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GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il)
Reynolds number: 100,000
Max Cl/Cd: 59.46 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe137-il-100000-n5.txt
Download as CSV file: xf-goe137-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 137 (MVA H.15) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3323   0.09912   0.09444  -0.0250   1.0000   0.0453
  -8.000  -0.3366   0.09726   0.09269  -0.0288   1.0000   0.0470
  -7.750  -0.3379   0.09478   0.09030  -0.0321   1.0000   0.0474
  -7.500  -0.3348   0.09168   0.08725  -0.0353   1.0000   0.0476
  -7.250  -0.3318   0.08846   0.08409  -0.0376   1.0000   0.0477
  -7.000  -0.3289   0.08519   0.08086  -0.0394   1.0000   0.0477
  -6.750  -0.3262   0.08192   0.07763  -0.0406   1.0000   0.0478
  -6.500  -0.3237   0.07871   0.07444  -0.0411   1.0000   0.0478
  -6.250  -0.3244   0.07503   0.07089  -0.0329   0.9987   0.0426
  -6.000  -0.2927   0.06902   0.06479  -0.0421   0.9892   0.0414
  -5.750  -0.2583   0.06316   0.05881  -0.0513   0.9799   0.0420
  -5.500  -0.2208   0.05598   0.05142  -0.0611   0.9705   0.0388
  -5.250  -0.1801   0.04843   0.04353  -0.0704   0.9620   0.0373
  -5.000  -0.1461   0.04489   0.03977  -0.0748   0.9528   0.0408
  -4.750  -0.1107   0.03956   0.03404  -0.0796   0.9419   0.0419
  -4.500  -0.0750   0.03436   0.02831  -0.0835   0.9317   0.0430
  -4.250  -0.0382   0.02996   0.02316  -0.0865   0.9223   0.0464
  -4.000  -0.0065   0.02692   0.01947  -0.0877   0.9097   0.0473
  -3.750   0.0233   0.02452   0.01668  -0.0886   0.8969   0.0501
  -3.500   0.0533   0.02304   0.01491  -0.0892   0.8836   0.0526
  -3.250   0.0835   0.02148   0.01296  -0.0894   0.8702   0.0536
  -3.000   0.1130   0.02022   0.01139  -0.0894   0.8564   0.0549
  -2.750   0.1420   0.01922   0.01013  -0.0892   0.8424   0.0567
  -2.500   0.1706   0.01851   0.00916  -0.0890   0.8283   0.0602
  -2.250   0.1986   0.01779   0.00825  -0.0886   0.8143   0.0615
  -2.000   0.2261   0.01709   0.00743  -0.0882   0.8006   0.0625
  -1.750   0.2532   0.01650   0.00676  -0.0877   0.7872   0.0642
  -1.500   0.2804   0.01609   0.00625  -0.0873   0.7742   0.0666
  -1.250   0.3076   0.01577   0.00581  -0.0868   0.7616   0.0702
  -1.000   0.3348   0.01551   0.00544  -0.0864   0.7492   0.0756
  -0.750   0.3620   0.01527   0.00521  -0.0860   0.7367   0.0895
  -0.500   0.3891   0.01504   0.00506  -0.0857   0.7249   0.1379
  -0.250   0.4163   0.01471   0.00497  -0.0856   0.7137   0.2327
   0.000   0.4453   0.01275   0.00486  -0.0853   0.7035   1.0000
   0.250   0.4724   0.01290   0.00478  -0.0850   0.6919   1.0000
   0.500   0.4994   0.01305   0.00473  -0.0847   0.6809   1.0000
   0.750   0.5265   0.01321   0.00471  -0.0843   0.6705   1.0000
   1.000   0.5535   0.01338   0.00470  -0.0840   0.6601   1.0000
   1.250   0.5803   0.01355   0.00475  -0.0837   0.6483   1.0000
   1.500   0.6070   0.01373   0.00480  -0.0834   0.6366   1.0000
   1.750   0.6337   0.01390   0.00486  -0.0831   0.6251   1.0000
   2.000   0.6603   0.01408   0.00492  -0.0827   0.6134   1.0000
   2.250   0.6868   0.01426   0.00502  -0.0824   0.6011   1.0000
   2.500   0.7132   0.01445   0.00514  -0.0820   0.5882   1.0000
   2.750   0.7396   0.01464   0.00529  -0.0817   0.5757   1.0000
   3.000   0.7659   0.01484   0.00544  -0.0814   0.5631   1.0000
   3.250   0.7922   0.01504   0.00560  -0.0810   0.5509   1.0000
   3.500   0.8185   0.01526   0.00579  -0.0807   0.5399   1.0000
   3.750   0.8446   0.01549   0.00602  -0.0804   0.5282   1.0000
