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GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il)
Reynolds number: 500,000
Max Cl/Cd: 104.29 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe137-il-500000.txt
Download as CSV file: xf-goe137-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 137 (MVA H.15) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3468   0.08580   0.08372  -0.0239   1.0000   0.0203
  -7.500  -0.3451   0.08280   0.08077  -0.0254   1.0000   0.0209
  -7.250  -0.3438   0.07966   0.07767  -0.0275   1.0000   0.0218
  -7.000  -0.3379   0.07528   0.07331  -0.0352   0.9983   0.0230
  -6.750  -0.3019   0.06849   0.06645  -0.0473   0.9934   0.0232
  -6.500  -0.2686   0.06159   0.05946  -0.0572   0.9878   0.0232
  -6.000  -0.2210   0.05138   0.04914  -0.0675   0.9746   0.0248
  -5.750  -0.1924   0.04792   0.04559  -0.0716   0.9650   0.0261
  -5.500  -0.1538   0.04281   0.04022  -0.0773   0.9531   0.0301
  -5.250  -0.1264   0.03723   0.03426  -0.0801   0.9389   0.0305
  -5.000  -0.1121   0.02963   0.02634  -0.0822   0.9234   0.0321
  -4.750  -0.0909   0.02862   0.02525  -0.0817   0.9060   0.0332
  -4.500  -0.0680   0.02695   0.02339  -0.0814   0.8870   0.0352
  -4.250  -0.0383   0.02673   0.02273  -0.0805   0.8663   0.0405
  -4.000  -0.0182   0.02094   0.01650  -0.0813   0.8451   0.0435
  -3.750   0.0074   0.00558   0.00069  -0.0772   0.7860   0.0384
  -3.500   0.0367   0.01844   0.01317  -0.0799   0.7997   0.0405
  -3.000   0.0899   0.01368   0.00759  -0.0794   0.7634   0.0388
  -2.750   0.1175   0.01298   0.00665  -0.0792   0.7477   0.0394
  -2.500   0.1455   0.01305   0.00656  -0.0790   0.7336   0.0406
  -2.250   0.1730   0.01191   0.00522  -0.0788   0.7213   0.0411
  -2.000   0.2005   0.01113   0.00431  -0.0786   0.7087   0.0417
  -1.750   0.2281   0.01056   0.00365  -0.0785   0.6969   0.0424
  -1.500   0.2558   0.01014   0.00316  -0.0783   0.6857   0.0439
  -1.250   0.2836   0.00987   0.00282  -0.0783   0.6755   0.0457
  -1.000   0.3117   0.00965   0.00255  -0.0782   0.6652   0.0470
  -0.750   0.3398   0.00947   0.00232  -0.0781   0.6551   0.0487
  -0.500   0.3679   0.00936   0.00213  -0.0781   0.6452   0.0506
  -0.250   0.3960   0.00928   0.00198  -0.0780   0.6347   0.0524
   0.000   0.4244   0.00916   0.00184  -0.0780   0.6246   0.0586
   0.250   0.4523   0.00892   0.00182  -0.0781   0.6154   0.1327
   0.500   0.4802   0.00870   0.00183  -0.0782   0.6058   0.2239
   0.750   0.5060   0.00679   0.00191  -0.0780   0.5966   1.0000
   1.000   0.5339   0.00689   0.00190  -0.0779   0.5871   1.0000
   1.250   0.5618   0.00698   0.00190  -0.0779   0.5765   1.0000
   1.500   0.5898   0.00706   0.00191  -0.0779   0.5655   1.0000
   1.750   0.6176   0.00717   0.00193  -0.0778   0.5539   1.0000
   2.000   0.6453   0.00728   0.00197  -0.0777   0.5415   1.0000
   2.250   0.6730   0.00740   0.00201  -0.0777   0.5294   1.0000
   2.500   0.7006   0.00752   0.00207  -0.0776   0.5166   1.0000
   2.750   0.7282   0.00765   0.00214  -0.0776   0.5030   1.0000
   3.000   0.7557   0.00780   0.00223  -0.0775   0.4889   1.0000
   3.250   0.7830   0.00796   0.00232  -0.0774   0.4748   1.0000
   3.500   0.8103   0.00812   0.00243  -0.0773   0.4610   1.0000
   3.750   0.8376   0.00830   0.00256  -0.0773   0.4483   1.0000
   4.000   0.8647   0.00849   0.00270  -0.0772   0.4341   1.0000
   4.250   0.8916   0.00869   0.00285  -0.0771   0.4194   1.0000
