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GOE 134 (MVA H.12) AIRFOIL (goe134-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 134 (MVA H.12) AIRFOIL (goe134-il)
Reynolds number: 50,000
Max Cl/Cd: 29.37 at α=11°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe134-il-50000.txt
Download as CSV file: xf-goe134-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 134 (MVA H.12) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4017   0.10647   0.09980  -0.0182   1.0000   0.1833
  -7.750  -0.3864   0.10173   0.09508  -0.0168   1.0000   0.1923
  -7.500  -0.4032   0.10074   0.09425  -0.0185   1.0000   0.1989
  -7.250  -0.3898   0.09645   0.08999  -0.0165   1.0000   0.2110
  -7.000  -0.3880   0.09332   0.08694  -0.0160   1.0000   0.2220
  -6.750  -0.4069   0.09254   0.08630  -0.0211   1.0000   0.2307
  -6.500  -0.4044   0.08952   0.08335  -0.0203   1.0000   0.2461
  -6.250  -0.3884   0.08494   0.07883  -0.0149   1.0000   0.2653
  -6.000  -0.3835   0.08203   0.07599  -0.0127   1.0000   0.2845
  -5.750  -0.3878   0.07992   0.07397  -0.0126   1.0000   0.3063
  -5.500  -0.3804   0.07662   0.07076  -0.0087   1.0000   0.3292
  -5.250  -0.3800   0.07412   0.06835  -0.0059   1.0000   0.3580
  -5.000  -0.3753   0.07158   0.06590  -0.0011   1.0000   0.3931
  -4.750   0.0163   0.04769   0.04085  -0.0245   1.0000   1.0000
  -4.500   0.0274   0.04561   0.03881  -0.0255   1.0000   1.0000
  -4.250   0.0382   0.04362   0.03687  -0.0264   1.0000   1.0000
  -4.000   0.0488   0.04170   0.03503  -0.0272   1.0000   1.0000
  -3.750  -0.0102   0.04388   0.03746  -0.0120   1.0000   0.9618
  -3.500  -0.0706   0.04550   0.03937   0.0016   1.0000   0.9133
  -3.250  -0.1258   0.04627   0.04044   0.0125   1.0000   0.8683
  -3.000  -0.1787   0.04658   0.04104   0.0224   1.0000   0.8359
  -2.750  -0.2314   0.04673   0.04147   0.0326   1.0000   0.8182
  -2.500  -0.2818   0.04654   0.04153   0.0423   1.0000   0.8042
  -2.250  -0.1370   0.03778   0.02960  -0.0425   1.0000   0.2288
  -2.000  -0.1049   0.03595   0.02718  -0.0438   1.0000   0.1967
  -1.750  -0.0763   0.03452   0.02530  -0.0444   1.0000   0.1786
  -1.500  -0.0492   0.03361   0.02391  -0.0447   1.0000   0.1660
  -1.250  -0.0246   0.03270   0.02271  -0.0449   1.0000   0.1586
  -1.000  -0.0012   0.03233   0.02196  -0.0449   1.0000   0.1553
  -0.750   0.0204   0.03208   0.02148  -0.0448   1.0000   0.1546
  -0.500   0.0596   0.03167   0.02083  -0.0477   0.9946   0.1529
  -0.250   0.1182   0.03098   0.01992  -0.0533   0.9808   0.1519
   0.000   0.1748   0.03057   0.01928  -0.0585   0.9656   0.1535
   0.250   0.2291   0.03002   0.01876  -0.0637   0.9496   0.1631
   0.500   0.2826   0.02959   0.01833  -0.0688   0.9326   0.1806
   0.750   0.3369   0.02867   0.01797  -0.0740   0.9162   0.2559
   1.000   0.3805   0.02689   0.01764  -0.0754   0.8994   1.0000
   1.250   0.4347   0.02692   0.01720  -0.0796   0.8823   1.0000
   1.500   0.4742   0.02710   0.01712  -0.0816   0.8621   1.0000
   1.750   0.5173   0.02706   0.01689  -0.0837   0.8434   1.0000
   2.000   0.5607   0.02689   0.01657  -0.0856   0.8259   1.0000
   2.250   0.6022   0.02665   0.01622  -0.0869   0.8087   1.0000
