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GOE 375 AIRFOIL (goe375-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 375 AIRFOIL (goe375-il)
Reynolds number: 50,000
Max Cl/Cd: 37.58 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe375-il-50000-n5.txt
Download as CSV file: xf-goe375-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 375 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3270   0.10326   0.09665  -0.0168   1.0000   0.0438
  -7.750  -0.3265   0.10144   0.09494  -0.0180   1.0000   0.0445
  -7.500  -0.3248   0.09971   0.09332  -0.0204   1.0000   0.0450
  -7.250  -0.3197   0.09794   0.09163  -0.0238   1.0000   0.0454
  -7.000  -0.3122   0.09612   0.08984  -0.0277   1.0000   0.0457
  -6.750  -0.3071   0.09074   0.08459  -0.0250   1.0000   0.0467
  -6.500  -0.3015   0.08672   0.08064  -0.0229   1.0000   0.0485
  -6.250  -0.2953   0.08375   0.07774  -0.0230   1.0000   0.0506
  -6.000  -0.2882   0.08104   0.07509  -0.0241   1.0000   0.0531
  -5.750  -0.2784   0.07865   0.07274  -0.0266   1.0000   0.0561
  -5.500  -0.2578   0.07824   0.07215  -0.0341   1.0000   0.0585
  -5.250  -0.2602   0.07288   0.06704  -0.0295   1.0000   0.0607
  -5.000  -0.2548   0.06993   0.06413  -0.0282   1.0000   0.0650
  -4.750  -0.2408   0.06776   0.06190  -0.0305   1.0000   0.0706
  -4.500  -0.2281   0.06496   0.05905  -0.0321   1.0000   0.0743
  -4.250  -0.2229   0.06198   0.05616  -0.0303   1.0000   0.0793
  -4.000  -0.2042   0.05978   0.05379  -0.0330   1.0000   0.0883
  -3.750  -0.1964   0.05697   0.05103  -0.0317   1.0000   0.0962
  -3.500  -0.1831   0.05435   0.04837  -0.0321   1.0000   0.1080
  -3.250  -0.1658   0.05218   0.04605  -0.0337   1.0000   0.1311
  -3.000  -0.1414   0.04860   0.04255  -0.0359   0.9916   0.1785
  -2.750  -0.1209   0.04584   0.03988  -0.0369   0.9810   0.2776
  -2.500  -0.1064   0.04229   0.03662  -0.0344   0.9707   0.3563
  -2.250  -0.0802   0.03929   0.03368  -0.0342   0.9597   0.4161
  -1.750   0.0925   0.03417   0.02617  -0.0582   0.9392   0.1370
  -1.500   0.1413   0.03240   0.02369  -0.0600   0.9270   0.0981
  -1.250   0.1851   0.03047   0.02128  -0.0618   0.9147   0.0835
  -1.000   0.2278   0.02872   0.01913  -0.0639   0.9020   0.0826
  -0.750   0.2703   0.02712   0.01715  -0.0655   0.8882   0.0783
  -0.500   0.3121   0.02593   0.01553  -0.0667   0.8725   0.0746
  -0.250   0.3507   0.02460   0.01402  -0.0678   0.8549   0.0783
   0.000   0.3923   0.02353   0.01262  -0.0688   0.8359   0.0784
   0.250   0.4266   0.02274   0.01160  -0.0686   0.8123   0.0776
   0.500   0.4583   0.02209   0.01075  -0.0681   0.7879   0.0775
   0.750   0.4874   0.02157   0.01003  -0.0673   0.7623   0.0787
   1.000   0.5134   0.02122   0.00953  -0.0662   0.7339   0.0834
   1.250   0.5393   0.02097   0.00909  -0.0650   0.7046   0.0861
   1.500   0.5653   0.02075   0.00869  -0.0639   0.6748   0.0875
   1.750   0.5913   0.02060   0.00833  -0.0628   0.6449   0.0898
   2.000   0.6170   0.02057   0.00808  -0.0617   0.6155   0.0934