   4.500   0.9186   0.00889   0.00301  -0.0770   0.4075   1.0000
   4.750   0.9454   0.00910   0.00320  -0.0769   0.3951   1.0000
   5.000   0.9720   0.00932   0.00338  -0.0767   0.3790   1.0000
   5.250   0.9982   0.00960   0.00357  -0.0766   0.3592   1.0000
   5.500   1.0243   0.00988   0.00380  -0.0764   0.3416   1.0000
   5.750   1.0504   0.01016   0.00403  -0.0762   0.3209   1.0000
   6.000   1.0758   0.01051   0.00430  -0.0759   0.2975   1.0000
   6.250   1.1006   0.01093   0.00460  -0.0756   0.2653   1.0000
   6.500   1.1223   0.01173   0.00508  -0.0750   0.2069   1.0000
   6.750   1.1445   0.01246   0.00561  -0.0744   0.1770   1.0000
   7.000   1.1677   0.01304   0.00610  -0.0739   0.1594   1.0000
   7.250   1.1916   0.01351   0.00653  -0.0734   0.1393   1.0000
   7.500   1.2071   0.01498   0.00749  -0.0720   0.0607   1.0000
   7.750   1.2232   0.01633   0.00858  -0.0705   0.0213   1.0000
   8.000   1.2445   0.01703   0.00935  -0.0696   0.0187   1.0000
   8.250   1.2646   0.01784   0.01026  -0.0684   0.0169   1.0000
   8.500   1.2846   0.01859   0.01112  -0.0674   0.0162   1.0000
   8.750   1.3035   0.01940   0.01204  -0.0662   0.0155   1.0000
   9.000   1.3208   0.02031   0.01304  -0.0648   0.0146   1.0000
   9.250   1.3361   0.02133   0.01414  -0.0632   0.0138   1.0000
   9.500   1.3476   0.02256   0.01547  -0.0611   0.0132   1.0000
   9.750   1.3540   0.02405   0.01705  -0.0583   0.0127   1.0000
  10.000   1.3521   0.02580   0.01891  -0.0545   0.0124   1.0000
  10.250   1.3475   0.02796   0.02119  -0.0509   0.0121   1.0000
  10.500   1.3536   0.02947   0.02280  -0.0488   0.0120   1.0000
  10.750   1.3607   0.03097   0.02441  -0.0470   0.0118   1.0000
  11.000   1.3662   0.03272   0.02626  -0.0454   0.0116   1.0000
  11.250   1.3711   0.03464   0.02827  -0.0438   0.0114   1.0000
  11.500   1.3755   0.03670   0.03044  -0.0424   0.0113   1.0000
  11.750   1.3801   0.03881   0.03265  -0.0411   0.0111   1.0000
  12.000   1.3849   0.04097   0.03491  -0.0401   0.0108   1.0000
  12.250   1.3893   0.04321   0.03725  -0.0392   0.0105   1.0000
  12.500   1.3933   0.04553   0.03966  -0.0384   0.0102   1.0000
  12.750   1.3968   0.04796   0.04221  -0.0376   0.0100   1.0000
  13.000   1.3998   0.05049   0.04484  -0.0367   0.0098   1.0000
  13.250   1.4024   0.05313   0.04758  -0.0359   0.0097   1.0000
  13.500   1.4042   0.05591   0.05048  -0.0352   0.0096   1.0000
  13.750   1.4052   0.05881   0.05350  -0.0346   0.0095   1.0000
  14.000   1.4045   0.06199   0.05682  -0.0341   0.0095   1.0000
  14.250   1.4011   0.06560   0.06060  -0.0340   0.0095   1.0000
  14.500   1.3960   0.06942   0.06459  -0.0340   0.0095   1.0000
  14.750   1.3868   0.07396   0.06933  -0.0346   0.0096   1.0000
  15.000   1.3705   0.07978   0.07544  -0.0359   0.0098   1.0000
  15.250   1.3541   0.08582   0.08173  -0.0375   0.0100   1.0000
  15.500   1.3359   0.09249   0.08864  -0.0397   0.0103   1.0000
  15.750   1.3183   0.09927   0.09563  -0.0423   0.0106   1.0000
  16.000   1.3001   0.10642   0.10297  -0.0454   0.0109   1.0000
  16.250   1.2820   0.11387   0.11060  -0.0490   0.0112   1.0000
  16.500   1.2623   0.12189   0.11878  -0.0529   0.0115   1.0000
  17.000   1.0217   0.12104   0.11819  -0.0366   0.0108   1.0000
  17.250   1.0008   0.12688   0.12417  -0.0399   0.0110   1.0000
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