   2.500   0.6328   0.02681   0.01630  -0.0867   0.7888   1.0000
   2.750   0.6651   0.02688   0.01630  -0.0866   0.7699   1.0000
   3.000   0.6976   0.02692   0.01626  -0.0863   0.7519   1.0000
   3.250   0.7290   0.02702   0.01631  -0.0857   0.7344   1.0000
   3.500   0.7558   0.02745   0.01669  -0.0849   0.7160   1.0000
   3.750   0.7797   0.02812   0.01735  -0.0839   0.6966   1.0000
   4.000   0.8050   0.02873   0.01797  -0.0830   0.6789   1.0000
   4.250   0.8302   0.02938   0.01861  -0.0821   0.6621   1.0000
   4.500   0.8550   0.03008   0.01933  -0.0812   0.6459   1.0000
   4.750   0.8790   0.03088   0.02015  -0.0804   0.6304   1.0000
   5.000   0.9024   0.03176   0.02110  -0.0796   0.6155   1.0000
   5.250   0.9250   0.03275   0.02217  -0.0789   0.6011   1.0000
   5.500   0.9471   0.03383   0.02333  -0.0781   0.5873   1.0000
   5.750   0.9688   0.03496   0.02456  -0.0773   0.5741   1.0000
   6.000   0.9914   0.03605   0.02578  -0.0766   0.5618   1.0000
   6.250   1.0178   0.03674   0.02653  -0.0759   0.5504   1.0000
   6.500   1.0391   0.03791   0.02783  -0.0750   0.5377   1.0000
   6.750   1.0566   0.03941   0.02950  -0.0740   0.5242   1.0000
   7.000   1.0762   0.04054   0.03080  -0.0727   0.5101   1.0000
   7.250   1.0971   0.04143   0.03183  -0.0714   0.4955   1.0000
   7.500   1.1184   0.04226   0.03279  -0.0700   0.4807   1.0000
   7.750   1.1389   0.04318   0.03387  -0.0686   0.4660   1.0000
   8.000   1.1601   0.04400   0.03487  -0.0672   0.4509   1.0000
   8.250   1.1833   0.04454   0.03554  -0.0657   0.4351   1.0000
   8.500   1.2144   0.04414   0.03519  -0.0644   0.4176   1.0000
   8.750   1.2306   0.04519   0.03646  -0.0624   0.3993   1.0000
   9.000   1.2457   0.04624   0.03772  -0.0603   0.3798   1.0000
   9.250   1.2786   0.04558   0.03704  -0.0590   0.3587   1.0000
   9.500   1.2918   0.04699   0.03864  -0.0568   0.3391   1.0000
   9.750   1.3066   0.04816   0.03998  -0.0546   0.3188   1.0000
  10.000   1.3367   0.04813   0.03991  -0.0533   0.2975   1.0000
  10.250   1.3406   0.04998   0.04204  -0.0504   0.2785   1.0000
  10.500   1.3627   0.04834   0.04026  -0.0480   0.2499   1.0000
  10.750   1.3736   0.04709   0.03885  -0.0448   0.2220   1.0000
  11.000   1.3787   0.04695   0.03855  -0.0414   0.1965   1.0000
  11.250   1.3706   0.04870   0.04044  -0.0372   0.1758   1.0000
  11.500   1.3642   0.05041   0.04195  -0.0332   0.1540   1.0000
  11.750   1.3538   0.05320   0.04473  -0.0292   0.1379   1.0000
  12.000   1.3486   0.05635   0.04785  -0.0262   0.1244   1.0000
  12.250   1.3479   0.05966   0.05113  -0.0240   0.1138   1.0000
  12.500   1.3576   0.06298   0.05432  -0.0226   0.1037   1.0000
  12.750   1.3398   0.06719   0.05898  -0.0204   0.1019   1.0000
  13.000   1.3217   0.07192   0.06407  -0.0192   0.1003   1.0000
  13.250   1.3011   0.07721   0.06969  -0.0190   0.0995   1.0000
  13.500   1.2762   0.08335   0.07612  -0.0200   0.0995   1.0000
  13.750   1.2470   0.09060   0.08363  -0.0224   0.1003   1.0000
  14.000   1.2156   0.09897   0.09220  -0.0262   0.1017   1.0000
  14.250   1.1853   0.10816   0.10153  -0.0307   0.1031   1.0000
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