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GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il)
Reynolds number: 1,000,000
Max Cl/Cd: 111.39 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe142-il-1000000-n5.txt
Download as CSV file: xf-goe142-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4102   0.09184   0.09027  -0.0089   1.0000   0.0042
  -7.750  -0.4071   0.08788   0.08632  -0.0111   1.0000   0.0044
  -7.500  -0.4038   0.08330   0.08176  -0.0144   1.0000   0.0047
  -7.250  -0.3946   0.07865   0.07712  -0.0190   1.0000   0.0049
  -7.000  -0.3799   0.07375   0.07222  -0.0249   0.9969   0.0050
  -6.000  -0.2629   0.01416   0.01039  -0.0784   0.9485   0.0071
  -5.750  -0.2369   0.01289   0.00885  -0.0782   0.9383   0.0073
  -5.500  -0.2109   0.01200   0.00772  -0.0779   0.9271   0.0074
  -5.250  -0.1845   0.01138   0.00692  -0.0775   0.9149   0.0076
  -5.000  -0.1582   0.01026   0.00554  -0.0773   0.9025   0.0081
  -4.750  -0.1315   0.00982   0.00498  -0.0770   0.8894   0.0085
  -4.500  -0.1045   0.00953   0.00459  -0.0767   0.8754   0.0090
  -4.250  -0.0774   0.00929   0.00425  -0.0764   0.8605   0.0096
  -4.000  -0.0503   0.00902   0.00384  -0.0761   0.8439   0.0102
  -3.750  -0.0230   0.00875   0.00344  -0.0758   0.8262   0.0107
  -3.500   0.0044   0.00853   0.00310  -0.0756   0.8073   0.0110
  -3.250   0.0318   0.00816   0.00259  -0.0754   0.7885   0.0119
  -3.000   0.0594   0.00800   0.00233  -0.0752   0.7691   0.0128
  -2.750   0.0870   0.00788   0.00211  -0.0751   0.7486   0.0139
  -2.500   0.1146   0.00780   0.00193  -0.0749   0.7276   0.0151
  -2.250   0.1423   0.00768   0.00171  -0.0748   0.7055   0.0168
  -2.000   0.1700   0.00762   0.00156  -0.0747   0.6817   0.0190
  -1.750   0.1977   0.00760   0.00143  -0.0745   0.6576   0.0210
  -1.500   0.2254   0.00758   0.00130  -0.0744   0.6333   0.0230
  -1.250   0.2532   0.00756   0.00121  -0.0744   0.6094   0.0272
  -1.000   0.2809   0.00759   0.00114  -0.0743   0.5860   0.0303
  -0.750   0.3088   0.00759   0.00107  -0.0742   0.5630   0.0351
  -0.500   0.3365   0.00761   0.00103  -0.0742   0.5410   0.0404
  -0.250   0.3643   0.00765   0.00099  -0.0741   0.5191   0.0454
   0.000   0.3922   0.00769   0.00097  -0.0741   0.4995   0.0526
   0.250   0.4199   0.00773   0.00096  -0.0740   0.4783   0.0618
   0.500   0.4477   0.00780   0.00096  -0.0740   0.4594   0.0701
   0.750   0.4754   0.00785   0.00098  -0.0740   0.4402   0.0829
   1.000   0.5031   0.00791   0.00100  -0.0739   0.4214   0.0985
   1.250   0.5308   0.00797   0.00104  -0.0739   0.4029   0.1202
   1.500   0.5585   0.00799   0.00110  -0.0739   0.3858   0.1635
   1.750   0.5845   0.00681   0.00129  -0.0744   0.3695   0.7537
   2.250   0.6364   0.00653   0.00139  -0.0732   0.3404   1.0000
   2.500   0.6639   0.00669   0.00147  -0.0732   0.3252   1.0000
   2.750   0.6915   0.00684   0.00155  -0.0731   0.3127   1.0000
   3.000   0.7190   0.00699   0.00164  -0.0730   0.3005   1.0000
   3.250   0.7464   0.00716   0.00174  -0.0730   0.2870   1.0000
   3.500   0.7737   0.00733   0.00184  -0.0729   0.2750   1.0000
   3.750   0.8011   0.00749   0.00197  -0.0728   0.2639   1.0000
   4.000   0.8284   0.00767   0.00209  -0.0727   0.2519   1.0000
   4.250   0.8556   0.00784   0.00223  -0.0726   0.2411   1.0000
   4.500   0.8827   0.00802   0.00237  -0.0725   0.2314   1.0000
