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GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il)
Reynolds number: 50,000
Max Cl/Cd: 39.55 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe184-il-50000-n5.txt
Download as CSV file: xf-goe184-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2943   0.10049   0.09394  -0.0262   1.0000   0.0978
  -7.500  -0.2945   0.09824   0.09179  -0.0263   1.0000   0.0995
  -7.250  -0.2960   0.09615   0.08982  -0.0267   1.0000   0.1013
  -7.000  -0.2992   0.09443   0.08822  -0.0283   1.0000   0.1032
  -6.750  -0.3025   0.09287   0.08678  -0.0309   1.0000   0.1043
  -6.500  -0.3037   0.09109   0.08508  -0.0336   1.0000   0.1048
  -6.250  -0.3019   0.08738   0.08145  -0.0302   1.0000   0.1064
  -6.000  -0.3001   0.08481   0.07895  -0.0266   1.0000   0.1103
  -5.750  -0.3009   0.08289   0.07710  -0.0264   1.0000   0.1141
  -5.500  -0.2971   0.08164   0.07582  -0.0329   1.0000   0.1189
  -5.250  -0.2530   0.07195   0.06583  -0.0453   0.9910   0.0783
  -5.000  -0.2274   0.06779   0.06165  -0.0473   0.9832   0.0757
  -4.750  -0.1851   0.06259   0.05624  -0.0566   0.9741   0.0765
  -4.500  -0.1461   0.05784   0.05128  -0.0638   0.9643   0.0759
  -4.250  -0.1065   0.05320   0.04638  -0.0704   0.9548   0.0744
  -4.000  -0.0592   0.04833   0.04115  -0.0783   0.9475   0.0748
  -3.750  -0.0146   0.04359   0.03587  -0.0852   0.9372   0.0775
  -3.500   0.0318   0.03921   0.03091  -0.0912   0.9294   0.0780
  -3.250   0.0731   0.03588   0.02711  -0.0954   0.9203   0.0792
  -3.000   0.1103   0.03388   0.02485  -0.0981   0.9103   0.0818
  -2.750   0.1528   0.03168   0.02218  -0.1014   0.9019   0.0881
  -2.500   0.1895   0.02952   0.01948  -0.1034   0.8904   0.0925
  -2.250   0.2248   0.02812   0.01784  -0.1049   0.8793   0.0976
  -2.000   0.2632   0.02647   0.01573  -0.1065   0.8693   0.1064
  -1.750   0.2969   0.02557   0.01463  -0.1072   0.8571   0.1209
  -1.500   0.3282   0.02499   0.01393  -0.1075   0.8433   0.1387
  -1.250   0.3595   0.02460   0.01337  -0.1077   0.8286   0.1613
  -1.000   0.3904   0.02411   0.01271  -0.1077   0.8136   0.1772
  -0.750   0.4203   0.02363   0.01210  -0.1073   0.7984   0.1889
  -0.500   0.4496   0.02322   0.01148  -0.1068   0.7833   0.1964
  -0.250   0.4777   0.02285   0.01102  -0.1062   0.7684   0.2028
   0.250   0.5325   0.02236   0.01037  -0.1050   0.7399   0.2220
   0.500   0.5595   0.02216   0.01017  -0.1044   0.7263   0.2397
   0.750   0.5865   0.02191   0.01005  -0.1039   0.7133   0.2769
   1.000   0.6130   0.02123   0.00991  -0.1036   0.7010   0.4142
   1.500   0.6627   0.02065   0.00983  -0.1013   0.6736   1.0000
   1.750   0.6889   0.02094   0.00994  -0.1008   0.6605   1.0000
   2.000   0.7152   0.02123   0.01006  -0.1002   0.6481   1.0000
   2.250   0.7418   0.02150   0.01019  -0.0997   0.6365   1.0000
   2.500   0.7682   0.02180   0.01036  -0.0992   0.6249   1.0000
