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GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il)
Reynolds number: 1,000,000
Max Cl/Cd: 127.66 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe184-il-1000000.txt
Download as CSV file: xf-goe184-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 184 (MVA H.29) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3372   0.09182   0.09027  -0.0241   1.0000   0.0168
  -8.250  -0.3332   0.08816   0.08663  -0.0261   1.0000   0.0168
  -8.000  -0.3320   0.08464   0.08315  -0.0276   1.0000   0.0168
  -7.750  -0.3426   0.02324   0.02057  -0.0972   0.9713   0.0172
  -7.500  -0.3161   0.02203   0.01928  -0.0979   0.9607   0.0176
  -7.250  -0.2896   0.02202   0.01928  -0.0977   0.9494   0.0181
  -7.000  -0.2641   0.02200   0.01925  -0.0972   0.9367   0.0186
  -6.750  -0.2396   0.02010   0.01709  -0.0977   0.9216   0.0193
  -6.500  -0.2149   0.01814   0.01476  -0.0979   0.9031   0.0201
  -6.250  -0.1893   0.01720   0.01351  -0.0977   0.8816   0.0207
  -6.000  -0.1623   0.01729   0.01339  -0.0973   0.8599   0.0211
  -5.750  -0.1384   0.01421   0.00989  -0.0979   0.8401   0.0223
  -5.500  -0.1116   0.01376   0.00932  -0.0977   0.8211   0.0230
  -5.250  -0.0845   0.01323   0.00863  -0.0976   0.8039   0.0237
  -5.000  -0.0570   0.01265   0.00785  -0.0975   0.7886   0.0244
  -4.750  -0.0292   0.01213   0.00715  -0.0975   0.7748   0.0251
  -4.500  -0.0011   0.01176   0.00664  -0.0974   0.7619   0.0257
  -4.250   0.0271   0.01176   0.00651  -0.0972   0.7492   0.0262
  -4.000   0.0549   0.01074   0.00527  -0.0973   0.7378   0.0268
  -3.750   0.0828   0.00991   0.00431  -0.0973   0.7272   0.0275
  -3.500   0.1111   0.00944   0.00376  -0.0973   0.7173   0.0282
  -3.250   0.1394   0.00911   0.00337  -0.0973   0.7073   0.0290
  -3.000   0.1677   0.00885   0.00303  -0.0973   0.6963   0.0299
  -2.750   0.1962   0.00861   0.00272  -0.0972   0.6846   0.0304
  -2.500   0.2247   0.00841   0.00243  -0.0972   0.6715   0.0308
  -2.250   0.2531   0.00825   0.00219  -0.0972   0.6555   0.0313
  -2.000   0.2813   0.00813   0.00198  -0.0971   0.6353   0.0318
  -1.750   0.3095   0.00805   0.00179  -0.0970   0.6106   0.0323
  -1.500   0.3375   0.00804   0.00165  -0.0969   0.5847   0.0329
  -1.250   0.3655   0.00802   0.00149  -0.0968   0.5620   0.0344
  -1.000   0.3936   0.00802   0.00140  -0.0967   0.5454   0.0360
  -0.750   0.4219   0.00800   0.00133  -0.0967   0.5337   0.0381
  -0.500   0.4502   0.00797   0.00129  -0.0967   0.5244   0.0460
  -0.250   0.4786   0.00800   0.00137  -0.0967   0.5161   0.0666
   0.000   0.5069   0.00806   0.00142  -0.0966   0.5088   0.0711
   0.250   0.5352   0.00811   0.00148  -0.0966   0.5014   0.0765
   0.500   0.5633   0.00820   0.00154  -0.0966   0.4937   0.0795
   0.750   0.5915   0.00824   0.00155  -0.0966   0.4840   0.0814
   1.000   0.6198   0.00822   0.00152  -0.0966   0.4746   0.0846
   1.250   0.6479   0.00825   0.00153  -0.0966   0.4647   0.0866
   1.500   0.6762   0.00827   0.00153  -0.0966   0.4549   0.0883
   1.750   0.7044   0.00831   0.00155  -0.0966   0.4453   0.0897
   2.000   0.7324   0.00837   0.00158  -0.0966   0.4341   0.0916
   2.250   0.7602   0.00845   0.00162  -0.0966   0.4208   0.0934
   2.500   0.7881   0.00852   0.00166  -0.0965   0.4063   0.0962
   2.750   0.8158   0.00862   0.00172  -0.0965   0.3917   0.0993
   3.000   0.8434   0.00873   0.00180  -0.0964   0.3780   0.1051
   3.250   0.8711   0.00875   0.00193  -0.0965   0.3650   0.1711
