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GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 488 AIRFOIL (goe488-il)
Reynolds number: 200,000
Max Cl/Cd: 74.59 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe488-il-200000.txt
Download as CSV file: xf-goe488-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 488 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3232   0.08401   0.08063  -0.0284   1.0000   0.0477
  -8.250  -0.3229   0.08109   0.07774  -0.0280   1.0000   0.0491
  -8.000  -0.4353   0.08955   0.08614  -0.0312   1.0000   0.0449
  -7.750  -0.4172   0.08639   0.08296  -0.0260   1.0000   0.0469
  -7.500  -0.4204   0.08431   0.08093  -0.0244   1.0000   0.0481
  -7.250  -0.4243   0.08193   0.07859  -0.0238   1.0000   0.0490
  -7.000  -0.4287   0.07955   0.07625  -0.0233   1.0000   0.0501
  -6.750  -0.4331   0.07708   0.07382  -0.0230   1.0000   0.0515
  -6.500  -0.4365   0.07440   0.07115  -0.0236   1.0000   0.0535
  -6.250  -0.4307   0.07152   0.06809  -0.0305   1.0000   0.0563
  -6.000  -0.4237   0.06845   0.06485  -0.0318   1.0000   0.0566
  -5.750  -0.4280   0.06259   0.05909  -0.0301   1.0000   0.0577
  -5.500  -0.4238   0.06033   0.05686  -0.0275   1.0000   0.0588
  -5.250  -0.4168   0.05839   0.05493  -0.0256   1.0000   0.0606
  -5.000  -0.4063   0.05601   0.05249  -0.0253   1.0000   0.0636
  -4.750  -0.3799   0.05091   0.04681  -0.0307   1.0000   0.0707
  -4.500  -0.3713   0.04779   0.04379  -0.0292   1.0000   0.0720
  -4.250  -0.3477   0.04547   0.04148  -0.0303   0.9976   0.0743
  -4.000  -0.3063   0.04148   0.03694  -0.0356   0.9942   0.0854
  -3.750  -0.2811   0.03913   0.03469  -0.0368   0.9904   0.0880
  -3.500  -0.2415   0.03629   0.03137  -0.0406   0.9859   0.0999
  -3.250  -0.2082   0.03399   0.02914  -0.0430   0.9819   0.1032
  -3.000  -0.1730   0.03176   0.02659  -0.0454   0.9758   0.1156
  -2.750  -0.1355   0.03014   0.02480  -0.0481   0.9718   0.1298
  -2.500  -0.0884   0.02313   0.01624  -0.0487   0.9702   0.0704
  -2.250  -0.0606   0.02069   0.01359  -0.0488   0.9648   0.0678
  -2.000  -0.0230   0.01917   0.01179  -0.0505   0.9602   0.0667
  -1.750   0.0195   0.01820   0.01058  -0.0531   0.9569   0.0680
  -1.500   0.0502   0.01747   0.00971  -0.0534   0.9503   0.0689
  -1.250   0.0893   0.01659   0.00875  -0.0554   0.9455   0.0694
  -1.000   0.1335   0.01565   0.00778  -0.0584   0.9422   0.0709
  -0.750   0.1631   0.01487   0.00707  -0.0585   0.9341   0.0739
  -0.500   0.2067   0.01422   0.00649  -0.0614   0.9295   0.0796
  -0.250   0.2432   0.01364   0.00599  -0.0628   0.9227   0.0909
   0.000   0.2810   0.01280   0.00554  -0.0645   0.9170   0.1605
   0.250   0.3715   0.01039   0.00539  -0.0774   0.9216   1.0000
   0.500   0.4113   0.01017   0.00507  -0.0794   0.9154   1.0000
   0.750   0.4433   0.01000   0.00484  -0.0798   0.9061   1.0000
   1.000   0.4821   0.00972   0.00451  -0.0814   0.8986   1.0000
   1.250   0.5088   0.00958   0.00434  -0.0806   0.8863   1.0000
   1.500   0.5361   0.00944   0.00417  -0.0799   0.8734   1.0000
   1.750   0.5633   0.00929   0.00399  -0.0791   0.8587   1.0000
   2.000   0.5907   0.00913   0.00379  -0.0783   0.8408   1.0000
