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GOE 796 AIRFOIL (goe796-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 796 AIRFOIL (goe796-il)
Reynolds number: 50,000
Max Cl/Cd: 32.16 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe796-il-50000.txt
Download as CSV file: xf-goe796-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 796 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3399   0.10981   0.10272  -0.0314   1.0000   0.2348
  -8.500  -0.3468   0.10736   0.10039  -0.0306   1.0000   0.2395
  -8.250  -0.3408   0.10472   0.09780  -0.0290   1.0000   0.2495
  -8.000  -0.3808   0.10550   0.09881  -0.0273   1.0000   0.2529
  -7.750  -0.3514   0.10051   0.09378  -0.0254   1.0000   0.2654
  -7.500  -0.3941   0.10130   0.09482  -0.0221   1.0000   0.2686
  -7.250  -0.3691   0.09682   0.09031  -0.0203   1.0000   0.2811
  -7.000  -0.4139   0.09755   0.09128  -0.0159   1.0000   0.2844
  -6.750  -0.3948   0.09363   0.08737  -0.0137   1.0000   0.2961
  -6.500  -0.4427   0.09423   0.08818  -0.0105   1.0000   0.3007
  -6.250  -0.4258   0.09061   0.08459  -0.0070   1.0000   0.3120
  -5.750  -0.4729   0.08827   0.08247  -0.0029   1.0000   0.3329
  -5.500  -0.4602   0.08498   0.07922   0.0012   1.0000   0.3445
  -5.250  -0.4662   0.08271   0.07703   0.0039   1.0000   0.3579
  -5.000  -0.4724   0.08055   0.07492   0.0066   1.0000   0.3744
  -4.750  -0.4617   0.06194   0.05519  -0.0294   1.0000   0.1876
  -4.500  -0.4369   0.05238   0.04456  -0.0363   1.0000   0.1587
  -4.250  -0.4216   0.05009   0.04237  -0.0353   1.0000   0.1633
  -4.000  -0.4007   0.04685   0.03871  -0.0363   1.0000   0.1692
  -3.750  -0.3804   0.04439   0.03597  -0.0367   1.0000   0.1803
  -3.500  -0.3606   0.04274   0.03412  -0.0366   1.0000   0.1969
  -3.250  -0.3382   0.04083   0.03187  -0.0370   1.0000   0.2105
  -3.000  -0.3127   0.03889   0.02943  -0.0377   1.0000   0.2181
  -2.750  -0.2900   0.03755   0.02791  -0.0377   1.0000   0.2280
  -2.500  -0.2642   0.03629   0.02616  -0.0382   1.0000   0.2357
  -2.250  -0.2408   0.03522   0.02495  -0.0383   1.0000   0.2430
  -2.000  -0.2168   0.03451   0.02398  -0.0384   1.0000   0.2554
  -1.750  -0.1931   0.03396   0.02323  -0.0385   1.0000   0.2684
  -1.500  -0.1699   0.03340   0.02264  -0.0384   1.0000   0.2813
  -1.250  -0.1467   0.03305   0.02219  -0.0384   1.0000   0.2989
  -1.000  -0.1235   0.03282   0.02197  -0.0383   1.0000   0.3210
  -0.750  -0.0989   0.03273   0.02189  -0.0385   1.0000   0.3501
  -0.500  -0.0739   0.03261   0.02196  -0.0388   1.0000   0.3880
  -0.250  -0.0464   0.03233   0.02209  -0.0395   1.0000   0.4511
   0.000  -0.0319   0.03015   0.02185  -0.0362   1.0000   1.0000
   0.250   0.0239   0.03165   0.02249  -0.0425   0.9866   1.0000
   0.500   0.0790   0.03315   0.02355  -0.0487   0.9715   1.0000
   0.750   0.1246   0.03432   0.02442  -0.0531   0.9556   1.0000
   1.000   0.1661   0.03536   0.02524  -0.0566   0.9401   1.0000
   1.250   0.2070   0.03638   0.02607  -0.0599   0.9253   1.0000
   1.500   0.2478   0.03737   0.02691  -0.0631   0.9112   1.0000
   1.750   0.2850   0.03827   0.02769  -0.0655   0.8969   1.0000
   2.000   0.3183   0.03910   0.02844  -0.0673   0.8822   1.0000