   4.750   0.9097   0.00823   0.00254  -0.0724   0.2200   1.0000
   5.000   0.9368   0.00841   0.00270  -0.0723   0.2106   1.0000
   5.250   0.9633   0.00867   0.00289  -0.0722   0.1950   1.0000
   5.500   0.9895   0.00899   0.00311  -0.0720   0.1744   1.0000
   5.750   1.0158   0.00926   0.00334  -0.0718   0.1596   1.0000
   6.000   1.0415   0.00963   0.00360  -0.0716   0.1397   1.0000
   6.250   1.0673   0.00997   0.00387  -0.0714   0.1228   1.0000
   6.500   1.0929   0.01033   0.00417  -0.0711   0.1066   1.0000
   6.750   1.1176   0.01084   0.00456  -0.0708   0.0829   1.0000
   7.000   1.1409   0.01154   0.00507  -0.0703   0.0529   1.0000
   7.250   1.1648   0.01214   0.00558  -0.0698   0.0336   1.0000
   7.500   1.1891   0.01266   0.00604  -0.0694   0.0228   1.0000
   7.750   1.2139   0.01307   0.00644  -0.0690   0.0185   1.0000
   8.000   1.2385   0.01350   0.00689  -0.0687   0.0149   1.0000
   8.250   1.2632   0.01389   0.00731  -0.0683   0.0130   1.0000
   8.500   1.2872   0.01437   0.00781  -0.0678   0.0109   1.0000
   8.750   1.3113   0.01481   0.00829  -0.0674   0.0096   1.0000
   9.000   1.3352   0.01526   0.00877  -0.0669   0.0087   1.0000
   9.250   1.3584   0.01578   0.00933  -0.0664   0.0076   1.0000
   9.500   1.3807   0.01642   0.01002  -0.0657   0.0065   1.0000
   9.750   1.4037   0.01691   0.01057  -0.0651   0.0063   1.0000
  10.000   1.4262   0.01744   0.01116  -0.0645   0.0058   1.0000
  10.250   1.4483   0.01800   0.01178  -0.0638   0.0054   1.0000
  10.500   1.4696   0.01860   0.01243  -0.0631   0.0049   1.0000
  10.750   1.4900   0.01930   0.01320  -0.0622   0.0045   1.0000
  11.000   1.5083   0.02020   0.01419  -0.0610   0.0041   1.0000
  11.250   1.5275   0.02093   0.01500  -0.0600   0.0040   1.0000
  11.500   1.5462   0.02166   0.01582  -0.0590   0.0039   1.0000
  11.750   1.5639   0.02244   0.01669  -0.0578   0.0037   1.0000
  12.000   1.5804   0.02327   0.01761  -0.0565   0.0035   1.0000
  12.250   1.5956   0.02416   0.01859  -0.0550   0.0034   1.0000
  12.500   1.6094   0.02510   0.01962  -0.0534   0.0032   1.0000
  12.750   1.6206   0.02606   0.02069  -0.0514   0.0031   1.0000
  13.000   1.6281   0.02710   0.02182  -0.0489   0.0030   1.0000
  13.250   1.6340   0.02829   0.02310  -0.0465   0.0029   1.0000
  13.500   1.6383   0.02968   0.02459  -0.0442   0.0028   1.0000
  13.750   1.6405   0.03135   0.02637  -0.0421   0.0027   1.0000
  14.000   1.6402   0.03341   0.02855  -0.0403   0.0026   1.0000
  14.250   1.6360   0.03604   0.03133  -0.0388   0.0025   1.0000
  14.500   1.6297   0.03919   0.03463  -0.0380   0.0024   1.0000
  14.750   1.6211   0.04298   0.03857  -0.0379   0.0023   1.0000
  15.000   1.6165   0.04657   0.04231  -0.0383   0.0023   1.0000
  15.250   1.6091   0.05084   0.04672  -0.0394   0.0023   1.0000
  15.500   1.6003   0.05556   0.05158  -0.0409   0.0023   1.0000
  15.750   1.5880   0.06108   0.05725  -0.0430   0.0023   1.0000
  16.000   1.5725   0.06729   0.06361  -0.0455   0.0023   1.0000
  16.250   1.5534   0.07428   0.07075  -0.0485   0.0023   1.0000
  16.500   1.5320   0.08180   0.07842  -0.0517   0.0023   1.0000
  16.750   1.5088   0.08975   0.08651  -0.0551   0.0023   1.0000
  17.000   1.4841   0.09815   0.09505  -0.0588   0.0023   1.0000
  17.250   1.4605   0.10644   0.10346  -0.0624   0.0023   1.0000
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