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GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.75 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe137-il-1000000.txt
Download as CSV file: xf-goe137-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4540   0.14673   0.14508   0.0055   1.0000   0.0090
 -12.000  -0.4475   0.14316   0.14151   0.0041   1.0000   0.0096
  -7.000  -0.3381   0.01711   0.01363  -0.0825   0.9609   0.0145
  -6.750  -0.3116   0.01753   0.01410  -0.0819   0.9517   0.0148
  -6.500  -0.2859   0.01806   0.01466  -0.0812   0.9414   0.0151
  -6.250  -0.2610   0.01761   0.01411  -0.0807   0.9292   0.0157
  -6.000  -0.2368   0.01612   0.01231  -0.0802   0.9160   0.0168
  -5.750  -0.2112   0.01550   0.01148  -0.0796   0.9011   0.0177
  -5.500  -0.1868   0.01414   0.00984  -0.0793   0.8838   0.0188
  -5.250  -0.1602   0.01428   0.00994  -0.0790   0.8628   0.0194
  -5.000  -0.1339   0.01417   0.00971  -0.0786   0.8379   0.0201
  -4.750  -0.1073   0.01380   0.00914  -0.0782   0.8099   0.0211
  -4.500  -0.0804   0.01339   0.00849  -0.0780   0.7823   0.0222
  -4.250  -0.0526   0.01361   0.00856  -0.0778   0.7581   0.0230
  -4.000  -0.0263   0.01192   0.00657  -0.0777   0.7392   0.0247
  -3.750   0.0013   0.01164   0.00619  -0.0777   0.7233   0.0256
  -3.500   0.0292   0.01137   0.00581  -0.0777   0.7094   0.0266
  -3.250   0.0573   0.01110   0.00545  -0.0777   0.6971   0.0278
  -3.000   0.0854   0.01073   0.00497  -0.0777   0.6851   0.0287
  -2.750   0.1135   0.01042   0.00455  -0.0776   0.6737   0.0295
  -2.500   0.1417   0.01023   0.00427  -0.0776   0.6625   0.0301
  -2.250   0.1699   0.00982   0.00377  -0.0776   0.6522   0.0311
  -2.000   0.1977   0.00916   0.00302  -0.0776   0.6429   0.0319
  -1.500   0.2541   0.00852   0.00228  -0.0776   0.6254   0.0334
  -1.250   0.2824   0.00834   0.00204  -0.0776   0.6169   0.0345
  -1.000   0.3109   0.00820   0.00187  -0.0777   0.6071   0.0359
  -0.750   0.3393   0.00808   0.00170  -0.0777   0.5979   0.0371
  -0.250   0.3963   0.00791   0.00145  -0.0778   0.5806   0.0394
   0.000   0.4247   0.00787   0.00136  -0.0779   0.5718   0.0402
   0.250   0.4532   0.00782   0.00126  -0.0779   0.5618   0.0422
   0.500   0.4817   0.00776   0.00118  -0.0780   0.5514   0.0504
   0.750   0.5099   0.00755   0.00120  -0.0782   0.5405   0.1451
   1.000   0.5380   0.00743   0.00123  -0.0783   0.5289   0.2159
   1.250   0.5634   0.00625   0.00136  -0.0785   0.5165   0.7340
   2.250   0.6745   0.00613   0.00151  -0.0781   0.4585   1.0000
   2.500   0.7023   0.00627   0.00158  -0.0781   0.4445   1.0000
   2.750   0.7302   0.00641   0.00165  -0.0782   0.4316   1.0000
   3.000   0.7580   0.00655   0.00174  -0.0782   0.4195   1.0000
   3.250   0.7856   0.00672   0.00183  -0.0782   0.4047   1.0000
   3.500   0.8131   0.00689   0.00193  -0.0782   0.3899   1.0000
   3.750   0.8407   0.00705   0.00205  -0.0782   0.3777   1.0000
   4.000   0.8682   0.00723   0.00217  -0.0782   0.3643   1.0000
   4.250   0.8955   0.00742   0.00230  -0.0781   0.3494   1.0000
   4.500   0.9225   0.00764   0.00244  -0.0781   0.3321   1.0000
   4.750   0.9493   0.00790   0.00261  -0.0780   0.3130   1.0000
   5.000   0.9759   0.00817   0.00279  -0.0779   0.2897   1.0000
   5.250   1.0018   0.00853   0.00301  -0.0778   0.2597   1.0000
   5.500   1.0259   0.00915   0.00337  -0.0774   0.2076   1.0000
   5.750   1.0503   0.00969   0.00373  -0.0771   0.1777   1.0000
