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GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il)
Reynolds number: 50,000
Max Cl/Cd: 41.19 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe124-il-50000-n5.txt
Download as CSV file: xf-goe124-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 124 (MVA H.4) 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  -0.2975   0.11056   0.10377  -0.0276   1.0000   0.0853
  -8.250  -0.3032   0.11014   0.10349  -0.0299   1.0000   0.0864
  -8.000  -0.3071   0.10959   0.10309  -0.0336   1.0000   0.0870
  -7.750  -0.2927   0.10310   0.09663  -0.0299   1.0000   0.0889
  -7.500  -0.2839   0.09958   0.09315  -0.0284   1.0000   0.0925
  -7.250  -0.2843   0.09763   0.09132  -0.0281   1.0000   0.0963
  -7.000  -0.2910   0.09669   0.09052  -0.0286   1.0000   0.0997
  -6.750  -0.3022   0.09688   0.09085  -0.0309   1.0000   0.1015
  -6.500  -0.3093   0.09680   0.09087  -0.0342   1.0000   0.1022
  -6.250  -0.3102   0.09201   0.08617  -0.0265   1.0000   0.1044
  -6.000  -0.2866   0.08789   0.08202  -0.0295   0.9920   0.1100
  -5.750  -0.2465   0.08432   0.07832  -0.0451   0.9787   0.1178
  -5.500  -0.2275   0.07975   0.07375  -0.0439   0.9724   0.1224
  -5.250  -0.1898   0.07599   0.06987  -0.0547   0.9620   0.1338
  -5.000  -0.1551   0.07281   0.06657  -0.0627   0.9516   0.1480
  -4.750  -0.1337   0.06875   0.06254  -0.0621   0.9453   0.1563
  -4.500  -0.1017   0.06528   0.05898  -0.0678   0.9357   0.1684
  -4.250  -0.0674   0.06192   0.05552  -0.0734   0.9276   0.1832
  -4.000  -0.0350   0.05880   0.05232  -0.0779   0.9190   0.1994
  -3.750  -0.0011   0.05613   0.04952  -0.0832   0.9097   0.2259
  -3.250   0.1167   0.04724   0.03952  -0.1039   0.8942   0.1315
  -3.000   0.1598   0.04294   0.03490  -0.1082   0.8871   0.0973
  -2.750   0.2038   0.03993   0.03130  -0.1126   0.8786   0.0854
  -2.500   0.2403   0.03758   0.02870  -0.1152   0.8712   0.0828
  -2.250   0.2743   0.03576   0.02654  -0.1172   0.8618   0.0828
  -2.000   0.3124   0.03393   0.02433  -0.1195   0.8548   0.0828
  -1.750   0.3438   0.03251   0.02258  -0.1205   0.8448   0.0813
  -1.500   0.3797   0.03103   0.02073  -0.1218   0.8376   0.0798
  -1.250   0.4098   0.02997   0.01937  -0.1222   0.8274   0.0789
  -1.000   0.4406   0.02902   0.01812  -0.1225   0.8182   0.0785
  -0.750   0.4723   0.02811   0.01691  -0.1226   0.8091   0.0785
  -0.500   0.4998   0.02748   0.01608  -0.1222   0.7973   0.0803
  -0.250   0.5283   0.02691   0.01526  -0.1216   0.7863   0.0836
   0.000   0.5585   0.02629   0.01437  -0.1209   0.7766   0.0860
   0.500   0.6114   0.02546   0.01332  -0.1194   0.7535   0.0892
   0.750   0.6403   0.02500   0.01276  -0.1189   0.7448   0.0922
   1.000   0.6663   0.02488   0.01259  -0.1184   0.7331   0.0962
   1.250   0.6932   0.02476   0.01242  -0.1179   0.7227   0.1037
   1.500   0.7221   0.02446   0.01216  -0.1176   0.7139   0.1200
   1.750   0.7488   0.02424   0.01230  -0.1175   0.7023   0.1764
   2.250   0.7960   0.02299   0.01218  -0.1146   0.6828   1.0000
   2.500   0.8211   0.02337   0.01241  -0.1140   0.6708   1.0000
