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GOE 425 AIRFOIL (goe425-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 425 AIRFOIL (goe425-il)
Reynolds number: 200,000
Max Cl/Cd: 69.77 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe425-il-200000.txt
Download as CSV file: xf-goe425-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 425 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2435   0.10201   0.09852  -0.0530   0.8911   0.0738
 -10.000  -0.2738   0.09459   0.09106  -0.0622   0.8664   0.0775
  -9.750  -0.2560   0.09321   0.08955  -0.0586   0.8448   0.0783
  -9.500  -0.2434   0.09146   0.08769  -0.0571   0.8275   0.0797
  -9.250  -0.2359   0.08907   0.08521  -0.0573   0.8134   0.0819
  -9.000  -0.3256   0.07491   0.07081  -0.0854   0.8031   0.0875
  -8.750  -0.2596   0.07735   0.07345  -0.0696   0.7920   0.0889
  -8.500  -0.2407   0.07676   0.07275  -0.0662   0.7817   0.0904
  -8.250  -0.2311   0.07438   0.07035  -0.0668   0.7715   0.0929
  -8.000  -0.2965   0.06074   0.05618  -0.0893   0.7652   0.1001
  -7.750  -0.2683   0.05842   0.05405  -0.0873   0.7563   0.1015
  -7.500  -0.2496   0.05679   0.05241  -0.0863   0.7479   0.1032
  -7.250  -0.2371   0.05432   0.04985  -0.0870   0.7399   0.1064
  -7.000  -0.2441   0.04881   0.04380  -0.0913   0.7329   0.1147
  -6.750  -0.2235   0.04670   0.04170  -0.0908   0.7260   0.1167
  -6.500  -0.2056   0.04462   0.03955  -0.0909   0.7179   0.1201
  -6.250  -0.2069   0.03239   0.02558  -0.0914   0.7139   0.0786
  -6.000  -0.1862   0.02822   0.02058  -0.0899   0.7087   0.0668
  -5.750  -0.1627   0.02612   0.01833  -0.0896   0.7014   0.0653
  -5.500  -0.1382   0.02437   0.01629  -0.0890   0.6954   0.0639
  -5.250  -0.1127   0.02297   0.01458  -0.0885   0.6899   0.0630
  -5.000  -0.0867   0.02182   0.01326  -0.0881   0.6831   0.0627
  -4.750  -0.0602   0.02099   0.01227  -0.0878   0.6774   0.0633
  -4.500  -0.0335   0.02030   0.01144  -0.0874   0.6724   0.0642
  -4.250  -0.0069   0.01960   0.01069  -0.0871   0.6664   0.0648
  -4.000   0.0197   0.01894   0.00997  -0.0868   0.6613   0.0653
  -3.750   0.0465   0.01840   0.00933  -0.0864   0.6571   0.0659
  -3.500   0.0724   0.01793   0.00885  -0.0860   0.6519   0.0667
  -3.250   0.0984   0.01749   0.00839  -0.0856   0.6466   0.0677
  -3.000   0.1240   0.01698   0.00788  -0.0852   0.6423   0.0695
  -2.750   0.1506   0.01673   0.00758  -0.0850   0.6388   0.0726
  -2.500   0.1768   0.01651   0.00740  -0.0847   0.6339   0.0762
  -2.250   0.2032   0.01627   0.00719  -0.0845   0.6293   0.0808
  -2.000   0.2305   0.01608   0.00698  -0.0843   0.6253   0.0891
  -1.750   0.2579   0.01586   0.00674  -0.0841   0.6220   0.1140
  -1.500   0.2795   0.01487   0.00659  -0.0836   0.6180   0.2989
  -1.250   0.3013   0.01439   0.00681  -0.0827   0.6136   0.4969
  -1.000   0.3271   0.01434   0.00687  -0.0821   0.6097   0.5571
  -0.750   0.3535   0.01431   0.00690  -0.0816   0.6064   0.6019
  -0.500   0.3798   0.01436   0.00699  -0.0811   0.6032   0.6365
  -0.250   0.4047   0.01437   0.00714  -0.0805   0.5988   0.6720
   0.000   0.4300   0.01431   0.00720  -0.0798   0.5948   0.7085
   0.250   0.4553   0.01419   0.00722  -0.0789   0.5914   0.7542
   0.500   0.4820   0.01403   0.00726  -0.0781   0.5885   0.8268
   0.750   0.5372   0.01405   0.00746  -0.0833   0.5841   0.9320
   1.000   0.5964   0.01418   0.00754  -0.0900   0.5793   0.9941
   1.250   0.6292   0.01430   0.00754  -0.0913   0.5756   1.0000
   1.500   0.6553   0.01444   0.00753  -0.0911   0.5726   1.0000
   1.750   0.6809   0.01468   0.00767  -0.0909   0.5694   1.0000
   2.000   0.7040   0.01493   0.00794  -0.0902   0.5652   1.0000
   2.250   0.7288   0.01513   0.00810  -0.0897   0.5613   1.0000
   2.500   0.7549   0.01529   0.00818  -0.0895   0.5579   1.0000
   2.750   0.7822   0.01548   0.00826  -0.0894   0.5550   1.0000
   3.000   0.8069   0.01579   0.00856  -0.0890   0.5516   1.0000
   3.250   0.8303   0.01608   0.00889  -0.0884   0.5474   1.0000
   3.500   0.8557   0.01629   0.00909  -0.0880   0.5435   1.0000
   3.750   0.8826   0.01646   0.00919  -0.0879   0.5402   1.0000
