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GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il)
Reynolds number: 100,000
Max Cl/Cd: 48.61 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe147-il-100000.txt
Download as CSV file: xf-goe147-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 147 (MVA H.6) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4684   0.10687   0.10222   0.0139   1.0000   0.0870
  -8.000  -0.4671   0.10436   0.09977   0.0106   1.0000   0.0899
  -7.750  -0.4727   0.10327   0.09878   0.0012   1.0000   0.0912
  -7.500  -0.4651   0.09900   0.09456  -0.0056   1.0000   0.0919
  -7.250  -0.4523   0.09329   0.08887   0.0028   1.0000   0.0936
  -7.000  -0.4403   0.08967   0.08526   0.0036   1.0000   0.0967
  -6.750  -0.4296   0.08615   0.08177   0.0004   1.0000   0.1002
  -6.500  -0.4097   0.08304   0.07857  -0.0168   1.0000   0.1047
  -6.250  -0.3956   0.07772   0.07326  -0.0198   1.0000   0.1055
  -6.000  -0.3841   0.07319   0.06878  -0.0178   1.0000   0.1065
  -5.750  -0.3691   0.06924   0.06483  -0.0182   1.0000   0.1079
  -5.500  -0.3511   0.06534   0.06091  -0.0203   1.0000   0.1097
  -5.250  -0.3299   0.06129   0.05681  -0.0238   1.0000   0.1120
  -5.000  -0.2880   0.04876   0.04370  -0.0387   1.0000   0.0802
  -4.750  -0.2636   0.04423   0.03902  -0.0405   1.0000   0.0773
  -4.500  -0.2362   0.03885   0.03337  -0.0434   1.0000   0.0753
  -4.250  -0.2036   0.03075   0.02456  -0.0474   1.0000   0.0722
  -4.000  -0.1732   0.02575   0.01885  -0.0489   1.0000   0.0754
  -3.750  -0.1460   0.02410   0.01695  -0.0490   1.0000   0.0839
  -3.500  -0.1177   0.02185   0.01422  -0.0490   1.0000   0.0948
  -3.250  -0.0920   0.02123   0.01352  -0.0485   1.0000   0.1156
  -3.000  -0.0675   0.02070   0.01292  -0.0479   1.0000   0.1489
  -2.750  -0.0457   0.02094   0.01328  -0.0470   1.0000   0.1720
  -2.500  -0.0240   0.02084   0.01304  -0.0463   1.0000   0.1904
  -2.250  -0.0077   0.02079   0.01319  -0.0452   1.0000   0.2078
  -2.000   0.0157   0.02064   0.01281  -0.0456   0.9973   0.2179
  -1.750   0.0735   0.01938   0.01145  -0.0518   0.9796   0.2232
  -1.500   0.1292   0.01838   0.01022  -0.0571   0.9594   0.2248
  -1.250   0.1781   0.01761   0.00927  -0.0608   0.9333   0.2275
  -1.000   0.2191   0.01711   0.00853  -0.0626   0.9033   0.2318
  -0.750   0.2505   0.01661   0.00794  -0.0624   0.8718   0.2346
  -0.500   0.2769   0.01629   0.00752  -0.0611   0.8412   0.2376
  -0.250   0.3021   0.01606   0.00717  -0.0597   0.8124   0.2415
   0.000   0.3273   0.01591   0.00686  -0.0583   0.7854   0.2462
   0.250   0.3520   0.01564   0.00658  -0.0570   0.7600   0.2521
   0.500   0.3768   0.01550   0.00633  -0.0556   0.7353   0.2607
   0.750   0.4015   0.01530   0.00615  -0.0544   0.7098   0.2739
   1.000   0.4268   0.01510   0.00595  -0.0532   0.6847   0.2945
   1.250   0.4523   0.01474   0.00573  -0.0523   0.6602   0.3489
   1.500   0.4758   0.01323   0.00545  -0.0502   0.6339   1.0000
   1.750   0.5018   0.01353   0.00546  -0.0493   0.6058   1.0000
   2.000   0.5277   0.01386   0.00554  -0.0484   0.5770   1.0000
   2.250   0.5537   0.01421   0.00565  -0.0477   0.5480   1.0000
   2.500   0.5797   0.01455   0.00577  -0.0470   0.5196   1.0000
   2.750   0.6058   0.01486   0.00590  -0.0463   0.4924   1.0000
   3.000   0.6319   0.01516   0.00600  -0.0457   0.4684   1.0000
