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GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il)
Reynolds number: 50,000
Max Cl/Cd: 39.83 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe137-il-50000-n5.txt
Download as CSV file: xf-goe137-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 137 (MVA H.15) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3418   0.10836   0.10175  -0.0230   1.0000   0.0997
  -8.250  -0.3500   0.10743   0.10096  -0.0262   1.0000   0.1018
  -8.000  -0.3571   0.10618   0.09986  -0.0302   1.0000   0.1024
  -7.750  -0.3351   0.09938   0.09304  -0.0257   1.0000   0.1058
  -7.500  -0.3305   0.09636   0.09008  -0.0256   1.0000   0.1087
  -7.250  -0.3292   0.09372   0.08754  -0.0265   1.0000   0.1118
  -7.000  -0.3323   0.09179   0.08573  -0.0299   1.0000   0.1157
  -6.750  -0.3360   0.09023   0.08425  -0.0357   1.0000   0.1172
  -6.500  -0.3318   0.08631   0.08044  -0.0349   1.0000   0.1181
  -6.250  -0.3255   0.08266   0.07686  -0.0305   1.0000   0.1216
  -6.000  -0.3232   0.08013   0.07439  -0.0302   1.0000   0.1261
  -5.750  -0.3219   0.07846   0.07268  -0.0367   1.0000   0.1320
  -5.500  -0.3189   0.07505   0.06935  -0.0358   1.0000   0.1332
  -5.250  -0.2990   0.06665   0.06065  -0.0419   1.0000   0.0743
  -5.000  -0.2887   0.06343   0.05744  -0.0416   0.9981   0.0715
  -4.750  -0.2486   0.05763   0.05135  -0.0495   0.9887   0.0680
  -4.500  -0.2068   0.05253   0.04591  -0.0570   0.9792   0.0703
  -4.250  -0.1649   0.04748   0.04043  -0.0634   0.9699   0.0697
  -4.000  -0.1223   0.04281   0.03525  -0.0691   0.9610   0.0694
  -3.750  -0.0777   0.03870   0.03040  -0.0743   0.9524   0.0736
  -3.500  -0.0378   0.03531   0.02636  -0.0778   0.9425   0.0742
  -3.250   0.0052   0.03237   0.02271  -0.0812   0.9346   0.0750
  -3.000   0.0428   0.03068   0.02086  -0.0837   0.9247   0.0789
  -2.750   0.0796   0.02922   0.01902  -0.0856   0.9137   0.0844
  -2.500   0.1180   0.02755   0.01685  -0.0874   0.9039   0.0862
  -2.250   0.1562   0.02617   0.01504  -0.0889   0.8941   0.0883
  -2.000   0.1886   0.02521   0.01397  -0.0894   0.8820   0.0914
  -1.750   0.2221   0.02442   0.01296  -0.0900   0.8701   0.0961
  -1.500   0.2554   0.02371   0.01200  -0.0905   0.8585   0.1029
  -1.250   0.2875   0.02316   0.01139  -0.0910   0.8469   0.1183
  -1.000   0.3197   0.02252   0.01073  -0.0914   0.8358   0.1466
  -0.750   0.3491   0.02170   0.01018  -0.0915   0.8234   0.2091
  -0.500   0.3772   0.01914   0.00985  -0.0910   0.8115   1.0000
  -0.250   0.4059   0.01926   0.00951  -0.0907   0.7987   1.0000
   0.000   0.4341   0.01939   0.00929  -0.0903   0.7863   1.0000
   0.250   0.4623   0.01951   0.00913  -0.0899   0.7743   1.0000
   0.500   0.4908   0.01963   0.00898  -0.0896   0.7629   1.0000
   0.750   0.5172   0.01984   0.00898  -0.0890   0.7501   1.0000
   1.000   0.5437   0.02007   0.00904  -0.0886   0.7376   1.0000
   1.250   0.5705   0.02030   0.00912  -0.0881   0.7254   1.0000
   1.500   0.5974   0.02054   0.00921  -0.0877   0.7139   1.0000
   1.750   0.6250   0.02075   0.00927  -0.0873   0.7030   1.0000
