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GOE 361 AIRFOIL (goe361-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 361 AIRFOIL (goe361-il)
Reynolds number: 100,000
Max Cl/Cd: 57.8 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe361-il-100000.txt
Download as CSV file: xf-goe361-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 361 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2776   0.09458   0.09002  -0.0230   1.0000   0.0543
  -7.000  -0.2816   0.09354   0.08909  -0.0233   1.0000   0.0556
  -6.750  -0.2831   0.09319   0.08884  -0.0265   1.0000   0.0565
  -6.500  -0.2793   0.09280   0.08851  -0.0318   1.0000   0.0570
  -6.250  -0.2756   0.08992   0.08570  -0.0336   1.0000   0.0574
  -6.000  -0.2796   0.08476   0.08063  -0.0258   1.0000   0.0585
  -5.750  -0.2796   0.08197   0.07788  -0.0227   1.0000   0.0600
  -5.500  -0.2791   0.07981   0.07577  -0.0215   1.0000   0.0616
  -5.250  -0.2777   0.07781   0.07383  -0.0212   1.0000   0.0635
  -5.000  -0.2742   0.07589   0.07195  -0.0221   1.0000   0.0662
  -4.750  -0.2324   0.07598   0.07181  -0.0396   1.0000   0.0706
  -4.500  -0.2437   0.07156   0.06756  -0.0336   1.0000   0.0715
  -4.250  -0.2207   0.06690   0.06295  -0.0341   0.9934   0.0752
  -4.000  -0.1371   0.06239   0.05806  -0.0551   0.9842   0.0853
  -3.750  -0.1177   0.05774   0.05350  -0.0548   0.9755   0.0885
  -3.500  -0.0561   0.05355   0.04905  -0.0671   0.9670   0.1007
  -3.250   0.0008   0.05012   0.04534  -0.0767   0.9584   0.1143
  -3.000   0.0282   0.04630   0.04163  -0.0781   0.9484   0.1202
  -2.750   0.0819   0.04273   0.03786  -0.0858   0.9417   0.1352
  -2.500   0.1325   0.03994   0.03479  -0.0928   0.9311   0.1585
  -2.250   0.1710   0.03706   0.03191  -0.0961   0.9215   0.1787
  -2.000   0.2236   0.03443   0.02907  -0.1023   0.9148   0.2177
  -0.750   0.4571   0.02330   0.01558  -0.1166   0.8537   0.1280
  -0.500   0.4878   0.02143   0.01345  -0.1159   0.8351   0.1118
  -0.250   0.5178   0.02005   0.01184  -0.1153   0.8168   0.1045
   0.000   0.5483   0.01942   0.01076  -0.1142   0.7988   0.0989
   0.250   0.5770   0.01843   0.00962  -0.1135   0.7814   0.0978
   0.500   0.6035   0.01774   0.00881  -0.1125   0.7619   0.1008
   0.750   0.6301   0.01718   0.00819  -0.1115   0.7425   0.1047
   1.000   0.6568   0.01673   0.00764  -0.1105   0.7239   0.1068
   1.250   0.6824   0.01645   0.00724  -0.1093   0.7049   0.1107
   1.500   0.7090   0.01625   0.00692  -0.1085   0.6848   0.1179
   1.750   0.7363   0.01611   0.00667  -0.1077   0.6656   0.1366
   2.000   0.7675   0.01445   0.00644  -0.1080   0.6467   1.0000
   2.250   0.7925   0.01474   0.00646  -0.1070   0.6260   1.0000
   2.500   0.8178   0.01504   0.00651  -0.1061   0.6067   1.0000
   2.750   0.8431   0.01535   0.00660  -0.1052   0.5881   1.0000
   3.000   0.8677   0.01568   0.00683  -0.1044   0.5681   1.0000
