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GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il)
Reynolds number: 100,000
Max Cl/Cd: 58.54 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe117-il-100000-n5.txt
Download as CSV file: xf-goe117-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 117 (MVA MK.4) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3341   0.09122   0.08661  -0.0410   1.0000   0.0305
  -8.000  -0.3409   0.08882   0.08431  -0.0401   1.0000   0.0303
  -7.750  -0.3535   0.08686   0.08247  -0.0383   1.0000   0.0306
  -7.500  -0.3699   0.08547   0.08120  -0.0353   1.0000   0.0302
  -7.250  -0.3530   0.07981   0.07555  -0.0429   0.9901   0.0301
  -7.000  -0.3346   0.07376   0.06948  -0.0512   0.9798   0.0296
  -6.750  -0.3151   0.06727   0.06295  -0.0600   0.9693   0.0293
  -6.500  -0.2932   0.06012   0.05571  -0.0693   0.9589   0.0291
  -6.250  -0.2673   0.05114   0.04652  -0.0801   0.9495   0.0291
  -6.000  -0.2391   0.04018   0.03495  -0.0910   0.9407   0.0303
  -5.750  -0.2124   0.03350   0.02734  -0.0960   0.9318   0.0326
  -5.500  -0.1797   0.02938   0.02228  -0.0990   0.9258   0.0340
  -5.250  -0.1540   0.02647   0.01909  -0.1001   0.9173   0.0373
  -5.000  -0.1201   0.02452   0.01671  -0.1019   0.9114   0.0417
  -4.750  -0.0909   0.02281   0.01452  -0.1022   0.9025   0.0449
  -4.500  -0.0572   0.02117   0.01262  -0.1038   0.8965   0.0499
  -4.250  -0.0290   0.02007   0.01132  -0.1038   0.8866   0.0528
  -4.000   0.0024   0.01925   0.01024  -0.1045   0.8780   0.0579
  -3.750   0.0334   0.01831   0.00912  -0.1050   0.8691   0.0609
  -3.500   0.0614   0.01758   0.00827  -0.1050   0.8582   0.0637
  -3.250   0.0905   0.01699   0.00752  -0.1051   0.8476   0.0681
  -3.000   0.1204   0.01643   0.00682  -0.1053   0.8376   0.0752
  -2.750   0.1487   0.01577   0.00629  -0.1054   0.8265   0.0983
  -2.500   0.1761   0.01543   0.00602  -0.1052   0.8140   0.1650
  -2.250   0.2034   0.01525   0.00592  -0.1051   0.8013   0.2091
  -2.000   0.2310   0.01525   0.00589  -0.1050   0.7885   0.2503
  -1.750   0.2585   0.01518   0.00573  -0.1048   0.7760   0.2731
  -1.500   0.2862   0.01509   0.00554  -0.1046   0.7639   0.2957
  -1.250   0.3136   0.01492   0.00534  -0.1044   0.7520   0.3187
  -1.000   0.3408   0.01476   0.00512  -0.1042   0.7400   0.3368
  -0.750   0.3676   0.01462   0.00495  -0.1039   0.7279   0.3555
  -0.500   0.3946   0.01448   0.00481  -0.1037   0.7171   0.3794
  -0.250   0.4216   0.01432   0.00471  -0.1036   0.7076   0.4155
   0.000   0.4475   0.01406   0.00465  -0.1032   0.6983   0.4887
   0.250   0.4929   0.01299   0.00457  -0.1063   0.6892   1.0000
   0.500   0.5199   0.01313   0.00451  -0.1060   0.6815   1.0000
   0.750   0.5458   0.01329   0.00456  -0.1057   0.6731   1.0000
   1.000   0.5726   0.01346   0.00458  -0.1054   0.6663   1.0000
   1.250   0.5985   0.01364   0.00469  -0.1051   0.6587   1.0000
   1.500   0.6254   0.01383   0.00476  -0.1049   0.6526   1.0000
   1.750   0.6511   0.01404   0.00496  -0.1045   0.6455   1.0000
   2.000   0.6779   0.01425   0.00510  -0.1043   0.6398   1.0000