   3.250   0.6586   0.01547   0.00621  -0.0453   0.4450   1.0000
   3.500   0.6852   0.01582   0.00642  -0.0449   0.4263   1.0000
   3.750   0.7118   0.01622   0.00672  -0.0446   0.4093   1.0000
   4.000   0.7386   0.01665   0.00708  -0.0442   0.3929   1.0000
   4.250   0.7652   0.01712   0.00748  -0.0439   0.3777   1.0000
   4.500   0.7917   0.01764   0.00793  -0.0436   0.3633   1.0000
   4.750   0.8181   0.01823   0.00847  -0.0433   0.3495   1.0000
   5.000   0.8444   0.01886   0.00904  -0.0430   0.3359   1.0000
   5.250   0.8705   0.01955   0.00966  -0.0427   0.3227   1.0000
   5.500   0.8967   0.02025   0.01038  -0.0424   0.3097   1.0000
   5.750   0.9227   0.02099   0.01120  -0.0421   0.2972   1.0000
   6.000   0.9487   0.02185   0.01214  -0.0418   0.2866   1.0000
   6.250   0.9750   0.02277   0.01301  -0.0415   0.2786   1.0000
   6.500   1.0007   0.02368   0.01418  -0.0413   0.2703   1.0000
   6.750   1.0271   0.02472   0.01516  -0.0411   0.2650   1.0000
   7.000   1.0522   0.02583   0.01665  -0.0408   0.2592   1.0000
   7.250   1.0778   0.02693   0.01794  -0.0405   0.2548   1.0000
   7.500   1.1038   0.02801   0.01901  -0.0403   0.2507   1.0000
   7.750   1.1270   0.02816   0.01944  -0.0397   0.2394   1.0000
   8.000   1.1504   0.02764   0.01889  -0.0391   0.2245   1.0000
   8.250   1.1734   0.02769   0.01915  -0.0385   0.2132   1.0000
   8.500   1.1960   0.02730   0.01892  -0.0378   0.1997   1.0000
   8.750   1.2180   0.02649   0.01834  -0.0369   0.1825   1.0000
   9.000   1.2400   0.02551   0.01764  -0.0363   0.1419   1.0000
   9.250   1.2572   0.02711   0.01892  -0.0354   0.0756   1.0000
   9.500   1.2686   0.02960   0.02118  -0.0341   0.0608   1.0000
   9.750   1.2773   0.03211   0.02375  -0.0326   0.0552   1.0000
  10.000   1.2864   0.03433   0.02619  -0.0311   0.0511   1.0000
  10.250   1.2907   0.03683   0.02881  -0.0294   0.0481   1.0000
  10.500   1.2923   0.03951   0.03153  -0.0273   0.0463   1.0000
  10.750   1.2984   0.04194   0.03406  -0.0254   0.0451   1.0000
  11.000   1.3054   0.04416   0.03645  -0.0234   0.0443   1.0000
  11.250   1.3127   0.04659   0.03906  -0.0217   0.0435   1.0000
  11.500   1.3183   0.04927   0.04193  -0.0201   0.0427   1.0000
  11.750   1.3207   0.05220   0.04508  -0.0189   0.0417   1.0000
  12.000   1.3205   0.05539   0.04847  -0.0182   0.0407   1.0000
  12.250   1.3183   0.05888   0.05217  -0.0179   0.0398   1.0000
  12.500   1.3130   0.06281   0.05631  -0.0182   0.0393   1.0000
  12.750   1.3051   0.06722   0.06096  -0.0191   0.0391   1.0000
  13.000   1.2940   0.07223   0.06624  -0.0209   0.0391   1.0000
  13.250   1.2789   0.07800   0.07226  -0.0236   0.0393   1.0000
  13.500   1.2596   0.08470   0.07923  -0.0275   0.0396   1.0000
  13.750   1.2371   0.09231   0.08709  -0.0323   0.0400   1.0000
  14.000   1.2112   0.10106   0.09607  -0.0382   0.0406   1.0000
  14.250   1.1809   0.11138   0.10660  -0.0454   0.0415   1.0000
  14.500   1.1474   0.12333   0.11872  -0.0533   0.0430   1.0000
  14.750   1.1171   0.13548   0.13096  -0.0608   0.0445   1.0000
  15.000   1.0951   0.14614   0.14165  -0.0666   0.0455   1.0000
  15.250   1.0236   0.17915   0.17451  -0.0860   0.0551   1.0000
  15.500   1.0288   0.18398   0.17937  -0.0873   0.0565   1.0000
  15.750   1.0226   0.19650   0.19181  -0.0924   0.0664   1.0000
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