   4.000   0.9109   0.01670   0.00933  -0.0880   0.5373   1.0000
   4.250   0.9335   0.01708   0.00980  -0.0873   0.5334   1.0000
   4.500   0.9573   0.01740   0.01017  -0.0868   0.5292   1.0000
   4.750   0.9832   0.01763   0.01039  -0.0865   0.5255   1.0000
   5.000   1.0110   0.01781   0.01052  -0.0865   0.5224   1.0000
   5.250   1.0382   0.01813   0.01079  -0.0865   0.5191   1.0000
   5.500   1.0590   0.01852   0.01131  -0.0856   0.5141   1.0000
   5.750   1.0840   0.01875   0.01157  -0.0852   0.5097   1.0000
   6.000   1.1117   0.01889   0.01167  -0.0852   0.5061   1.0000
   6.250   1.1408   0.01913   0.01184  -0.0855   0.5028   1.0000
   6.500   1.1595   0.01953   0.01242  -0.0843   0.4972   1.0000
   6.750   1.1845   0.01968   0.01260  -0.0839   0.4923   1.0000
   7.000   1.2131   0.01977   0.01264  -0.0840   0.4886   1.0000
   7.250   1.2391   0.02011   0.01300  -0.0839   0.4850   1.0000
   7.500   1.2581   0.02054   0.01359  -0.0827   0.4796   1.0000
   7.750   1.2832   0.02067   0.01375  -0.0823   0.4750   1.0000
   8.000   1.3146   0.02054   0.01352  -0.0828   0.4705   1.0000
   8.250   1.3313   0.02085   0.01401  -0.0812   0.4637   1.0000
   8.500   1.3559   0.02086   0.01405  -0.0807   0.4581   1.0000
   8.750   1.3859   0.02085   0.01397  -0.0811   0.4541   1.0000
   9.000   1.4018   0.02127   0.01459  -0.0794   0.4480   1.0000
   9.250   1.4249   0.02126   0.01463  -0.0787   0.4418   1.0000
   9.500   1.4519   0.02122   0.01455  -0.0786   0.4366   1.0000
   9.750   1.4662   0.02157   0.01510  -0.0767   0.4296   1.0000
  10.000   1.4902   0.02155   0.01509  -0.0761   0.4238   1.0000
  10.250   1.5081   0.02185   0.01550  -0.0747   0.4178   1.0000
  10.500   1.5249   0.02208   0.01585  -0.0732   0.4109   1.0000
  10.750   1.5461   0.02216   0.01594  -0.0722   0.4046   1.0000
  11.000   1.5554   0.02259   0.01653  -0.0697   0.3962   1.0000
  11.250   1.5693   0.02278   0.01675  -0.0676   0.3880   1.0000
  11.500   1.5736   0.02328   0.01736  -0.0644   0.3785   1.0000
  11.750   1.5780   0.02395   0.01810  -0.0614   0.3681   1.0000
  12.000   1.5819   0.02474   0.01891  -0.0588   0.3564   1.0000
  12.250   1.5825   0.02588   0.02006  -0.0562   0.3431   1.0000
  12.500   1.5796   0.02748   0.02169  -0.0537   0.3283   1.0000
  12.750   1.5737   0.02959   0.02383  -0.0516   0.3116   1.0000
  13.000   1.5646   0.03224   0.02650  -0.0499   0.2924   1.0000
  13.250   1.5509   0.03551   0.02972  -0.0482   0.2708   1.0000
  13.500   1.5329   0.03937   0.03350  -0.0468   0.2469   1.0000
  13.750   1.5103   0.04380   0.03782  -0.0454   0.2246   1.0000
  14.000   1.4886   0.04836   0.04228  -0.0443   0.2054   1.0000
  14.250   1.4686   0.05296   0.04678  -0.0435   0.1907   1.0000
  14.500   1.4521   0.05732   0.05104  -0.0429   0.1792   1.0000
  14.750   1.4397   0.06134   0.05499  -0.0424   0.1690   1.0000
  15.000   1.4325   0.06487   0.05852  -0.0420   0.1597   1.0000
  15.250   1.4252   0.06834   0.06189  -0.0416   0.1520   1.0000
  15.500   1.4227   0.07153   0.06516  -0.0416   0.1443   1.0000
  15.750   1.4199   0.07455   0.06811  -0.0412   0.1380   1.0000
  16.000   1.4197   0.07758   0.07127  -0.0413   0.1318   1.0000
  16.250   1.4179   0.08064   0.07429  -0.0413   0.1263   1.0000
  16.500   1.4183   0.08362   0.07737  -0.0415   0.1209   1.0000
  16.750   1.4173   0.08681   0.08061  -0.0418   0.1157   1.0000
  17.000   1.4160   0.08994   0.08374  -0.0420   0.1109   1.0000
  17.250   1.4156   0.09318   0.08710  -0.0425   0.1058   1.0000
  17.500   1.4125   0.09669   0.09060  -0.0430   0.1011   1.0000
  17.750   1.4116   0.10000   0.09402  -0.0436   0.0962   1.0000
  18.000   1.4079   0.10373   0.09778  -0.0444   0.0912   1.0000
  18.250   1.4047   0.10736   0.10146  -0.0451   0.0861   1.0000
  18.500   1.3993   0.11139   0.10553  -0.0461   0.0806   1.0000
  18.750   1.3935   0.11551   0.10969  -0.0472   0.0746   1.0000
  19.000   1.3859   0.11987   0.11400  -0.0485   0.0686   1.0000
  19.250   1.3784   0.12453   0.11878  -0.0500   0.0619   1.0000
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