   3.500   0.8982   0.00774   0.00225  -0.0970   0.3554   0.7962
   4.000   0.9484   0.00765   0.00246  -0.0956   0.3396   1.0000
   4.250   0.9757   0.00783   0.00259  -0.0955   0.3321   1.0000
   4.500   1.0032   0.00799   0.00272  -0.0954   0.3229   1.0000
   4.750   1.0303   0.00818   0.00287  -0.0953   0.3139   1.0000
   5.000   1.0577   0.00834   0.00301  -0.0952   0.3068   1.0000
   5.250   1.0848   0.00852   0.00317  -0.0951   0.2987   1.0000
   5.500   1.1118   0.00872   0.00333  -0.0950   0.2887   1.0000
   5.750   1.1387   0.00892   0.00350  -0.0949   0.2758   1.0000
   6.000   1.1648   0.00921   0.00370  -0.0947   0.2570   1.0000
   6.250   1.1892   0.00973   0.00400  -0.0943   0.2139   1.0000
   6.500   1.2108   0.01059   0.00457  -0.0936   0.1650   1.0000
   6.750   1.2355   0.01104   0.00494  -0.0932   0.1497   1.0000
   7.000   1.2608   0.01138   0.00525  -0.0929   0.1379   1.0000
   7.250   1.2847   0.01189   0.00563  -0.0924   0.1140   1.0000
   7.500   1.3056   0.01275   0.00625  -0.0916   0.0777   1.0000
   7.750   1.3242   0.01385   0.00708  -0.0904   0.0358   1.0000
   8.000   1.3464   0.01449   0.00770  -0.0896   0.0274   1.0000
   8.250   1.3692   0.01503   0.00827  -0.0889   0.0238   1.0000
   8.500   1.3924   0.01549   0.00878  -0.0883   0.0217   1.0000
   8.750   1.4130   0.01620   0.00952  -0.0873   0.0190   1.0000
   9.000   1.4357   0.01666   0.01002  -0.0866   0.0180   1.0000
   9.250   1.4578   0.01714   0.01054  -0.0859   0.0169   1.0000
   9.500   1.4787   0.01772   0.01114  -0.0850   0.0157   1.0000
   9.750   1.4948   0.01872   0.01222  -0.0834   0.0143   1.0000
  10.000   1.5159   0.01918   0.01271  -0.0826   0.0138   1.0000
  10.250   1.5357   0.01973   0.01331  -0.0815   0.0131   1.0000
  10.500   1.5540   0.02036   0.01398  -0.0803   0.0125   1.0000
  10.750   1.5704   0.02109   0.01475  -0.0789   0.0119   1.0000
  11.000   1.5805   0.02216   0.01589  -0.0765   0.0112   1.0000
  11.250   1.5829   0.02348   0.01733  -0.0731   0.0108   1.0000
  11.500   1.5942   0.02432   0.01823  -0.0710   0.0106   1.0000
  11.750   1.6036   0.02533   0.01932  -0.0690   0.0103   1.0000
  12.000   1.6114   0.02654   0.02061  -0.0670   0.0100   1.0000
  12.250   1.6185   0.02789   0.02204  -0.0652   0.0097   1.0000
  12.500   1.6251   0.02938   0.02360  -0.0637   0.0094   1.0000
  12.750   1.6311   0.03102   0.02532  -0.0624   0.0091   1.0000
  13.000   1.6362   0.03287   0.02724  -0.0613   0.0089   1.0000
  13.250   1.6369   0.03531   0.02976  -0.0604   0.0086   1.0000
  13.500   1.6307   0.03863   0.03319  -0.0596   0.0084   1.0000
  13.750   1.6170   0.04303   0.03774  -0.0591   0.0082   1.0000
  14.000   1.6095   0.04684   0.04168  -0.0590   0.0080   1.0000
  14.250   1.6094   0.04989   0.04483  -0.0590   0.0080   1.0000
  14.500   1.6074   0.05324   0.04829  -0.0592   0.0079   1.0000
  14.750   1.6027   0.05703   0.05218  -0.0596   0.0078   1.0000
  15.000   1.5974   0.06101   0.05627  -0.0602   0.0077   1.0000
  15.250   1.5909   0.06522   0.06059  -0.0609   0.0076   1.0000
  15.500   1.5836   0.06962   0.06509  -0.0617   0.0075   1.0000
  15.750   1.5756   0.07421   0.06979  -0.0626   0.0074   1.0000
  16.000   1.5673   0.07888   0.07456  -0.0637   0.0073   1.0000
  16.250   1.5585   0.08367   0.07945  -0.0648   0.0072   1.0000
  16.500   1.5496   0.08857   0.08445  -0.0660   0.0071   1.0000
  16.750   1.5412   0.09348   0.08945  -0.0674   0.0070   1.0000
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