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GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il)
Reynolds number: 1,000,000
Max Cl/Cd: 116.37 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe188-il-1000000-n5.txt
Download as CSV file: xf-goe188-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2221   0.08007   0.07799  -0.0323   0.7908   0.0034
  -7.750  -0.3133   0.08980   0.08771  -0.0262   0.8118   0.0034
  -5.750  -0.2039   0.05825   0.05566  -0.0582   0.7134   0.0035
  -5.500  -0.1840   0.05482   0.05214  -0.0611   0.7029   0.0036
  -5.250  -0.1616   0.05137   0.04858  -0.0641   0.6931   0.0038
  -5.000  -0.1374   0.04783   0.04490  -0.0668   0.6825   0.0039
  -4.750  -0.1121   0.04439   0.04132  -0.0691   0.6719   0.0040
  -4.500  -0.0861   0.04109   0.03787  -0.0709   0.6630   0.0041
  -4.250  -0.0594   0.03793   0.03455  -0.0724   0.6554   0.0043
  -4.000  -0.0321   0.03492   0.03137  -0.0735   0.6490   0.0045
  -3.750  -0.0041   0.03208   0.02835  -0.0743   0.6420   0.0047
  -3.500   0.0266   0.02947   0.02552  -0.0744   0.6357   0.0052
  -3.250   0.0561   0.02700   0.02283  -0.0744   0.6292   0.0053
  -3.000   0.0845   0.02470   0.02030  -0.0745   0.6237   0.0053
  -2.750   0.1131   0.02248   0.01787  -0.0745   0.6179   0.0053
  -2.500   0.1395   0.01999   0.01514  -0.0750   0.6113   0.0048
  -2.250   0.1690   0.01786   0.01274  -0.0748   0.6051   0.0043
  -2.000   0.1987   0.01610   0.01071  -0.0745   0.5977   0.0044
  -1.750   0.2284   0.01462   0.00900  -0.0742   0.5913   0.0049
  -1.500   0.2580   0.01347   0.00764  -0.0739   0.5841   0.0052
  -1.250   0.2869   0.01218   0.00615  -0.0738   0.5769   0.0050
  -1.000   0.3157   0.01114   0.00494  -0.0737   0.5679   0.0049
  -0.750   0.3443   0.01021   0.00387  -0.0735   0.5573   0.0048
  -0.500   0.3726   0.00945   0.00298  -0.0734   0.5446   0.0050
  -0.250   0.4008   0.00898   0.00238  -0.0734   0.5301   0.0055
   0.000   0.4289   0.00879   0.00212  -0.0735   0.5118   0.0063
   0.250   0.4569   0.00878   0.00201  -0.0736   0.4895   0.0075
   0.750   0.5127   0.00863   0.00155  -0.0738   0.4414   0.0094
   1.000   0.5404   0.00870   0.00151  -0.0739   0.4203   0.0119
   1.250   0.5683   0.00876   0.00148  -0.0740   0.4040   0.0137
   1.500   0.5964   0.00881   0.00142  -0.0741   0.3918   0.0189
   1.750   0.6238   0.00773   0.00157  -0.0749   0.3799   0.5898
   2.250   0.6740   0.00694   0.00169  -0.0738   0.3611   1.0000
   2.500   0.7020   0.00706   0.00174  -0.0739   0.3530   1.0000
   2.750   0.7299   0.00719   0.00182  -0.0740   0.3451   1.0000
   3.000   0.7577   0.00732   0.00189  -0.0742   0.3371   1.0000
   3.250   0.7856   0.00744   0.00198  -0.0743   0.3310   1.0000
   3.500   0.8134   0.00756   0.00207  -0.0745   0.3249   1.0000
   3.750   0.8411   0.00770   0.00218  -0.0746   0.3190   1.0000
   4.000   0.8689   0.00782   0.00228  -0.0747   0.3131   1.0000
   4.250   0.8965   0.00797   0.00241  -0.0749   0.3068   1.0000
   4.500   0.9240   0.00811   0.00253  -0.0750   0.2988   1.0000
   4.750   0.9513   0.00829   0.00268  -0.0751   0.2902   1.0000
