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GOE 593 AIRFOIL (goe593-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 593 AIRFOIL (goe593-il)
Reynolds number: 50,000
Max Cl/Cd: 24.34 at α=12°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe593-il-50000.txt
Download as CSV file: xf-goe593-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 593 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3450   0.12268   0.11556  -0.0332   1.0000   0.2076
  -9.750  -0.3242   0.11726   0.11013  -0.0316   1.0000   0.2142
  -9.500  -0.3343   0.11606   0.10903  -0.0313   1.0000   0.2227
  -9.250  -0.3289   0.11246   0.10550  -0.0302   1.0000   0.2286
  -9.000  -0.3335   0.11072   0.10384  -0.0291   1.0000   0.2384
  -8.750  -0.3368   0.10797   0.10119  -0.0281   1.0000   0.2440
  -8.500  -0.3353   0.10561   0.09889  -0.0264   1.0000   0.2537
  -8.250  -0.3773   0.10690   0.10043  -0.0247   1.0000   0.2572
  -8.000  -0.3436   0.10114   0.09461  -0.0228   1.0000   0.2695
  -7.750  -0.3887   0.10237   0.09608  -0.0200   1.0000   0.2736
  -7.500  -0.3638   0.09765   0.09135  -0.0180   1.0000   0.2874
  -7.250  -0.3643   0.09504   0.08882  -0.0154   1.0000   0.2975
  -7.000  -0.3971   0.09508   0.08904  -0.0115   1.0000   0.3052
  -6.750  -0.3906   0.09211   0.08611  -0.0088   1.0000   0.3186
  -6.500  -0.4379   0.09266   0.08687  -0.0049   1.0000   0.3228
  -6.250  -0.4354   0.09005   0.08432  -0.0015   1.0000   0.3384
  -6.000  -0.4381   0.08777   0.08211   0.0018   1.0000   0.3541
  -5.750  -0.4449   0.08573   0.08015   0.0052   1.0000   0.3704
  -5.500  -0.4562   0.08398   0.07849   0.0085   1.0000   0.3876
  -5.250  -0.4701   0.08221   0.07682   0.0119   1.0000   0.4070
  -5.000  -0.4547   0.07941   0.07403   0.0163   1.0000   0.4307
  -4.000  -0.4240   0.05181   0.04455  -0.0244   1.0000   0.1890
  -3.750  -0.4020   0.04741   0.03942  -0.0259   1.0000   0.1741
  -3.500  -0.3841   0.04466   0.03642  -0.0255   1.0000   0.1702
  -3.250  -0.3647   0.04218   0.03351  -0.0253   1.0000   0.1689
  -3.000  -0.3452   0.04024   0.03114  -0.0248   1.0000   0.1707
  -2.750  -0.3249   0.03848   0.02892  -0.0242   1.0000   0.1724
  -2.500  -0.3042   0.03696   0.02692  -0.0234   1.0000   0.1743
  -2.250  -0.2851   0.03571   0.02554  -0.0226   1.0000   0.1799
  -2.000  -0.2656   0.03485   0.02447  -0.0218   1.0000   0.1881
  -1.750  -0.2452   0.03391   0.02332  -0.0210   1.0000   0.1962
  -1.500  -0.2244   0.03329   0.02251  -0.0204   1.0000   0.2095
  -1.250  -0.2040   0.03271   0.02191  -0.0197   1.0000   0.2267
  -1.000  -0.1837   0.03226   0.02151  -0.0190   1.0000   0.2530
  -0.750  -0.1547   0.03184   0.02122  -0.0198   0.9986   0.3015
  -0.500  -0.0645   0.02948   0.02157  -0.0301   0.9858   1.0000
  -0.250  -0.0133   0.03090   0.02222  -0.0353   0.9708   1.0000
   0.000   0.0285   0.03196   0.02286  -0.0390   0.9554   1.0000
   0.250   0.0692   0.03297   0.02355  -0.0424   0.9397   1.0000
   0.500   0.1091   0.03393   0.02423  -0.0455   0.9236   1.0000
