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GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il)
Reynolds number: 1,000,000
Max Cl/Cd: 91.89 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe116-il-1000000-n5.txt
Download as CSV file: xf-goe116-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 116 (MVA MK.3) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4115   0.08618   0.08395  -0.0315   0.7709   0.0025
  -8.750  -0.4131   0.08100   0.07877  -0.0344   0.7630   0.0025
  -8.500  -0.4172   0.07516   0.07292  -0.0379   0.7561   0.0024
  -8.250  -0.4271   0.06752   0.06529  -0.0434   0.7491   0.0023
  -8.000  -0.4311   0.05490   0.05259  -0.0591   0.7430   0.0022
  -7.750  -0.4176   0.03586   0.03308  -0.0825   0.7377   0.0022
  -7.500  -0.4000   0.02924   0.02594  -0.0876   0.7317   0.0021
  -7.250  -0.3800   0.02483   0.02105  -0.0896   0.7261   0.0021
  -7.000  -0.3577   0.02146   0.01725  -0.0904   0.7200   0.0021
  -6.750  -0.3337   0.01873   0.01410  -0.0907   0.7145   0.0021
  -6.500  -0.3084   0.01648   0.01152  -0.0908   0.7092   0.0022
  -6.250  -0.2823   0.01475   0.00951  -0.0909   0.7040   0.0025
  -6.000  -0.2553   0.01364   0.00818  -0.0910   0.6993   0.0027
  -5.750  -0.2277   0.01289   0.00728  -0.0911   0.6941   0.0029
  -5.500  -0.2002   0.01196   0.00617  -0.0913   0.6889   0.0030
  -5.250  -0.1723   0.01141   0.00550  -0.0916   0.6843   0.0033
  -5.000  -0.1441   0.01108   0.00512  -0.0918   0.6796   0.0036
  -4.750  -0.1159   0.01074   0.00469  -0.0921   0.6749   0.0040
  -4.500  -0.0875   0.01028   0.00412  -0.0923   0.6706   0.0044
  -4.250  -0.0589   0.00987   0.00360  -0.0925   0.6661   0.0047
  -4.000  -0.0304   0.00945   0.00305  -0.0927   0.6617   0.0052
  -3.750  -0.0019   0.00916   0.00268  -0.0929   0.6576   0.0059
  -3.500   0.0268   0.00895   0.00243  -0.0931   0.6534   0.0070
  -3.250   0.0554   0.00881   0.00224  -0.0933   0.6490   0.0079
  -3.000   0.0840   0.00856   0.00187  -0.0935   0.6449   0.0103
  -2.750   0.1128   0.00842   0.00166  -0.0937   0.6410   0.0132
  -2.500   0.1415   0.00831   0.00150  -0.0939   0.6365   0.0211
  -2.250   0.1694   0.00774   0.00132  -0.0944   0.6323   0.1242
  -2.000   0.1981   0.00778   0.00133  -0.0946   0.6285   0.1316
  -1.750   0.2269   0.00776   0.00131  -0.0948   0.6247   0.1361
  -1.500   0.2556   0.00778   0.00135  -0.0951   0.6208   0.1412
  -1.250   0.2843   0.00777   0.00130  -0.0953   0.6171   0.1424
  -1.000   0.3130   0.00774   0.00126  -0.0955   0.6139   0.1432
  -0.750   0.3417   0.00771   0.00121  -0.0958   0.6103   0.1439
  -0.500   0.3704   0.00769   0.00118  -0.0960   0.6065   0.1446
  -0.250   0.3991   0.00769   0.00116  -0.0963   0.6031   0.1452
   0.000   0.4277   0.00768   0.00115  -0.0965   0.5999   0.1457
   0.250   0.4564   0.00767   0.00115  -0.0967   0.5951   0.1463
   0.500   0.4849   0.00766   0.00113  -0.0970   0.5894   0.1477
   0.750   0.5135   0.00765   0.00113  -0.0972   0.5843   0.1492
   1.000   0.5421   0.00763   0.00114  -0.0975   0.5793   0.1506
