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GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.03 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe140-il-1000000-n5.txt
Download as CSV file: xf-goe140-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 140 (MVA H.17) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3291   0.09357   0.09191  -0.0215   0.9075   0.0076
  -8.500  -0.3367   0.08749   0.08568  -0.0242   0.8674   0.0087
  -8.250  -0.3294   0.08505   0.08311  -0.0257   0.8359   0.0089
  -8.000  -0.3206   0.08261   0.08058  -0.0276   0.8127   0.0090
  -7.750  -0.3074   0.07980   0.07769  -0.0308   0.7940   0.0092
  -7.500  -0.2929   0.07670   0.07453  -0.0345   0.7767   0.0095
  -7.250  -0.2771   0.07308   0.07084  -0.0391   0.7601   0.0100
  -7.000  -0.2606   0.06472   0.06238  -0.0499   0.7475   0.0117
  -6.750  -0.2389   0.06231   0.05987  -0.0533   0.7291   0.0119
  -6.500  -0.2163   0.05971   0.05717  -0.0569   0.7099   0.0122
  -6.250  -0.1924   0.05680   0.05415  -0.0608   0.6913   0.0126
  -6.000  -0.1590   0.04644   0.04354  -0.0731   0.6788   0.0152
  -5.750  -0.1332   0.04440   0.04136  -0.0754   0.6598   0.0155
  -5.500  -0.1069   0.04254   0.03937  -0.0774   0.6409   0.0157
  -5.250  -0.0800   0.04064   0.03733  -0.0793   0.6239   0.0161
  -5.000  -0.0526   0.03870   0.03525  -0.0812   0.6078   0.0166
  -4.750  -0.0233   0.03593   0.03229  -0.0836   0.5920   0.0174
  -4.500   0.0133   0.02896   0.02489  -0.0879   0.5800   0.0195
  -4.250   0.0445   0.02426   0.01979  -0.0903   0.5666   0.0203
  -4.000   0.0732   0.02249   0.01780  -0.0912   0.5506   0.0206
  -3.750   0.1022   0.02072   0.01578  -0.0920   0.5337   0.0208
  -3.500   0.1312   0.01925   0.01408  -0.0926   0.5160   0.0212
  -3.250   0.1599   0.01826   0.01289  -0.0931   0.4977   0.0216
  -3.000   0.1900   0.01597   0.01025  -0.0938   0.4802   0.0223
  -2.500   0.2485   0.01323   0.00696  -0.0947   0.4505   0.0237
  -2.250   0.2773   0.01254   0.00608  -0.0950   0.4379   0.0240
  -2.000   0.3061   0.01200   0.00538  -0.0952   0.4265   0.0242
  -1.750   0.3349   0.01155   0.00479  -0.0954   0.4158   0.0244
  -1.500   0.3636   0.01117   0.00429  -0.0956   0.4065   0.0246
  -1.250   0.3923   0.01083   0.00386  -0.0957   0.3988   0.0248
  -1.000   0.4210   0.01061   0.00356  -0.0959   0.3905   0.0250
  -0.750   0.4497   0.01043   0.00331  -0.0960   0.3835   0.0253
  -0.500   0.4784   0.01022   0.00303  -0.0962   0.3759   0.0255
  -0.250   0.5071   0.01004   0.00279  -0.0964   0.3695   0.0256
   0.000   0.5358   0.00991   0.00261  -0.0965   0.3622   0.0258
   0.250   0.5645   0.00983   0.00247  -0.0967   0.3556   0.0260
   0.500   0.5931   0.00979   0.00239  -0.0968   0.3482   0.0262
   0.750   0.6216   0.00977   0.00234  -0.0970   0.3417   0.0264
   1.000   0.6505   0.00962   0.00212  -0.0972   0.3354   0.0279
   1.250   0.6790   0.00963   0.00208  -0.0973   0.3275   0.0290
   1.500   0.7073   0.00967   0.00207  -0.0975   0.3178   0.0299
   1.750   0.7357   0.00972   0.00209  -0.0976   0.3098   0.0306
   2.000   0.7640   0.00977   0.00211  -0.0977   0.3037   0.0314
   2.250   0.7923   0.00983   0.00215  -0.0978   0.2986   0.0322
   2.500   0.8206   0.00987   0.00220  -0.0979   0.2941   0.0334
   2.750   0.8488   0.00994   0.00226  -0.0980   0.2889   0.0354