   5.000   0.9784   0.00846   0.00283  -0.0752   0.2792   1.0000
   5.250   1.0055   0.00865   0.00299  -0.0752   0.2680   1.0000
   5.500   1.0322   0.00887   0.00317  -0.0753   0.2544   1.0000
   5.750   1.0587   0.00912   0.00337  -0.0753   0.2400   1.0000
   6.000   1.0845   0.00944   0.00361  -0.0752   0.2206   1.0000
   6.250   1.1102   0.00976   0.00387  -0.0751   0.2018   1.0000
   6.500   1.1354   0.01014   0.00418  -0.0749   0.1828   1.0000
   6.750   1.1587   0.01073   0.00462  -0.0745   0.1533   1.0000
   7.000   1.1794   0.01162   0.00521  -0.0738   0.1005   1.0000
   7.250   1.1989   0.01263   0.00597  -0.0728   0.0554   1.0000
   7.500   1.2220   0.01319   0.00646  -0.0724   0.0405   1.0000
   7.750   1.2444   0.01379   0.00699  -0.0718   0.0263   1.0000
   8.000   1.2638   0.01472   0.00784  -0.0707   0.0054   1.0000
   8.250   1.2865   0.01524   0.00839  -0.0702   0.0036   1.0000
   8.500   1.3092   0.01573   0.00894  -0.0696   0.0028   1.0000
   8.750   1.3312   0.01626   0.00953  -0.0690   0.0023   1.0000
   9.000   1.3519   0.01690   0.01027  -0.0681   0.0020   1.0000
   9.250   1.3726   0.01751   0.01095  -0.0673   0.0018   1.0000
   9.500   1.3922   0.01817   0.01168  -0.0663   0.0016   1.0000
   9.750   1.4112   0.01884   0.01242  -0.0652   0.0014   1.0000
  10.000   1.4261   0.01982   0.01350  -0.0636   0.0012   1.0000
  10.250   1.4436   0.02051   0.01426  -0.0624   0.0011   1.0000
  10.500   1.4581   0.02137   0.01521  -0.0607   0.0010   1.0000
  10.750   1.4697   0.02231   0.01626  -0.0586   0.0009   1.0000
  11.000   1.4769   0.02330   0.01734  -0.0558   0.0009   1.0000
  11.250   1.4834   0.02440   0.01854  -0.0531   0.0008   1.0000
  11.500   1.4890   0.02567   0.01992  -0.0507   0.0008   1.0000
  11.750   1.4941   0.02710   0.02145  -0.0486   0.0007   1.0000
  12.000   1.4985   0.02875   0.02323  -0.0469   0.0007   1.0000
  12.250   1.5014   0.03067   0.02527  -0.0455   0.0007   1.0000
  12.500   1.5017   0.03303   0.02774  -0.0444   0.0006   1.0000
  12.750   1.4986   0.03589   0.03075  -0.0434   0.0006   1.0000
  13.000   1.4891   0.03963   0.03464  -0.0427   0.0006   1.0000
  13.250   1.4857   0.04285   0.03799  -0.0424   0.0005   1.0000
  13.500   1.4818   0.04625   0.04153  -0.0423   0.0005   1.0000
  13.750   1.4761   0.04996   0.04537  -0.0425   0.0005   1.0000
  14.000   1.4687   0.05402   0.04956  -0.0428   0.0005   1.0000
  14.250   1.4603   0.05828   0.05397  -0.0433   0.0005   1.0000
  14.500   1.4505   0.06288   0.05870  -0.0441   0.0005   1.0000
  14.750   1.4393   0.06790   0.06386  -0.0452   0.0005   1.0000
  15.000   1.4279   0.07314   0.06923  -0.0465   0.0005   1.0000
  15.250   1.4160   0.07865   0.07487  -0.0481   0.0005   1.0000
  15.500   1.4040   0.08434   0.08070  -0.0499   0.0005   1.0000
  15.750   1.3914   0.09022   0.08671  -0.0518   0.0005   1.0000
  16.000   1.3783   0.09626   0.09288  -0.0539   0.0004   1.0000
  16.250   1.3652   0.10244   0.09919  -0.0561   0.0004   1.0000
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