   2.250   0.6140   0.00901   0.00362  -0.0766   0.8141   1.0000
   2.500   0.6372   0.00893   0.00344  -0.0748   0.7790   1.0000
   2.750   0.6592   0.00894   0.00333  -0.0729   0.7316   1.0000
   3.000   0.6803   0.00912   0.00318  -0.0707   0.6583   1.0000
   3.250   0.6973   0.00965   0.00323  -0.0681   0.5783   1.0000
   3.500   0.7135   0.01024   0.00342  -0.0655   0.5036   1.0000
   3.750   0.7314   0.01079   0.00367  -0.0635   0.4551   1.0000
   4.000   0.7514   0.01127   0.00396  -0.0619   0.4245   1.0000
   4.250   0.7725   0.01173   0.00427  -0.0606   0.4031   1.0000
   4.500   0.7948   0.01212   0.00458  -0.0595   0.3851   1.0000
   4.750   0.8174   0.01250   0.00492  -0.0585   0.3696   1.0000
   5.000   0.8399   0.01286   0.00526  -0.0574   0.3527   1.0000
   5.250   0.8622   0.01322   0.00559  -0.0564   0.3351   1.0000
   5.500   0.8841   0.01357   0.00590  -0.0553   0.3165   1.0000
   5.750   0.9063   0.01387   0.00620  -0.0542   0.2965   1.0000
   6.000   0.9288   0.01413   0.00651  -0.0532   0.2765   1.0000
   6.250   0.9509   0.01443   0.00680  -0.0521   0.2555   1.0000
   6.500   0.9730   0.01472   0.00707  -0.0511   0.2248   1.0000
   6.750   0.9932   0.01523   0.00741  -0.0498   0.1843   1.0000
   7.000   1.0119   0.01598   0.00798  -0.0484   0.1442   1.0000
   7.250   1.0261   0.01738   0.00888  -0.0464   0.0679   1.0000
   7.500   1.0380   0.01910   0.01043  -0.0438   0.0432   1.0000
   7.750   1.0570   0.01991   0.01133  -0.0422   0.0362   1.0000
   8.000   1.0723   0.02106   0.01254  -0.0401   0.0327   1.0000
   8.250   1.0887   0.02206   0.01365  -0.0382   0.0307   1.0000
   8.500   1.1040   0.02316   0.01486  -0.0361   0.0292   1.0000
   8.750   1.1184   0.02438   0.01614  -0.0340   0.0280   1.0000
   9.000   1.1320   0.02581   0.01762  -0.0319   0.0270   1.0000
   9.250   1.1449   0.02816   0.02000  -0.0299   0.0258   1.0000
   9.500   1.1625   0.02945   0.02144  -0.0284   0.0250   1.0000
   9.750   1.1798   0.03118   0.02334  -0.0269   0.0243   1.0000
  10.000   1.1968   0.03332   0.02571  -0.0254   0.0239   1.0000
  10.250   1.2124   0.03576   0.02841  -0.0238   0.0238   1.0000
  10.500   1.2245   0.03850   0.03145  -0.0219   0.0238   1.0000
  10.750   1.2318   0.04158   0.03487  -0.0195   0.0240   1.0000
  11.000   1.2340   0.04484   0.03845  -0.0167   0.0243   1.0000
  11.250   1.2302   0.04809   0.04200  -0.0134   0.0247   1.0000
  11.500   1.2218   0.05156   0.04574  -0.0100   0.0250   1.0000
  11.750   1.2105   0.05560   0.05003  -0.0070   0.0254   1.0000
  12.000   1.2084   0.05936   0.05397  -0.0052   0.0260   1.0000
  12.250   1.1980   0.06120   0.05605  -0.0025   0.0265   1.0000
  12.500   1.1669   0.06532   0.06059  -0.0006   0.0274   1.0000
  12.750   1.1293   0.07150   0.06714  -0.0014   0.0281   1.0000
  13.000   1.0992   0.07825   0.07414  -0.0043   0.0284   1.0000
  13.250   1.0720   0.08582   0.08190  -0.0091   0.0286   1.0000
  13.500   1.0454   0.09465   0.09090  -0.0155   0.0286   1.0000
  13.750   1.0135   0.10633   0.10272  -0.0243   0.0287   1.0000
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