   2.750   0.7937   0.02216   0.01066  -0.0987   0.6127   1.0000
   3.000   0.8196   0.02252   0.01096  -0.0982   0.6014   1.0000
   3.250   0.8462   0.02283   0.01118  -0.0977   0.5913   1.0000
   3.500   0.8721   0.02323   0.01153  -0.0973   0.5808   1.0000
   3.750   0.8976   0.02370   0.01201  -0.0969   0.5705   1.0000
   4.000   0.9245   0.02406   0.01230  -0.0964   0.5619   1.0000
   4.250   0.9494   0.02461   0.01289  -0.0960   0.5516   1.0000
   4.500   0.9749   0.02514   0.01346  -0.0956   0.5425   1.0000
   4.750   1.0009   0.02562   0.01395  -0.0951   0.5337   1.0000
   5.000   1.0248   0.02626   0.01466  -0.0946   0.5234   1.0000
   5.250   1.0506   0.02670   0.01512  -0.0940   0.5141   1.0000
   5.500   1.0742   0.02730   0.01581  -0.0933   0.5032   1.0000
   5.750   1.0972   0.02793   0.01655  -0.0926   0.4925   1.0000
   6.000   1.1224   0.02838   0.01705  -0.0920   0.4830   1.0000
   6.250   1.1443   0.02904   0.01787  -0.0911   0.4717   1.0000
   6.500   1.1660   0.02969   0.01868  -0.0903   0.4606   1.0000
   6.750   1.1897   0.03018   0.01926  -0.0895   0.4508   1.0000
   7.000   1.2112   0.03087   0.02017  -0.0886   0.4405   1.0000
   7.250   1.2318   0.03165   0.02117  -0.0877   0.4306   1.0000
   7.500   1.2555   0.03213   0.02177  -0.0868   0.4214   1.0000
   7.750   1.2750   0.03283   0.02270  -0.0857   0.4097   1.0000
   8.250   1.3126   0.03415   0.02447  -0.0830   0.3847   1.0000
   8.500   1.3313   0.03473   0.02522  -0.0816   0.3716   1.0000
   8.750   1.3491   0.03530   0.02595  -0.0800   0.3575   1.0000
   9.000   1.3634   0.03589   0.02670  -0.0781   0.3404   1.0000
   9.250   1.3748   0.03653   0.02749  -0.0758   0.3212   1.0000
   9.500   1.3841   0.03728   0.02833  -0.0734   0.3019   1.0000
   9.750   1.3910   0.03834   0.02951  -0.0710   0.2840   1.0000
  10.000   1.3931   0.03981   0.03122  -0.0685   0.2652   1.0000
  10.250   1.3902   0.04138   0.03292  -0.0656   0.2454   1.0000
  10.500   1.3858   0.04332   0.03494  -0.0631   0.2243   1.0000
  10.750   1.3819   0.04558   0.03724  -0.0613   0.2056   1.0000
  11.250   1.3647   0.05178   0.04323  -0.0588   0.1710   1.0000
  11.500   1.3529   0.05580   0.04722  -0.0584   0.1549   1.0000
  11.750   1.3418   0.06011   0.05165  -0.0584   0.1396   1.0000
  12.000   1.3306   0.06476   0.05648  -0.0589   0.1225   1.0000
  12.250   1.3179   0.06975   0.06153  -0.0597   0.1066   1.0000
  12.500   1.3040   0.07498   0.06672  -0.0607   0.0949   1.0000
  12.750   1.2906   0.08025   0.07194  -0.0617   0.0861   1.0000
  13.000   1.2771   0.08557   0.07717  -0.0628   0.0794   1.0000
  13.250   1.2678   0.09042   0.08209  -0.0636   0.0723   1.0000
  13.500   1.2587   0.09528   0.08696  -0.0645   0.0672   1.0000
  13.750   1.2524   0.09981   0.09155  -0.0652   0.0627   1.0000
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