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GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il)
Reynolds number: 100,000
Max Cl/Cd: 57.1 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe115-il-100000.txt
Download as CSV file: xf-goe115-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 115 (MVA MK.2) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3996   0.09885   0.09431  -0.0394   1.0000   0.1340
  -8.250  -0.3558   0.09299   0.08829  -0.0343   1.0000   0.1431
  -8.000  -0.3809   0.09207   0.08759  -0.0364   1.0000   0.1473
  -7.750  -0.3577   0.08775   0.08322  -0.0336   1.0000   0.1547
  -7.500  -0.3775   0.08664   0.08228  -0.0334   1.0000   0.1607
  -7.250  -0.4115   0.08583   0.08170  -0.0365   1.0000   0.1622
  -7.000  -0.3811   0.08162   0.07743  -0.0294   1.0000   0.1686
  -6.750  -0.4000   0.08046   0.07642  -0.0282   1.0000   0.1741
  -6.500  -0.4313   0.07911   0.07522  -0.0293   1.0000   0.1775
  -6.250  -0.4260   0.07696   0.07312  -0.0233   1.0000   0.1805
  -6.000  -0.4352   0.07554   0.07177  -0.0208   1.0000   0.1854
  -5.750  -0.4285   0.07187   0.06800  -0.0353   0.9942   0.2041
  -5.500  -0.3905   0.03994   0.03447  -0.0661   0.9856   0.0961
  -5.250  -0.3501   0.03320   0.02669  -0.0704   0.9785   0.0786
  -5.000  -0.3089   0.02918   0.02194  -0.0739   0.9716   0.0749
  -4.750  -0.2697   0.02677   0.01896  -0.0765   0.9630   0.0763
  -4.500  -0.2254   0.02454   0.01625  -0.0794   0.9567   0.0757
  -4.250  -0.1875   0.02302   0.01448  -0.0811   0.9473   0.0777
  -4.000  -0.1414   0.02169   0.01294  -0.0844   0.9416   0.0819
  -3.750  -0.1070   0.02047   0.01177  -0.0857   0.9314   0.0850
  -3.500  -0.0658   0.01960   0.01081  -0.0882   0.9240   0.0913
  -3.250  -0.0258   0.01876   0.00996  -0.0907   0.9161   0.1046
  -3.000   0.0108   0.01773   0.00935  -0.0925   0.9077   0.1742
  -2.750   0.0522   0.01795   0.00970  -0.0947   0.9002   0.3081
  -2.500   0.0837   0.01824   0.00982  -0.0952   0.8898   0.3461
  -2.250   0.1226   0.01818   0.00975  -0.0970   0.8841   0.3821
  -2.000   0.1495   0.01818   0.00966  -0.0969   0.8732   0.3999
  -1.750   0.1794   0.01811   0.00954  -0.0972   0.8647   0.4197
  -1.500   0.2120   0.01792   0.00928  -0.0980   0.8573   0.4343
  -1.250   0.2388   0.01789   0.00922  -0.0978   0.8481   0.4484
  -1.000   0.2699   0.01771   0.00912  -0.0982   0.8418   0.4789
  -0.750   0.2928   0.01778   0.00931  -0.0974   0.8326   0.5079
  -0.500   0.3238   0.01760   0.00916  -0.0978   0.8272   0.5305
  -0.250   0.3474   0.01771   0.00933  -0.0973   0.8184   0.5502
   0.000   0.3792   0.01751   0.00921  -0.0978   0.8130   0.5766
   0.250   0.4031   0.01754   0.00946  -0.0974   0.8050   0.6129
   0.750   0.4867   0.01678   0.00941  -0.1027   0.7947   1.0000
   1.000   0.5117   0.01718   0.00968  -0.1025   0.7876   1.0000
   1.250   0.5414   0.01738   0.00977  -0.1027   0.7832   1.0000
   1.500   0.5617   0.01800   0.01036  -0.1019   0.7751   1.0000
   1.750   0.5908   0.01813   0.01042  -0.1018   0.7696   1.0000
   2.000   0.6124   0.01857   0.01085  -0.1009   0.7604   1.0000
   2.250   0.6424   0.01852   0.01076  -0.1005   0.7537   1.0000
   2.500   0.6642   0.01893   0.01119  -0.0996   0.7442   1.0000
   2.750   0.6918   0.01913   0.01140  -0.0993   0.7387   1.0000
   3.000   0.7135   0.01968   0.01201  -0.0985   0.7307   1.0000
   3.250   0.7431   0.01979   0.01217  -0.0984   0.7258   1.0000
   3.500   0.7624   0.02048   0.01297  -0.0974   0.7170   1.0000
   3.750   0.7921   0.02057   0.01312  -0.0972   0.7119   1.0000
   4.000   0.8115   0.02127   0.01394  -0.0962   0.7028   1.0000
   4.250   0.8420   0.02130   0.01408  -0.0960   0.6974   1.0000
   4.500   0.8621   0.02187   0.01482  -0.0949   0.6871   1.0000
   4.750   0.8950   0.02072   0.01369  -0.0932   0.6699   1.0000
   5.000   0.9240   0.01925   0.01215  -0.0904   0.6413   1.0000
   5.250   0.9483   0.01821   0.01110  -0.0875   0.6085   1.0000
   5.500   0.9669   0.01726   0.01014  -0.0837   0.5605   1.0000
   5.750   0.9667   0.01693   0.00905  -0.0765   0.3746   1.0000
   6.000   0.9467   0.02062   0.01075  -0.0698   0.1106   1.0000
   6.500   0.9623   0.02394   0.01390  -0.0635   0.0729   1.0000
   6.750   0.9687   0.02549   0.01551  -0.0603   0.0673   1.0000
   7.000   0.9780   0.02684   0.01696  -0.0575   0.0620   1.0000
   7.250   0.9878   0.02841   0.01849  -0.0548   0.0593   1.0000
   7.500   1.0173   0.03121   0.02100  -0.0547   0.0565   1.0000
   7.750   1.0479   0.03288   0.02281  -0.0545   0.0546   1.0000
   8.000   1.0778   0.03477   0.02486  -0.0542   0.0517   1.0000
   8.250   1.1132   0.03749   0.02780  -0.0546   0.0515   1.0000
   8.500   1.1441   0.04066   0.03126  -0.0543   0.0528   1.0000
   8.750   1.1725   0.04476   0.03563  -0.0540   0.0550   1.0000
   9.000   1.2004   0.04766   0.03880  -0.0531   0.0582   1.0000
   9.250   1.2085   0.05067   0.04268  -0.0491   0.0641   1.0000
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