   3.000   0.8768   0.01002   0.00234  -0.0981   0.2840   0.0441
   3.250   0.9050   0.01007   0.00245  -0.0982   0.2801   0.0659
   3.500   0.9330   0.01016   0.00255  -0.0983   0.2747   0.0716
   3.750   0.9606   0.01030   0.00267  -0.0984   0.2653   0.0758
   4.250   1.0156   0.01061   0.00291  -0.0985   0.2464   0.0829
   4.500   1.0428   0.01078   0.00308  -0.0985   0.2358   0.0919
   4.750   1.0654   0.00951   0.00345  -0.0980   0.2234   1.0000
   5.000   1.0921   0.00979   0.00364  -0.0980   0.2092   1.0000
   5.250   1.1157   0.01054   0.00408  -0.0976   0.1558   1.0000
   5.500   1.1374   0.01158   0.00481  -0.0970   0.0957   1.0000
   5.750   1.1571   0.01292   0.00574  -0.0960   0.0161   1.0000
   6.000   1.1830   0.01323   0.00605  -0.0958   0.0128   1.0000
   6.250   1.2091   0.01351   0.00635  -0.0957   0.0116   1.0000
   6.500   1.2348   0.01382   0.00668  -0.0954   0.0106   1.0000
   6.750   1.2602   0.01417   0.00705  -0.0952   0.0096   1.0000
   7.000   1.2851   0.01456   0.00748  -0.0949   0.0087   1.0000
   7.250   1.3101   0.01490   0.00784  -0.0946   0.0080   1.0000
   7.500   1.3348   0.01528   0.00823  -0.0942   0.0074   1.0000
   7.750   1.3589   0.01569   0.00866  -0.0938   0.0069   1.0000
   8.000   1.3822   0.01618   0.00919  -0.0933   0.0064   1.0000
   8.250   1.4049   0.01671   0.00978  -0.0927   0.0061   1.0000
   8.500   1.4278   0.01719   0.01029  -0.0921   0.0058   1.0000
   8.750   1.4503   0.01768   0.01081  -0.0915   0.0055   1.0000
   9.000   1.4723   0.01818   0.01134  -0.0908   0.0051   1.0000
   9.250   1.4937   0.01870   0.01189  -0.0901   0.0048   1.0000
   9.500   1.5141   0.01929   0.01253  -0.0892   0.0046   1.0000
   9.750   1.5321   0.02005   0.01335  -0.0880   0.0044   1.0000
  10.000   1.5488   0.02087   0.01424  -0.0866   0.0042   1.0000
  10.250   1.5656   0.02160   0.01504  -0.0852   0.0041   1.0000
  10.500   1.5804   0.02241   0.01592  -0.0835   0.0040   1.0000
  10.750   1.5927   0.02329   0.01688  -0.0815   0.0038   1.0000
  11.000   1.6002   0.02425   0.01791  -0.0787   0.0037   1.0000
  11.250   1.6060   0.02533   0.01909  -0.0759   0.0036   1.0000
  11.500   1.6111   0.02659   0.02044  -0.0734   0.0035   1.0000
  11.750   1.6154   0.02806   0.02200  -0.0712   0.0034   1.0000
  12.000   1.6196   0.02970   0.02372  -0.0694   0.0033   1.0000
  12.250   1.6234   0.03155   0.02565  -0.0680   0.0033   1.0000
  12.500   1.6270   0.03361   0.02780  -0.0670   0.0032   1.0000
  12.750   1.6299   0.03590   0.03017  -0.0664   0.0031   1.0000
  13.000   1.6299   0.03870   0.03307  -0.0660   0.0031   1.0000
  13.250   1.6282   0.04188   0.03634  -0.0659   0.0030   1.0000
  13.500   1.6242   0.04552   0.04009  -0.0662   0.0029   1.0000
  13.750   1.6160   0.04990   0.04460  -0.0668   0.0029   1.0000
  14.000   1.6029   0.05509   0.04993  -0.0677   0.0028   1.0000
  14.250   1.5870   0.06076   0.05574  -0.0688   0.0028   1.0000
  14.500   1.5717   0.06641   0.06151  -0.0700   0.0028   1.0000
  14.750   1.5587   0.07176   0.06698  -0.0711   0.0028   1.0000
  15.000   1.5459   0.07721   0.07254  -0.0723   0.0027   1.0000
  15.250   1.5325   0.08277   0.07821  -0.0736   0.0027   1.0000
  15.500   1.5193   0.08839   0.08393  -0.0750   0.0027   1.0000
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