   2.250   0.3509   0.03994   0.02920  -0.0688   0.8675   1.0000
   2.500   0.3844   0.04074   0.02996  -0.0704   0.8524   1.0000
   2.750   0.4178   0.04152   0.03070  -0.0719   0.8372   1.0000
   3.000   0.4506   0.04228   0.03143  -0.0731   0.8219   1.0000
   3.250   0.4830   0.04301   0.03215  -0.0742   0.8064   1.0000
   3.500   0.5146   0.04373   0.03288  -0.0751   0.7910   1.0000
   3.750   0.5450   0.04445   0.03362  -0.0758   0.7755   1.0000
   4.000   0.5739   0.04519   0.03439  -0.0761   0.7601   1.0000
   4.250   0.6001   0.04604   0.03526  -0.0762   0.7448   1.0000
   4.500   0.6240   0.04698   0.03626  -0.0760   0.7297   1.0000
   4.750   0.6458   0.04803   0.03734  -0.0756   0.7147   1.0000
   5.000   0.6640   0.04932   0.03867  -0.0749   0.7003   1.0000
   5.250   0.6807   0.05073   0.04013  -0.0741   0.6863   1.0000
   5.500   0.6988   0.05208   0.04155  -0.0734   0.6727   1.0000
   5.750   0.7218   0.05302   0.04256  -0.0729   0.6589   1.0000
   6.000   0.7494   0.05337   0.04299  -0.0722   0.6434   1.0000
   6.250   0.7797   0.05326   0.04299  -0.0713   0.6272   1.0000
   6.500   0.8101   0.05309   0.04291  -0.0704   0.6119   1.0000
   6.750   0.8409   0.05303   0.04297  -0.0696   0.5989   1.0000
   7.000   0.9007   0.05027   0.04043  -0.0697   0.5888   1.0000
   7.250   0.9194   0.05092   0.04119  -0.0681   0.5743   1.0000
   7.500   0.9435   0.05099   0.04138  -0.0665   0.5596   1.0000
   7.750   0.9761   0.05020   0.04076  -0.0652   0.5448   1.0000
   8.000   1.0262   0.04792   0.03870  -0.0648   0.5296   1.0000
   8.250   1.1120   0.04257   0.03356  -0.0663   0.5118   1.0000
   8.500   1.1271   0.04293   0.03404  -0.0636   0.4903   1.0000
   8.750   1.1898   0.03959   0.03067  -0.0641   0.4631   1.0000
   9.000   1.2320   0.03831   0.02928  -0.0636   0.4348   1.0000
   9.250   1.2428   0.03935   0.03040  -0.0607   0.4102   1.0000
   9.500   1.2691   0.03978   0.03073  -0.0594   0.3850   1.0000
   9.750   1.2891   0.04072   0.03163  -0.0576   0.3616   1.0000
  10.000   1.3096   0.04187   0.03274  -0.0561   0.3395   1.0000
  10.250   1.3192   0.04356   0.03454  -0.0535   0.3203   1.0000
  10.500   1.3315   0.04522   0.03626  -0.0512   0.3018   1.0000
  10.750   1.3453   0.04673   0.03780  -0.0491   0.2839   1.0000
  11.000   1.3584   0.04831   0.03943  -0.0470   0.2674   1.0000
  11.500   1.3819   0.05124   0.04241  -0.0426   0.2366   1.0000
  11.750   1.3823   0.05288   0.04415  -0.0392   0.2233   1.0000
  12.000   1.3935   0.05379   0.04492  -0.0370   0.2070   1.0000
  12.250   1.3708   0.05668   0.04819  -0.0318   0.2006   1.0000
  12.500   1.3717   0.05858   0.05010  -0.0290   0.1885   1.0000
  12.750   1.3763   0.06084   0.05234  -0.0267   0.1761   1.0000
  13.000   1.3666   0.06387   0.05555  -0.0237   0.1677   1.0000
  13.250   1.1657   0.08858   0.08133  -0.0252   0.2118   1.0000
  13.500   1.1361   0.09679   0.08957  -0.0271   0.2087   1.0000
  13.750   1.2872   0.07839   0.07086  -0.0170   0.1597   1.0000
  14.000   1.2464   0.08568   0.07838  -0.0172   0.1611   1.0000
  14.250   1.2035   0.09443   0.08730  -0.0192   0.1628   1.0000
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