   2.250   0.7035   0.01449   0.00533  -0.1039   0.6332   1.0000
   2.500   0.7298   0.01472   0.00556  -0.1037   0.6272   1.0000
   2.750   0.7558   0.01497   0.00581  -0.1034   0.6211   1.0000
   3.000   0.7814   0.01523   0.00610  -0.1030   0.6147   1.0000
   3.250   0.8081   0.01549   0.00636  -0.1028   0.6092   1.0000
   3.500   0.8328   0.01577   0.00677  -0.1023   0.6024   1.0000
   3.750   0.8592   0.01605   0.00710  -0.1020   0.5970   1.0000
   4.000   0.8842   0.01637   0.00753  -0.1016   0.5911   1.0000
   4.250   0.9096   0.01667   0.00799  -0.1011   0.5851   1.0000
   4.500   0.9333   0.01690   0.00831  -0.1002   0.5737   1.0000
   4.750   0.9549   0.01693   0.00832  -0.0986   0.5522   1.0000
   5.000   0.9735   0.01699   0.00846  -0.0965   0.5269   1.0000
   5.250   0.9930   0.01711   0.00870  -0.0947   0.5021   1.0000
   5.500   1.0087   0.01723   0.00886  -0.0922   0.4589   1.0000
   5.750   1.0113   0.01814   0.00902  -0.0875   0.3184   1.0000
   6.000   0.9940   0.02159   0.01099  -0.0814   0.0919   1.0000
   6.250   1.0019   0.02308   0.01236  -0.0785   0.0618   1.0000
   6.500   1.0125   0.02427   0.01364  -0.0759   0.0503   1.0000
   6.750   1.0211   0.02549   0.01499  -0.0730   0.0423   1.0000
   7.000   1.0258   0.02675   0.01637  -0.0697   0.0383   1.0000
   7.250   1.0257   0.02825   0.01797  -0.0658   0.0356   1.0000
   7.500   1.0308   0.02952   0.01945  -0.0628   0.0322   1.0000
   7.750   1.0347   0.03096   0.02097  -0.0600   0.0297   1.0000
   8.000   1.0375   0.03265   0.02269  -0.0572   0.0280   1.0000
   8.250   1.0439   0.03466   0.02463  -0.0547   0.0266   1.0000
   8.500   1.0622   0.03603   0.02614  -0.0532   0.0249   1.0000
   8.750   1.0848   0.03758   0.02783  -0.0522   0.0224   1.0000
   9.000   1.1188   0.03971   0.03011  -0.0522   0.0209   1.0000
   9.250   1.1562   0.04244   0.03304  -0.0531   0.0198   1.0000
   9.500   1.1774   0.04485   0.03573  -0.0525   0.0186   1.0000
   9.750   1.1915   0.04738   0.03842  -0.0514   0.0174   1.0000
  10.000   1.2093   0.05228   0.04362  -0.0512   0.0164   1.0000
  10.250   1.2153   0.05517   0.04685  -0.0488   0.0162   1.0000
  10.500   1.2171   0.05822   0.05023  -0.0463   0.0161   1.0000
  10.750   1.2144   0.06137   0.05370  -0.0436   0.0160   1.0000
  11.000   1.2087   0.06462   0.05724  -0.0411   0.0160   1.0000
  11.250   1.2000   0.06806   0.06096  -0.0388   0.0160   1.0000
  11.500   1.1891   0.07168   0.06483  -0.0370   0.0160   1.0000
  11.750   1.1763   0.07555   0.06896  -0.0357   0.0160   1.0000
  12.000   1.1622   0.07970   0.07333  -0.0349   0.0160   1.0000
  12.250   1.1467   0.08415   0.07800  -0.0347   0.0161   1.0000
  12.500   1.1306   0.08896   0.08302  -0.0351   0.0161   1.0000
  12.750   1.1135   0.09412   0.08837  -0.0361   0.0162   1.0000
  13.000   1.0965   0.09966   0.09408  -0.0378   0.0163   1.0000
  13.250   1.0798   0.10558   0.10015  -0.0400   0.0164   1.0000
  13.750   0.8923   0.11062   0.10611  -0.0393   0.0171   1.0000
  14.000   0.8672   0.11789   0.11359  -0.0440   0.0174   1.0000
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