   1.250   0.5704   0.00766   0.00116  -0.0977   0.5725   0.1520
   1.500   0.5989   0.00766   0.00119  -0.0979   0.5639   0.1534
   1.750   0.6272   0.00769   0.00123  -0.0981   0.5562   0.1548
   2.000   0.6557   0.00771   0.00128  -0.0983   0.5495   0.1563
   2.250   0.6839   0.00775   0.00134  -0.0985   0.5424   0.1578
   2.500   0.7117   0.00786   0.00140  -0.0986   0.5202   0.1592
   2.750   0.7388   0.00804   0.00150  -0.0986   0.4903   0.1604
   3.000   0.7643   0.00845   0.00170  -0.0984   0.4339   0.1627
   3.250   0.7797   0.01031   0.00255  -0.0971   0.2122   0.1652
   3.500   0.7994   0.01150   0.00317  -0.0962   0.0757   0.1679
   3.750   0.8230   0.01211   0.00360  -0.0957   0.0148   0.1711
   4.000   0.8492   0.01236   0.00391  -0.0955   0.0091   0.1745
   4.250   0.8756   0.01257   0.00418  -0.0954   0.0078   0.1811
   4.750   0.9263   0.01319   0.00495  -0.0948   0.0053   0.2078
   5.000   0.9523   0.01313   0.00534  -0.0949   0.0047   0.4176
   5.500   0.9972   0.01270   0.00626  -0.0934   0.0037   1.0000
   5.750   1.0194   0.01336   0.00698  -0.0925   0.0033   1.0000
   6.000   1.0421   0.01393   0.00760  -0.0918   0.0031   1.0000
   6.250   1.0637   0.01459   0.00834  -0.0908   0.0029   1.0000
   6.500   1.0843   0.01530   0.00912  -0.0897   0.0027   1.0000
   6.750   1.1055   0.01592   0.00979  -0.0888   0.0024   1.0000
   7.000   1.1271   0.01645   0.01035  -0.0880   0.0022   1.0000
   7.250   1.1477   0.01705   0.01101  -0.0871   0.0021   1.0000
   7.500   1.1660   0.01782   0.01184  -0.0857   0.0020   1.0000
   7.750   1.1803   0.01893   0.01304  -0.0838   0.0019   1.0000
   8.000   1.1912   0.02037   0.01460  -0.0812   0.0018   1.0000
   8.250   1.2059   0.02145   0.01578  -0.0793   0.0017   1.0000
   8.500   1.2185   0.02271   0.01715  -0.0770   0.0016   1.0000
   8.750   1.2305   0.02444   0.01905  -0.0745   0.0015   1.0000
   9.000   1.2546   0.02941   0.02438  -0.0733   0.0013   1.0000
   9.250   1.2729   0.03461   0.02998  -0.0713   0.0012   1.0000
   9.500   1.2819   0.03914   0.03486  -0.0683   0.0012   1.0000
   9.750   1.2852   0.04338   0.03942  -0.0650   0.0012   1.0000
  10.000   1.2832   0.04739   0.04373  -0.0613   0.0013   1.0000
  10.250   1.2764   0.05104   0.04762  -0.0573   0.0013   1.0000
  10.500   1.2631   0.05418   0.05097  -0.0528   0.0013   1.0000
  10.750   1.2479   0.05748   0.05446  -0.0490   0.0013   1.0000
  11.000   1.2316   0.06111   0.05827  -0.0461   0.0014   1.0000
  11.250   1.2144   0.06497   0.06229  -0.0441   0.0014   1.0000
  11.500   1.1958   0.06926   0.06674  -0.0428   0.0014   1.0000
  11.750   1.1770   0.07387   0.07151  -0.0423   0.0014   1.0000
  12.000   1.1570   0.07897   0.07675  -0.0425   0.0014   1.0000
  12.250   1.1372   0.08441   0.08233  -0.0435   0.0014   1.0000
  12.500   1.1164   0.09038   0.08843  -0.0453   0.0014   1.0000
  12.750   1.0950   0.09699   0.09516  -0.0479   0.0015   1.0000
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