899  -0.0849   0.6698   1.0000
   2.250   0.7162   0.02110   0.00910  -0.0843   0.6550   1.0000
   2.500   0.7420   0.02140   0.00926  -0.0838   0.6404   1.0000
   2.750   0.7676   0.02171   0.00948  -0.0832   0.6259   1.0000
   3.000   0.7932   0.02206   0.00974  -0.0827   0.6118   1.0000
   3.250   0.8186   0.02242   0.01005  -0.0823   0.5981   1.0000
   3.500   0.8438   0.02282   0.01043  -0.0818   0.5848   1.0000
   3.750   0.8691   0.02323   0.01082  -0.0814   0.5723   1.0000
   4.000   0.8944   0.02365   0.01124  -0.0810   0.5607   1.0000
   4.250   0.9203   0.02405   0.01165  -0.0806   0.5503   1.0000
   4.500   0.9450   0.02454   0.01219  -0.0802   0.5392   1.0000
   4.750   0.9695   0.02508   0.01281  -0.0798   0.5286   1.0000
   5.000   0.9949   0.02557   0.01340  -0.0794   0.5195   1.0000
   5.250   1.0198   0.02610   0.01402  -0.0790   0.5101   1.0000
   5.500   1.0435   0.02670   0.01475  -0.0785   0.4999   1.0000
   5.750   1.0677   0.02718   0.01532  -0.0779   0.4892   1.0000
   6.000   1.0915   0.02755   0.01581  -0.0771   0.4769   1.0000
   6.250   1.1145   0.02792   0.01627  -0.0762   0.4631   1.0000
   6.500   1.1370   0.02834   0.01678  -0.0752   0.4492   1.0000
   6.750   1.1595   0.02879   0.01741  -0.0743   0.4357   1.0000
   7.000   1.1808   0.02931   0.01808  -0.0732   0.4213   1.0000
   7.500   1.2206   0.03045   0.01959  -0.0708   0.3907   1.0000
   7.750   1.2386   0.03111   0.02047  -0.0694   0.3744   1.0000
   8.000   1.2568   0.03180   0.02149  -0.0681   0.3595   1.0000
   8.250   1.2749   0.03256   0.02252  -0.0667   0.3454   1.0000
   8.500   1.2916   0.03338   0.02364  -0.0652   0.3306   1.0000
   8.750   1.3068   0.03427   0.02486  -0.0636   0.3149   1.0000
   9.000   1.3183   0.03521   0.02611  -0.0615   0.2959   1.0000
   9.250   1.3208   0.03614   0.02715  -0.0585   0.2656   1.0000
   9.500   1.3179   0.03745   0.02840  -0.0554   0.2278   1.0000
   9.750   1.3152   0.03908   0.02994  -0.0523   0.1995   1.0000
  10.000   1.3122   0.04110   0.03188  -0.0497   0.1796   1.0000
  10.250   1.3081   0.04355   0.03432  -0.0477   0.1624   1.0000
  10.500   1.3011   0.04662   0.03740  -0.0462   0.1393   1.0000
  10.750   1.2954   0.04987   0.04087  -0.0454   0.1193   1.0000
  11.000   1.2864   0.05374   0.04476  -0.0450   0.1004   1.0000
  11.250   1.2733   0.05835   0.04931  -0.0452   0.0862   1.0000
  11.500   1.2625   0.06297   0.05401  -0.0456   0.0717   1.0000
  11.750   1.2530   0.06763   0.05879  -0.0462   0.0485   1.0000
  12.000   1.2389   0.07301   0.06413  -0.0474   0.0407   1.0000
  12.250   1.2258   0.07842   0.06954  -0.0486   0.0369   1.0000
  12.500   1.2144   0.08370   0.07490  -0.0498   0.0344   1.0000
  12.750   1.2032   0.08907   0.08037  -0.0512   0.0323   1.0000
  13.000   1.1922   0.09451   0.08589  -0.0526   0.0308   1.0000
  13.250   1.1814   0.10006   0.09151  -0.0543   0.0296   1.0000
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