   4.000   0.8706   0.01572   0.00625  -0.0800   0.5157   1.0000
   4.250   0.8965   0.01596   0.00652  -0.0797   0.5034   1.0000
   4.500   0.9223   0.01622   0.00678  -0.0793   0.4915   1.0000
   4.750   0.9477   0.01648   0.00705  -0.0789   0.4785   1.0000
   5.000   0.9730   0.01676   0.00736  -0.0784   0.4655   1.0000
   5.250   0.9982   0.01707   0.00768  -0.0779   0.4537   1.0000
   5.500   1.0233   0.01739   0.00807  -0.0775   0.4414   1.0000
   5.750   1.0482   0.01772   0.00848  -0.0771   0.4294   1.0000
   6.000   1.0730   0.01808   0.00894  -0.0766   0.4178   1.0000
   6.250   1.0975   0.01846   0.00939  -0.0761   0.4062   1.0000
   6.500   1.1214   0.01886   0.00986  -0.0755   0.3933   1.0000
   6.750   1.1445   0.01927   0.01035  -0.0748   0.3758   1.0000
   7.000   1.1654   0.01974   0.01082  -0.0737   0.3501   1.0000
   7.250   1.1855   0.02028   0.01134  -0.0727   0.3211   1.0000
   7.500   1.2054   0.02089   0.01194  -0.0716   0.2920   1.0000
   7.750   1.2232   0.02167   0.01261  -0.0704   0.2513   1.0000
   8.000   1.2382   0.02272   0.01343  -0.0689   0.2086   1.0000
   8.250   1.2522   0.02392   0.01449  -0.0673   0.1795   1.0000
   8.500   1.2677   0.02500   0.01557  -0.0659   0.1593   1.0000
   8.750   1.2816   0.02622   0.01675  -0.0642   0.1107   1.0000
   9.250   1.2806   0.03093   0.02064  -0.0583   0.0290   1.0000
   9.500   1.2845   0.03258   0.02234  -0.0555   0.0258   1.0000
   9.750   1.2894   0.03418   0.02413  -0.0531   0.0242   1.0000
  10.000   1.2926   0.03599   0.02613  -0.0508   0.0228   1.0000
  10.250   1.2936   0.03807   0.02840  -0.0488   0.0214   1.0000
  10.500   1.2923   0.04048   0.03099  -0.0471   0.0202   1.0000
  10.750   1.2886   0.04329   0.03402  -0.0458   0.0194   1.0000
  11.000   1.2833   0.04645   0.03738  -0.0448   0.0188   1.0000
  11.250   1.2769   0.04995   0.04107  -0.0443   0.0184   1.0000
  11.500   1.2697   0.05370   0.04501  -0.0441   0.0181   1.0000
  11.750   1.2642   0.05738   0.04883  -0.0441   0.0179   1.0000
  12.000   1.2604   0.06093   0.05255  -0.0441   0.0177   1.0000
  12.250   1.2569   0.06449   0.05627  -0.0441   0.0175   1.0000
  12.500   1.2540   0.06798   0.05991  -0.0441   0.0173   1.0000
  12.750   1.2522   0.07136   0.06344  -0.0440   0.0171   1.0000
  13.000   1.2510   0.07468   0.06691  -0.0439   0.0167   1.0000
  13.250   1.2502   0.07803   0.07040  -0.0439   0.0163   1.0000
  13.500   1.2494   0.08144   0.07397  -0.0439   0.0158   1.0000
  13.750   1.2484   0.08495   0.07763  -0.0441   0.0153   1.0000
  14.000   1.2473   0.08857   0.08141  -0.0444   0.0149   1.0000
  14.250   1.2460   0.09232   0.08532  -0.0448   0.0146   1.0000
  14.500   1.2439   0.09629   0.08947  -0.0453   0.0145   1.0000
  14.750   1.2403   0.10063   0.09401  -0.0463   0.0144   1.0000
  15.000   1.2352   0.10539   0.09896  -0.0477   0.0143   1.0000
  15.250   1.2285   0.11061   0.10439  -0.0496   0.0142   1.0000
  15.500   1.2204   0.11627   0.11025  -0.0520   0.0142   1.0000
  15.750   1.2110   0.12240   0.11664  -0.0550   0.0142   1.0000
  16.000   1.2004   0.12903   0.12348  -0.0585   0.0142   1.0000
  16.250   1.1886   0.13628   0.13093  -0.0627   0.0142   1.0000
  16.500   1.1759   0.14415   0.13893  -0.0675   0.0143   1.0000
  16.750   1.1620   0.15277   0.14774  -0.0729   0.0144   1.0000
  17.000   1.1469   0.16235   0.15749  -0.0791   0.0146   1.0000
  17.250   1.1303   0.17324   0.16852  -0.0861   0.0149   1.0000
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