   3.250   0.8926   0.01602   0.00703  -0.1035   0.5494   1.0000
   3.500   0.9176   0.01637   0.00723  -0.1028   0.5318   1.0000
   3.750   0.9427   0.01677   0.00747  -0.1020   0.5151   1.0000
   4.000   0.9674   0.01720   0.00785  -0.1013   0.4979   1.0000
   4.250   0.9922   0.01766   0.00823  -0.1006   0.4821   1.0000
   4.500   1.0172   0.01816   0.00865  -0.1000   0.4678   1.0000
   4.750   1.0426   0.01870   0.00910  -0.0995   0.4554   1.0000
   5.000   1.0677   0.01928   0.00971  -0.0990   0.4438   1.0000
   5.250   1.0926   0.01991   0.01040  -0.0985   0.4335   1.0000
   5.500   1.1187   0.02058   0.01103  -0.0981   0.4255   1.0000
   5.750   1.1434   0.02126   0.01185  -0.0977   0.4172   1.0000
   6.000   1.1694   0.02198   0.01262  -0.0974   0.4108   1.0000
   6.250   1.1930   0.02240   0.01310  -0.0966   0.3994   1.0000
   6.500   1.2151   0.02247   0.01310  -0.0954   0.3824   1.0000
   6.750   1.2362   0.02260   0.01331  -0.0941   0.3666   1.0000
   7.000   1.2576   0.02276   0.01358  -0.0929   0.3520   1.0000
   7.250   1.2770   0.02280   0.01378  -0.0913   0.3347   1.0000
   7.500   1.2949   0.02272   0.01381  -0.0895   0.3135   1.0000
   7.750   1.3104   0.02267   0.01387  -0.0873   0.2845   1.0000
   8.000   1.3258   0.02295   0.01421  -0.0851   0.2461   1.0000
   8.250   1.3312   0.02463   0.01515  -0.0823   0.1142   1.0000
   8.500   1.3319   0.02758   0.01757  -0.0791   0.0664   1.0000
   8.750   1.3401   0.02948   0.01953  -0.0766   0.0586   1.0000
   9.000   1.3480   0.03116   0.02141  -0.0740   0.0553   1.0000
   9.250   1.3530   0.03287   0.02333  -0.0712   0.0530   1.0000
   9.500   1.3525   0.03465   0.02528  -0.0677   0.0514   1.0000
   9.750   1.3489   0.03663   0.02738  -0.0644   0.0500   1.0000
  10.000   1.3423   0.03899   0.02984  -0.0613   0.0486   1.0000
  10.250   1.3344   0.04176   0.03266  -0.0587   0.0472   1.0000
  10.500   1.3375   0.04391   0.03493  -0.0568   0.0460   1.0000
  10.750   1.3465   0.04591   0.03699  -0.0549   0.0452   1.0000
  11.000   1.3673   0.04765   0.03874  -0.0532   0.0445   1.0000
  11.250   1.4033   0.04967   0.04081  -0.0523   0.0442   1.0000
  11.500   1.4391   0.05256   0.04389  -0.0521   0.0440   1.0000
  11.750   1.4569   0.05558   0.04717  -0.0511   0.0433   1.0000
  12.000   1.4648   0.05870   0.05062  -0.0496   0.0428   1.0000
  12.250   1.4680   0.06220   0.05443  -0.0479   0.0431   1.0000
  12.500   1.4674   0.06606   0.05862  -0.0464   0.0440   1.0000
  12.750   1.4631   0.07023   0.06309  -0.0450   0.0448   1.0000
  13.000   1.4579   0.07489   0.06803  -0.0441   0.0457   1.0000
  13.250   1.4728   0.08069   0.07405  -0.0438   0.0475   1.0000
  13.500   1.4528   0.08337   0.07701  -0.0427   0.0481   1.0000
  13.750   1.4284   0.08751   0.08148  -0.0431   0.0488   1.0000
  14.000   1.3997   0.09297   0.08724  -0.0449   0.0492   1.0000
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