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GOE 311 (MVA H.43) AIRFOIL (goe311-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 311 (MVA H.43) AIRFOIL (goe311-il)
Reynolds number: 1,000,000
Max Cl/Cd: 136.18 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe311-il-1000000.txt
Download as CSV file: xf-goe311-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 311 (MVA H.43) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3327   0.11132   0.10981  -0.0166   0.9680   0.0115
  -9.500  -0.2371   0.09327   0.09172  -0.0277   0.9079   0.0133
  -7.750  -0.3809   0.03257   0.02993  -0.0743   0.8628   0.0095
  -7.500  -0.3657   0.02082   0.01731  -0.0796   0.8466   0.0096
  -7.250  -0.3441   0.01633   0.01225  -0.0805   0.8271   0.0101
  -7.000  -0.3187   0.01500   0.01064  -0.0804   0.8057   0.0105
  -6.750  -0.2923   0.01410   0.00951  -0.0804   0.7855   0.0109
  -6.500  -0.2653   0.01334   0.00854  -0.0803   0.7683   0.0114
  -6.250  -0.2380   0.01267   0.00765  -0.0803   0.7534   0.0118
  -6.000  -0.2104   0.01211   0.00690  -0.0802   0.7403   0.0123
  -5.750  -0.1824   0.01166   0.00630  -0.0802   0.7284   0.0127
  -5.500  -0.1547   0.01090   0.00534  -0.0802   0.7173   0.0138
  -5.000  -0.0984   0.01006   0.00424  -0.0802   0.6936   0.0165
  -4.750  -0.0700   0.00968   0.00375  -0.0802   0.6799   0.0191
  -4.500  -0.0417   0.00944   0.00356  -0.0802   0.6628   0.0292
  -4.250  -0.0127   0.00977   0.00386  -0.0803   0.6387   0.0355
  -4.000   0.0159   0.00996   0.00397  -0.0803   0.6053   0.0388
  -3.750   0.0444   0.01021   0.00410  -0.0804   0.5789   0.0413
  -3.500   0.0731   0.01043   0.00423  -0.0805   0.5639   0.0432
  -3.250   0.1019   0.01067   0.00440  -0.0806   0.5542   0.0441
  -3.000   0.1297   0.01009   0.00367  -0.0806   0.5470   0.0463
  -2.750   0.1579   0.00986   0.00339  -0.0807   0.5411   0.0481
  -2.500   0.1863   0.00971   0.00321  -0.0808   0.5364   0.0497
  -2.250   0.2147   0.00959   0.00304  -0.0809   0.5322   0.0511
  -2.000   0.2431   0.00951   0.00290  -0.0809   0.5281   0.0527
  -1.750   0.2716   0.00936   0.00272  -0.0810   0.5250   0.0534
  -1.500   0.3001   0.00921   0.00253  -0.0810   0.5220   0.0537
  -1.250   0.3286   0.00910   0.00237  -0.0811   0.5190   0.0539
  -1.000   0.3570   0.00901   0.00224  -0.0811   0.5158   0.0543
  -0.750   0.3853   0.00897   0.00214  -0.0812   0.5123   0.0547
  -0.500   0.4139   0.00887   0.00204  -0.0813   0.5101   0.0551
  -0.250   0.4425   0.00880   0.00197  -0.0813   0.5066   0.0556
   0.000   0.4709   0.00872   0.00184  -0.0814   0.5025   0.0580
   0.250   0.4991   0.00871   0.00179  -0.0814   0.4981   0.0604
   0.500   0.5276   0.00866   0.00175  -0.0815   0.4950   0.0633
   0.750   0.5562   0.00860   0.00171  -0.0816   0.4918   0.0668
   1.000   0.5845   0.00851   0.00172  -0.0818   0.4883   0.0992
   1.250   0.6129   0.00854   0.00178  -0.0819   0.4844   0.1158
   1.500   0.6412   0.00858   0.00183  -0.0820   0.4805   0.1241
   1.750   0.6699   0.00857   0.00186  -0.0821   0.4761   0.1309
   2.000   0.6983   0.00861   0.00188  -0.0822   0.4710   0.1346
   2.250   0.7265   0.00865   0.00193  -0.0823   0.4663   0.1400
   2.500   0.7551   0.00865   0.00197  -0.0825   0.4628   0.1448
   2.750   0.7835   0.00867   0.00202  -0.0826   0.4591   0.1477
   3.000   0.8117   0.00868   0.00205  -0.0828   0.4552   0.1534
   3.250   0.8398   0.00873   0.00211  -0.0829   0.4512   0.1586
   3.500   0.8683   0.00874   0.00216  -0.0831   0.4472   0.1622
   3.750   0.8965   0.00874   0.00221  -0.0832   0.4422   0.1702
   4.000   0.9245   0.00880   0.00228  -0.0833   0.4370   0.1794
   4.250   0.9528   0.00878   0.00236  -0.0835   0.4315   0.2026
   4.500   0.9806   0.00874   0.00251  -0.0837   0.4245   0.2926
   4.750   1.0044   0.00747   0.00270  -0.0831   0.4175   0.9942