   6.000   1.0759   0.01006   0.00403  -0.0768   0.1638   1.0000
   6.250   1.1019   0.01035   0.00429  -0.0767   0.1538   1.0000
   6.500   1.1276   0.01067   0.00457  -0.0765   0.1411   1.0000
   6.750   1.1481   0.01166   0.00516  -0.0757   0.0769   1.0000
   7.000   1.1655   0.01304   0.00617  -0.0743   0.0180   1.0000
   7.250   1.1901   0.01344   0.00662  -0.0739   0.0154   1.0000
   7.500   1.2139   0.01392   0.00715  -0.0734   0.0138   1.0000
   7.750   1.2365   0.01456   0.00786  -0.0726   0.0123   1.0000
   8.000   1.2598   0.01505   0.00840  -0.0720   0.0117   1.0000
   8.250   1.2829   0.01553   0.00893  -0.0714   0.0111   1.0000
   8.500   1.3052   0.01608   0.00952  -0.0707   0.0103   1.0000
   8.750   1.3264   0.01671   0.01021  -0.0699   0.0098   1.0000
   9.000   1.3453   0.01756   0.01113  -0.0687   0.0092   1.0000
   9.250   1.3565   0.01908   0.01279  -0.0664   0.0086   1.0000
   9.500   1.3766   0.01965   0.01342  -0.0654   0.0084   1.0000
   9.750   1.3945   0.02038   0.01421  -0.0642   0.0082   1.0000
  10.000   1.4104   0.02122   0.01513  -0.0626   0.0079   1.0000
  10.250   1.4240   0.02215   0.01613  -0.0608   0.0077   1.0000
  10.500   1.4347   0.02306   0.01711  -0.0585   0.0074   1.0000
  10.750   1.4443   0.02399   0.01810  -0.0562   0.0071   1.0000
  11.000   1.4529   0.02503   0.01921  -0.0540   0.0068   1.0000
  11.250   1.4607   0.02622   0.02045  -0.0520   0.0066   1.0000
  11.500   1.4638   0.02784   0.02215  -0.0498   0.0064   1.0000
  11.750   1.4612   0.03010   0.02451  -0.0475   0.0062   1.0000
  12.000   1.4518   0.03323   0.02775  -0.0453   0.0061   1.0000
  12.250   1.4431   0.03657   0.03121  -0.0434   0.0060   1.0000
  12.500   1.4497   0.03851   0.03324  -0.0429   0.0059   1.0000
  12.750   1.4540   0.04078   0.03562  -0.0424   0.0058   1.0000
  13.000   1.4569   0.04325   0.03819  -0.0420   0.0057   1.0000
  13.250   1.4582   0.04597   0.04100  -0.0417   0.0057   1.0000
  13.500   1.4580   0.04889   0.04403  -0.0414   0.0056   1.0000
  13.750   1.4572   0.05192   0.04717  -0.0413   0.0055   1.0000
  14.000   1.4553   0.05513   0.05049  -0.0412   0.0054   1.0000
  14.250   1.4524   0.05850   0.05397  -0.0412   0.0054   1.0000
  14.500   1.4490   0.06200   0.05758  -0.0413   0.0053   1.0000
  14.750   1.4449   0.06570   0.06140  -0.0417   0.0052   1.0000
  15.000   1.4399   0.06960   0.06542  -0.0422   0.0052   1.0000
  15.250   1.4345   0.07368   0.06961  -0.0429   0.0051   1.0000
  15.500   1.4280   0.07802   0.07407  -0.0438   0.0050   1.0000
  15.750   1.4213   0.08255   0.07872  -0.0450   0.0050   1.0000
  16.000   1.4133   0.08735   0.08365  -0.0463   0.0049   1.0000
  16.250   1.4054   0.09229   0.08871  -0.0480   0.0049   1.0000
  16.500   1.3960   0.09761   0.09415  -0.0498   0.0048   1.0000
  16.750   1.3865   0.10309   0.09976  -0.0519   0.0048   1.0000
  17.000   1.3761   0.10880   0.10560  -0.0542   0.0048   1.0000
  17.250   1.3657   0.11469   0.11161  -0.0568   0.0047   1.0000
  17.500   1.3531   0.12112   0.11818  -0.0598   0.0047   1.0000
  17.750   1.3402   0.12782   0.12502  -0.0630   0.0047   1.0000
  18.000   1.3287   0.13438   0.13169  -0.0665   0.0047   1.0000
  18.250   1.3140   0.14183   0.13928  -0.0705   0.0047   1.0000
  18.500   1.2996   0.14952   0.14711  -0.0748   0.0047   1.0000
  18.750   1.2865   0.15724   0.15496  -0.0795   0.0047   1.0000
  19.000   1.2706   0.16603   0.16390  -0.0849   0.0047   1.0000
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