   2.000   0.6509   0.02106   0.00951  -0.0868   0.6909   1.0000
   2.250   0.6767   0.02140   0.00978  -0.0863   0.6787   1.0000
   2.500   0.7027   0.02173   0.01005  -0.0859   0.6671   1.0000
   2.750   0.7293   0.02204   0.01032  -0.0854   0.6564   1.0000
   3.000   0.7556   0.02236   0.01060  -0.0850   0.6454   1.0000
   3.250   0.7805   0.02278   0.01103  -0.0845   0.6333   1.0000
   3.500   0.8057   0.02317   0.01145  -0.0840   0.6213   1.0000
   3.750   0.8310   0.02352   0.01181  -0.0834   0.6094   1.0000
   4.000   0.8566   0.02383   0.01212  -0.0827   0.5975   1.0000
   4.250   0.8821   0.02411   0.01243  -0.0820   0.5852   1.0000
   4.500   0.9061   0.02446   0.01283  -0.0812   0.5714   1.0000
   4.750   0.9300   0.02479   0.01322  -0.0804   0.5572   1.0000
   5.000   0.9538   0.02509   0.01358  -0.0795   0.5428   1.0000
   5.250   0.9773   0.02540   0.01400  -0.0785   0.5283   1.0000
   5.500   1.0007   0.02575   0.01443  -0.0777   0.5140   1.0000
   5.750   1.0240   0.02617   0.01497  -0.0768   0.5006   1.0000
   6.000   1.0472   0.02665   0.01563  -0.0761   0.4881   1.0000
   6.250   1.0706   0.02713   0.01625  -0.0753   0.4759   1.0000
   6.500   1.0939   0.02761   0.01687  -0.0744   0.4634   1.0000
   6.750   1.1167   0.02809   0.01749  -0.0735   0.4502   1.0000
   7.000   1.1391   0.02860   0.01819  -0.0726   0.4363   1.0000
   7.250   1.1609   0.02916   0.01892  -0.0715   0.4219   1.0000
   7.500   1.1823   0.02977   0.01972  -0.0705   0.4074   1.0000
   7.750   1.2034   0.03046   0.02059  -0.0694   0.3931   1.0000
   8.000   1.2222   0.03119   0.02152  -0.0680   0.3761   1.0000
   8.250   1.2378   0.03171   0.02214  -0.0661   0.3535   1.0000
   8.500   1.2503   0.03240   0.02300  -0.0640   0.3294   1.0000
   8.750   1.2605   0.03316   0.02379  -0.0617   0.3037   1.0000
   9.000   1.2671   0.03416   0.02484  -0.0592   0.2754   1.0000
   9.250   1.2748   0.03534   0.02614  -0.0571   0.2525   1.0000
   9.500   1.2801   0.03671   0.02761  -0.0548   0.2295   1.0000
   9.750   1.2764   0.03852   0.02930  -0.0518   0.2013   1.0000
  10.000   1.2688   0.04100   0.03158  -0.0494   0.1734   1.0000
  10.250   1.2607   0.04402   0.03452  -0.0477   0.1420   1.0000
  10.500   1.2550   0.04722   0.03772  -0.0467   0.0961   1.0000
  10.750   1.2414   0.05148   0.04171  -0.0463   0.0784   1.0000
  11.000   1.2307   0.05578   0.04598  -0.0461   0.0656   1.0000
  11.250   1.2213   0.06014   0.05041  -0.0462   0.0573   1.0000
  11.500   1.2115   0.06468   0.05502  -0.0465   0.0519   1.0000
  11.750   1.2027   0.06923   0.05964  -0.0470   0.0482   1.0000
  12.000   1.1949   0.07371   0.06434  -0.0477   0.0450   1.0000
  12.250   1.1864   0.07840   0.06914  -0.0485   0.0426   1.0000
  12.500   1.1770   0.08328   0.07410  -0.0495   0.0409   1.0000
  12.750   1.1708   0.08776   0.07871  -0.0503   0.0391   1.0000
  13.000   1.1653   0.09218   0.08328  -0.0512   0.0376   1.0000
  13.250   1.1604   0.09656   0.08781  -0.0520   0.0363   1.0000
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