   2.250   0.6421   0.02064   0.00793  -0.0606   0.5866   0.0987
   2.500   0.6669   0.02074   0.00792  -0.0595   0.5590   0.1133
   2.750   0.6979   0.01938   0.00804  -0.0601   0.5317   1.0000
   3.000   0.7222   0.01984   0.00818  -0.0590   0.5071   1.0000
   3.250   0.7462   0.02033   0.00843  -0.0581   0.4834   1.0000
   3.500   0.7703   0.02085   0.00870  -0.0573   0.4618   1.0000
   3.750   0.7942   0.02138   0.00906  -0.0565   0.4403   1.0000
   4.000   0.8181   0.02193   0.00945  -0.0557   0.4213   1.0000
   4.250   0.8420   0.02250   0.00985  -0.0549   0.4032   1.0000
   4.500   0.8655   0.02308   0.01034  -0.0542   0.3856   1.0000
   4.750   0.8891   0.02367   0.01085  -0.0535   0.3696   1.0000
   5.000   0.9125   0.02428   0.01142  -0.0528   0.3544   1.0000
   5.250   0.9358   0.02491   0.01199  -0.0521   0.3408   1.0000
   5.500   0.9592   0.02556   0.01259  -0.0514   0.3286   1.0000
   5.750   0.9825   0.02624   0.01330  -0.0507   0.3166   1.0000
   6.000   1.0056   0.02698   0.01410  -0.0501   0.3053   1.0000
   6.250   1.0287   0.02774   0.01491  -0.0494   0.2952   1.0000
   6.500   1.0519   0.02849   0.01562  -0.0488   0.2861   1.0000
   6.750   1.0741   0.02937   0.01673  -0.0481   0.2762   1.0000
   7.000   1.0973   0.03026   0.01766  -0.0475   0.2688   1.0000
   7.250   1.1196   0.03129   0.01889  -0.0469   0.2611   1.0000
   7.500   1.1427   0.03226   0.01991  -0.0463   0.2549   1.0000
   7.750   1.1633   0.03345   0.02144  -0.0455   0.2473   1.0000
   8.000   1.1862   0.03442   0.02245  -0.0449   0.2415   1.0000
   8.250   1.2047   0.03583   0.02422  -0.0440   0.2347   1.0000
   8.500   1.2255   0.03709   0.02570  -0.0433   0.2295   1.0000
   8.750   1.2481   0.03834   0.02711  -0.0428   0.2256   1.0000
   9.000   1.2629   0.04030   0.02958  -0.0417   0.2209   1.0000
   9.250   1.2797   0.04199   0.03161  -0.0407   0.2164   1.0000
   9.500   1.3002   0.04332   0.03312  -0.0400   0.2125   1.0000
   9.750   1.3124   0.04527   0.03547  -0.0387   0.2080   1.0000
  10.000   1.3250   0.04608   0.03654  -0.0372   0.1993   1.0000
  10.250   1.3323   0.04685   0.03765  -0.0352   0.1891   1.0000
  10.500   1.3417   0.04682   0.03776  -0.0332   0.1780   1.0000
  10.750   1.3456   0.04678   0.03786  -0.0308   0.1657   1.0000
  11.000   1.3457   0.04823   0.03967  -0.0286   0.1579   1.0000
  11.250   1.3442   0.04946   0.04114  -0.0261   0.1509   1.0000
  11.500   1.3380   0.05162   0.04364  -0.0240   0.1452   1.0000
  11.750   1.3300   0.05361   0.04581  -0.0225   0.1374   1.0000
  12.000   1.3155   0.05710   0.04958  -0.0221   0.1302   1.0000
  12.250   1.3020   0.06095   0.05359  -0.0226   0.1233   1.0000
  12.500   1.2822   0.06675   0.05968  -0.0245   0.1202   1.0000
  12.750   1.2593   0.07375   0.06690  -0.0274   0.1195   1.0000
  13.000   1.2326   0.08223   0.07553  -0.0313   0.1219   1.0000
  13.250   1.2049   0.09149   0.08487  -0.0356   0.1241   1.0000
  13.500   1.1782   0.10110   0.09450  -0.0401   0.1255   1.0000
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