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GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il)
Reynolds number: 200,000
Max Cl/Cd: 74.17 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe142-il-200000.txt
Download as CSV file: xf-goe142-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 142 (MVA H.19) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3613   0.08730   0.08400  -0.0279   1.0000   0.0311
  -6.750  -0.3567   0.08313   0.07986  -0.0247   1.0000   0.0318
  -6.500  -0.3487   0.07989   0.07665  -0.0243   1.0000   0.0325
  -6.250  -0.3403   0.07688   0.07366  -0.0251   1.0000   0.0333
  -6.000  -0.3319   0.07395   0.07074  -0.0263   1.0000   0.0342
  -5.750  -0.3231   0.07103   0.06784  -0.0277   1.0000   0.0352
  -5.500  -0.3139   0.06813   0.06495  -0.0292   1.0000   0.0364
  -5.250  -0.3033   0.06520   0.06201  -0.0308   1.0000   0.0379
  -5.000  -0.2859   0.06224   0.05899  -0.0342   1.0000   0.0401
  -4.750  -0.2526   0.05995   0.05645  -0.0407   1.0000   0.0417
  -4.500  -0.2347   0.05713   0.05349  -0.0419   1.0000   0.0418
  -4.250  -0.2322   0.05116   0.04762  -0.0417   1.0000   0.0431
  -4.000  -0.2231   0.04867   0.04515  -0.0406   1.0000   0.0443
  -3.750  -0.1849   0.04544   0.04184  -0.0453   0.9962   0.0494
  -3.500  -0.1235   0.04039   0.03623  -0.0543   0.9919   0.0556
  -3.250  -0.0896   0.03670   0.03255  -0.0580   0.9874   0.0580
  -3.000  -0.0447   0.03371   0.02936  -0.0627   0.9838   0.0639
  -2.250   0.1262   0.00636   0.00058  -0.0771   0.9561   0.0533
  -1.750   0.1804   0.01686   0.00999  -0.0786   0.9597   0.0558
  -1.500   0.2239   0.01526   0.00824  -0.0816   0.9553   0.0604
  -1.250   0.2608   0.01459   0.00734  -0.0828   0.9458   0.0679
  -1.000   0.2962   0.01334   0.00609  -0.0840   0.9366   0.0756
  -0.750   0.3307   0.01258   0.00530  -0.0848   0.9268   0.0866
  -0.500   0.3609   0.01201   0.00471  -0.0846   0.9138   0.0981
  -0.250   0.3882   0.01147   0.00423  -0.0840   0.8986   0.1142
   0.000   0.4143   0.01103   0.00386  -0.0831   0.8813   0.1356
   0.250   0.4402   0.01056   0.00352  -0.0822   0.8631   0.1770
   0.500   0.4635   0.00838   0.00327  -0.0806   0.8456   1.0000
   0.750   0.4891   0.00840   0.00308  -0.0795   0.8246   1.0000
   1.000   0.5148   0.00846   0.00295  -0.0785   0.8026   1.0000
   1.250   0.5405   0.00854   0.00286  -0.0776   0.7787   1.0000
   1.500   0.5663   0.00865   0.00280  -0.0768   0.7544   1.0000
   1.750   0.5920   0.00879   0.00277  -0.0759   0.7289   1.0000
   2.000   0.6178   0.00896   0.00277  -0.0752   0.7021   1.0000
   2.250   0.6436   0.00915   0.00281  -0.0745   0.6744   1.0000
   2.500   0.6694   0.00937   0.00287  -0.0738   0.6465   1.0000
   2.750   0.6951   0.00961   0.00297  -0.0732   0.6182   1.0000
   3.000   0.7208   0.00988   0.00308  -0.0726   0.5902   1.0000
   3.250   0.7465   0.01016   0.00322  -0.0721   0.5625   1.0000
   3.500   0.7721   0.01045   0.00338  -0.0716   0.5356   1.0000
   3.750   0.7977   0.01077   0.00360  -0.0711   0.5098   1.0000
   4.000   0.8233   0.01110   0.00382  -0.0706   0.4852   1.0000
   4.250   0.8487   0.01145   0.00406  -0.0701   0.4614   1.0000
   4.500   0.8743   0.01179   0.00433  -0.0697   0.4386   1.0000
   4.750   0.8995   0.01218   0.00464  -0.0693   0.4176   1.0000
   5.000   0.9251   0.01254   0.00497  -0.0689   0.3964   1.0000
   5.250   0.9503   0.01294   0.00531  -0.0684   0.3774   1.0000
   5.500   0.9754   0.01336   0.00568  -0.0680   0.3592   1.0000
   5.750   1.0006   0.01376   0.00610  -0.0676   0.3413   1.0000
   6.000   1.0256   0.01419   0.00653  -0.0671   0.3246   1.0000
   6.250   1.0504   0.01464   0.00697  -0.0667   0.3085   1.0000
   6.500   1.0749   0.01509   0.00741  -0.0662   0.2924   1.0000
   6.750   1.0990   0.01548   0.00781  -0.0657   0.2734   1.0000
   7.000   1.1231   0.01583   0.00822  -0.0652   0.2529   1.0000
   7.250   1.1467   0.01628   0.00867  -0.0646   0.2354   1.0000
   7.500   1.1706   0.01669   0.00915  -0.0641   0.2170   1.0000
   7.750   1.1941   0.01713   0.00963  -0.0636   0.1963   1.0000
   8.000   1.2172   0.01761   0.01016  -0.0630   0.1707   1.0000
   8.250   1.2380   0.01842   0.01084  -0.0622   0.1271   1.0000
   8.500   1.2492   0.02075   0.01260  -0.0603   0.0589   1.0000
   8.750   1.2638   0.02246   0.01431  -0.0585   0.0449   1.0000
   9.000   1.2764   0.02427   0.01621  -0.0565   0.0390   1.0000
   9.250   1.2915   0.02568   0.01772  -0.0548   0.0345   1.0000
   9.500   1.2978   0.02820   0.02026  -0.0522   0.0309   1.0000
   9.750   1.3130   0.02965   0.02188  -0.0505   0.0293   1.0000
  10.000   1.3263   0.03144   0.02387  -0.0486   0.0277   1.0000
  10.250   1.3391   0.03342   0.02599  -0.0467   0.0263   1.0000
  10.500   1.3513   0.03552   0.02824  -0.0449   0.0251   1.0000
  10.750   1.3616   0.03772   0.03054  -0.0431   0.0238   1.0000
  11.000   1.3688   0.04194   0.03496  -0.0414   0.0224   1.0000
  11.250   1.3712   0.04510   0.03844  -0.0389   0.0218   1.0000
  11.500   1.3707   0.04761   0.04123  -0.0361   0.0216   1.0000
  11.750   1.3666   0.05045   0.04436  -0.0334   0.0214   1.0000
  12.000   1.3590   0.05364   0.04783  -0.0310   0.0213   1.0000
  12.250   1.3485   0.05723   0.05169  -0.0293   0.0212   1.0000
  12.500   1.3355   0.06124   0.05598  -0.0283   0.0212   1.0000
  12.750   1.3204   0.06575   0.06074  -0.0281   0.0213   1.0000
  13.000   1.3036   0.07080   0.06603  -0.0289   0.0213   1.0000
  13.250   1.2855   0.07646   0.07191  -0.0307   0.0214   1.0000
  13.500   1.2662   0.08273   0.07839  -0.0334   0.0215   1.0000
  13.750   1.2458   0.08967   0.08552  -0.0369   0.0216   1.0000
  14.000   1.2245   0.09726   0.09328  -0.0410   0.0218   1.0000
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