   5.000   1.0336   0.00759   0.00277  -0.0835   0.4046   1.0000
   5.250   1.0600   0.00784   0.00289  -0.0834   0.3773   1.0000
   5.500   1.0855   0.00822   0.00310  -0.0832   0.3434   1.0000
   5.750   1.1098   0.00874   0.00341  -0.0829   0.3045   1.0000
   6.000   1.1328   0.00941   0.00382  -0.0825   0.2570   1.0000
   6.250   1.1555   0.01010   0.00427  -0.0819   0.2130   1.0000
   6.500   1.1787   0.01069   0.00468  -0.0815   0.1822   1.0000
   6.750   1.2015   0.01130   0.00511  -0.0810   0.1530   1.0000
   7.000   1.2191   0.01245   0.00589  -0.0798   0.0877   1.0000
   7.250   1.2422   0.01294   0.00634  -0.0793   0.0774   1.0000
   7.500   1.2657   0.01337   0.00676  -0.0788   0.0682   1.0000
   7.750   1.2813   0.01456   0.00766  -0.0772   0.0197   1.0000
   8.000   1.3025   0.01515   0.00826  -0.0763   0.0153   1.0000
   8.250   1.3244   0.01563   0.00879  -0.0756   0.0139   1.0000
   8.500   1.3456   0.01614   0.00935  -0.0748   0.0129   1.0000
   8.750   1.3654   0.01674   0.01000  -0.0737   0.0119   1.0000
   9.000   1.3820   0.01757   0.01089  -0.0722   0.0109   1.0000
   9.250   1.3976   0.01840   0.01181  -0.0706   0.0103   1.0000
   9.500   1.4156   0.01897   0.01242  -0.0693   0.0099   1.0000
   9.750   1.4308   0.01962   0.01313  -0.0676   0.0094   1.0000
  10.000   1.4421   0.02037   0.01394  -0.0653   0.0089   1.0000
  10.250   1.4523   0.02125   0.01488  -0.0631   0.0086   1.0000
  10.500   1.4611   0.02230   0.01599  -0.0609   0.0082   1.0000
  10.750   1.4664   0.02367   0.01743  -0.0586   0.0079   1.0000
  11.000   1.4635   0.02579   0.01967  -0.0558   0.0076   1.0000
  11.250   1.4564   0.02847   0.02249  -0.0532   0.0074   1.0000
  11.500   1.4653   0.02996   0.02406  -0.0522   0.0072   1.0000
  11.750   1.4712   0.03181   0.02599  -0.0512   0.0071   1.0000
  12.000   1.4762   0.03387   0.02814  -0.0504   0.0070   1.0000
  12.250   1.4791   0.03621   0.03057  -0.0496   0.0068   1.0000
  12.500   1.4807   0.03876   0.03320  -0.0490   0.0067   1.0000
  12.750   1.4812   0.04148   0.03601  -0.0485   0.0065   1.0000
  13.000   1.4816   0.04424   0.03886  -0.0480   0.0064   1.0000
  13.250   1.4823   0.04702   0.04172  -0.0477   0.0062   1.0000
  13.500   1.4826   0.04992   0.04469  -0.0475   0.0060   1.0000
  13.750   1.4832   0.05282   0.04767  -0.0475   0.0059   1.0000
  14.000   1.4832   0.05589   0.05082  -0.0475   0.0057   1.0000
  14.250   1.4819   0.05919   0.05418  -0.0477   0.0056   1.0000
  14.500   1.4786   0.06274   0.05781  -0.0479   0.0055   1.0000
  14.750   1.4733   0.06655   0.06170  -0.0481   0.0054   1.0000
  15.000   1.4658   0.07063   0.06587  -0.0482   0.0053   1.0000
  15.250   1.4537   0.07507   0.07039  -0.0479   0.0051   1.0000
  15.500   1.4445   0.07891   0.07432  -0.0471   0.0050   1.0000
  15.750   1.4436   0.08245   0.07796  -0.0477   0.0050   1.0000
  16.000   1.4422   0.08610   0.08170  -0.0484   0.0049   1.0000
  16.250   1.4402   0.08974   0.08544  -0.0489   0.0049   1.0000
  16.500   1.4373   0.09356   0.08936  -0.0496   0.0048   1.0000
  16.750   1.4341   0.09746   0.09336  -0.0503   0.0048   1.0000
  17.000   1.4308   0.10144   0.09744  -0.0512   0.0047   1.0000
  17.250   1.4264   0.10561   0.10172  -0.0521   0.0046   1.0000
  17.500   1.4217   0.10987   0.10608  -0.0532   0.0046   1.0000
  17.750   1.4169   0.11426   0.11059  -0.0545   0.0045   1.0000
  18.000   1.4109   0.11889   0.11534  -0.0559   0.0045   1.0000
  18.250   1.4046   0.12369   0.12027  -0.0576   0.0044   1.0000
  18.500   1.3980   0.12865   0.12535  -0.0595   0.0044   1.0000
  18.750   1.3905   0.13384   0.13065  -0.0617   0.0044   1.0000
  19.000   1.3827   0.13925   0.13619  -0.0641   0.0043   1.0000
  19.250   1.3739   0.14500   0.14207  -0.0669   0.0043   1.0000
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