   2.750   0.8470   0.02370   0.01260  -0.1135   0.6597   1.0000
   3.000   0.8743   0.02389   0.01265  -0.1129   0.6501   1.0000
   3.250   0.8995   0.02427   0.01299  -0.1123   0.6384   1.0000
   3.500   0.9245   0.02467   0.01336  -0.1118   0.6266   1.0000
   3.750   0.9505   0.02499   0.01363  -0.1112   0.6160   1.0000
   4.000   0.9769   0.02529   0.01391  -0.1106   0.6057   1.0000
   4.250   1.0010   0.02581   0.01447  -0.1101   0.5938   1.0000
   4.500   1.0260   0.02627   0.01494  -0.1095   0.5830   1.0000
   4.750   1.0529   0.02654   0.01522  -0.1090   0.5738   1.0000
   5.000   1.0760   0.02718   0.01596  -0.1084   0.5620   1.0000
   5.250   1.1003   0.02777   0.01662  -0.1079   0.5518   1.0000
   5.500   1.1267   0.02815   0.01706  -0.1074   0.5434   1.0000
   5.750   1.1489   0.02891   0.01795  -0.1068   0.5322   1.0000
   6.000   1.1726   0.02942   0.01856  -0.1060   0.5215   1.0000
   6.250   1.1979   0.02966   0.01884  -0.1052   0.5106   1.0000
   6.500   1.2206   0.03003   0.01934  -0.1042   0.4976   1.0000
   6.750   1.2422   0.03044   0.01986  -0.1030   0.4835   1.0000
   7.000   1.2634   0.03084   0.02036  -0.1018   0.4692   1.0000
   7.250   1.2842   0.03125   0.02092  -0.1006   0.4548   1.0000
   7.500   1.3045   0.03167   0.02145  -0.0992   0.4398   1.0000
   7.750   1.3242   0.03219   0.02212  -0.0979   0.4255   1.0000
   8.000   1.3434   0.03281   0.02289  -0.0966   0.4118   1.0000
   8.250   1.3617   0.03343   0.02370  -0.0951   0.3972   1.0000
   8.500   1.3787   0.03408   0.02450  -0.0935   0.3812   1.0000
   8.750   1.3942   0.03479   0.02533  -0.0917   0.3637   1.0000
   9.000   1.4083   0.03555   0.02619  -0.0897   0.3453   1.0000
   9.250   1.4173   0.03667   0.02745  -0.0874   0.3248   1.0000
   9.500   1.4233   0.03793   0.02887  -0.0848   0.3028   1.0000
   9.750   1.4268   0.03936   0.03037  -0.0821   0.2807   1.0000
  10.000   1.4252   0.04111   0.03224  -0.0791   0.2588   1.0000
  10.250   1.4241   0.04301   0.03414  -0.0766   0.2386   1.0000
  10.500   1.4229   0.04525   0.03642  -0.0745   0.2197   1.0000
  10.750   1.4216   0.04764   0.03880  -0.0727   0.2042   1.0000
  11.000   1.4195   0.05025   0.04138  -0.0711   0.1909   1.0000
  11.250   1.4163   0.05310   0.04417  -0.0698   0.1787   1.0000
  11.500   1.4114   0.05622   0.04723  -0.0687   0.1666   1.0000
  12.000   1.3968   0.06341   0.05442  -0.0674   0.1427   1.0000
  12.250   1.3886   0.06740   0.05850  -0.0673   0.1315   1.0000
  12.500   1.3806   0.07144   0.06259  -0.0673   0.1217   1.0000
  12.750   1.3737   0.07536   0.06655  -0.0672   0.1132   1.0000
  13.000   1.3671   0.07957   0.07097  -0.0674   0.1046   1.0000
  13.250   1.3601   0.08364   0.07503  -0.0676   0.0970   1.0000
  13.500   1.3522   0.08829   0.07994  -0.0683   0.0888   1.0000
  13.750   1.3454   0.09270   0.08442  -0.0689   0.0820   1.0000
  14.000   1.3385   0.09737   0.08925  -0.0698   0.0753   1.0000
  14.250   1.3324   0.10195   0.09392  -0.0708   0.0699   1.0000
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