   0.750   0.1484   0.03482   0.02491  -0.0483   0.9072   1.0000
   1.000   0.1868   0.03567   0.02556  -0.0509   0.8907   1.0000
   1.250   0.2246   0.03646   0.02619  -0.0532   0.8741   1.0000
   1.500   0.2622   0.03717   0.02677  -0.0553   0.8573   1.0000
   1.750   0.3006   0.03780   0.02729  -0.0574   0.8402   1.0000
   2.000   0.3386   0.03836   0.02776  -0.0592   0.8234   1.0000
   2.250   0.3778   0.03880   0.02812  -0.0610   0.8066   1.0000
   2.500   0.4167   0.03915   0.02841  -0.0626   0.7900   1.0000
   2.750   0.4562   0.03936   0.02859  -0.0641   0.7735   1.0000
   3.000   0.4769   0.03994   0.02914  -0.0631   0.7542   1.0000
   3.250   0.5072   0.04028   0.02947  -0.0632   0.7365   1.0000
   3.500   0.5402   0.04048   0.02967  -0.0634   0.7195   1.0000
   3.750   0.5733   0.04062   0.02982  -0.0636   0.7031   1.0000
   4.000   0.6066   0.04070   0.02991  -0.0637   0.6872   1.0000
   4.250   0.6419   0.04060   0.02984  -0.0638   0.6722   1.0000
   4.500   0.7131   0.03867   0.02799  -0.0676   0.6627   1.0000
   4.750   0.7440   0.03873   0.02810  -0.0672   0.6473   1.0000
   5.000   0.7703   0.03904   0.02845  -0.0664   0.6321   1.0000
   5.250   0.7934   0.03955   0.02900  -0.0653   0.6171   1.0000
   5.500   0.8128   0.04030   0.02981  -0.0638   0.6024   1.0000
   5.750   0.8258   0.04150   0.03104  -0.0619   0.5885   1.0000
   6.000   0.8445   0.04248   0.03207  -0.0606   0.5759   1.0000
   6.250   0.9181   0.04035   0.03007  -0.0644   0.5672   1.0000
   6.500   0.9039   0.04323   0.03299  -0.0601   0.5535   1.0000
   6.750   0.8732   0.04737   0.03712  -0.0548   0.5408   1.0000
   7.000   0.8856   0.04906   0.03887  -0.0534   0.5313   1.0000
   7.250   0.9042   0.05028   0.04017  -0.0524   0.5216   1.0000
   7.500   0.8248   0.06025   0.05003  -0.0486   0.5088   1.0000
   7.750   0.9112   0.05544   0.04544  -0.0492   0.5041   1.0000
   8.000   0.7958   0.06971   0.05952  -0.0472   0.4939   1.0000
   8.250   0.8348   0.06958   0.05951  -0.0468   0.4870   1.0000
   8.500   0.7832   0.07792   0.06779  -0.0467   0.4827   1.0000
   8.750   0.7713   0.08263   0.07253  -0.0468   0.4790   1.0000
   9.000   0.8049   0.08341   0.07345  -0.0464   0.4714   1.0000
   9.250   0.7816   0.08931   0.07935  -0.0469   0.4701   1.0000
   9.500   0.7693   0.09430   0.08438  -0.0475   0.4696   1.0000
   9.750   0.7623   0.09893   0.08907  -0.0482   0.4697   1.0000
  10.000   0.7644   0.10330   0.09352  -0.0491   0.4712   1.0000
  10.750   1.2072   0.05767   0.04933  -0.0334   0.3618   1.0000
  11.000   1.2708   0.05390   0.04569  -0.0336   0.3320   1.0000
  11.250   1.2010   0.06080   0.05268  -0.0268   0.3324   1.0000
  11.500   1.1300   0.07043   0.06230  -0.0243   0.3307   1.0000
  11.750   1.1283   0.07228   0.06424  -0.0221   0.3142   1.0000
  12.000   1.3220   0.05431   0.04587  -0.0214   0.2367   1.0000
  12.250   1.2851   0.05836   0.05020  -0.0163   0.2321   1.0000
  12.500   0.8819   0.12113   0.11251  -0.0387   0.3013   1.0000
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