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GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il)
Reynolds number: 50,000
Max Cl/Cd: 39.84 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe143-il-50000-n5.txt
Download as CSV file: xf-goe143-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 143 (MVA H.20) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4268   0.12248   0.11541  -0.0059   1.0000   0.0856
  -9.250  -0.4292   0.12076   0.11377  -0.0092   1.0000   0.0865
  -9.000  -0.4315   0.11881   0.11192  -0.0125   1.0000   0.0868
  -8.750  -0.4103   0.11169   0.10474  -0.0094   1.0000   0.0893
  -8.500  -0.4016   0.10815   0.10122  -0.0096   1.0000   0.0930
  -8.250  -0.4000   0.10567   0.09880  -0.0117   1.0000   0.0975
  -8.000  -0.4063   0.10432   0.09758  -0.0163   1.0000   0.0996
  -7.750  -0.3975   0.09975   0.09306  -0.0161   1.0000   0.1017
  -7.500  -0.3865   0.09594   0.08927  -0.0151   1.0000   0.1061
  -7.250  -0.3812   0.09294   0.08633  -0.0178   1.0000   0.1102
  -7.000  -0.3774   0.09076   0.08418  -0.0278   1.0000   0.1135
  -6.250  -0.3476   0.07990   0.07339  -0.0338   1.0000   0.1284
  -6.000  -0.3397   0.07624   0.06983  -0.0282   1.0000   0.1347
  -5.750  -0.3277   0.07304   0.06657  -0.0344   1.0000   0.1439
  -5.500  -0.3185   0.06975   0.06334  -0.0321   1.0000   0.1480
  -5.000  -0.2940   0.06367   0.05724  -0.0346   1.0000   0.1649
  -4.750  -0.2810   0.06119   0.05472  -0.0370   1.0000   0.1899
  -4.500  -0.2375   0.05378   0.04669  -0.0462   1.0000   0.1113
  -4.000  -0.1813   0.04501   0.03691  -0.0525   1.0000   0.0867
  -3.750  -0.1625   0.04242   0.03425  -0.0527   1.0000   0.0880
  -3.500  -0.1447   0.04058   0.03237  -0.0524   1.0000   0.0913
  -3.250  -0.1213   0.03836   0.02986  -0.0532   1.0000   0.0921
  -3.000  -0.0955   0.03602   0.02711  -0.0541   1.0000   0.0903
  -2.750  -0.0696   0.03403   0.02470  -0.0547   1.0000   0.0893
  -2.500  -0.0359   0.03215   0.02240  -0.0566   0.9964   0.0890
  -2.250   0.0102   0.03028   0.02014  -0.0607   0.9867   0.0900
  -2.000   0.0547   0.02891   0.01846  -0.0645   0.9762   0.0951
  -1.750   0.0990   0.02760   0.01671  -0.0677   0.9650   0.0980
  -1.500   0.1419   0.02641   0.01518  -0.0705   0.9531   0.0993
  -1.250   0.1838   0.02529   0.01386  -0.0731   0.9407   0.1012
  -1.000   0.2251   0.02428   0.01278  -0.0754   0.9280   0.1046
  -0.750   0.2652   0.02360   0.01191  -0.0773   0.9138   0.1127
  -0.500   0.3032   0.02279   0.01107  -0.0788   0.8986   0.1191
  -0.250   0.3394   0.02215   0.01034  -0.0797   0.8820   0.1248
   0.000   0.3746   0.02152   0.00969  -0.0805   0.8647   0.1321
   0.250   0.4088   0.02095   0.00916  -0.0812   0.8469   0.1486
   0.500   0.4406   0.02045   0.00874  -0.0813   0.8272   0.1717
   0.750   0.4678   0.01871   0.00857  -0.0812   0.8076   0.5330
   1.000   0.4963   0.01796   0.00815  -0.0795   0.7865   1.0000
   1.250   0.5234   0.01812   0.00804  -0.0786   0.7631   1.0000
   1.500   0.5508   0.01826   0.00795  -0.0778   0.7408   1.0000
   1.750   0.5769   0.01845   0.00797  -0.0769   0.7167   1.0000
   2.000   0.6035   0.01863   0.00796  -0.0759   0.6949   1.0000
   2.500   0.6556   0.01912   0.00817  -0.0742   0.6512   1.0000
   2.750   0.6815   0.01942   0.00835  -0.0735   0.6305   1.0000
   3.250   0.7337   0.02010   0.00885  -0.0721   0.5926   1.0000
   3.500   0.7601   0.02049   0.00914  -0.0715   0.5752   1.0000
   3.750   0.7861   0.02091   0.00950  -0.0709   0.5578   1.0000
   4.000   0.8116   0.02134   0.00993  -0.0703   0.5389   1.0000
   4.250   0.8361   0.02173   0.01024  -0.0693   0.5170   1.0000
   4.500   0.8597   0.02212   0.01055  -0.0683   0.4923   1.0000
   4.750   0.8830   0.02251   0.01084  -0.0671   0.4681   1.0000
   5.000   0.9063   0.02297   0.01130  -0.0662   0.4448   1.0000
   5.250   0.9303   0.02346   0.01179  -0.0654   0.4257   1.0000
   5.500   0.9540   0.02398   0.01235  -0.0647   0.4067   1.0000
   5.750   0.9773   0.02453   0.01300  -0.0639   0.3867   1.0000
   6.000   1.0004   0.02511   0.01364  -0.0631   0.3671   1.0000
   6.250   1.0229   0.02571   0.01427  -0.0622   0.3473   1.0000
   6.500   1.0449   0.02638   0.01510  -0.0613   0.3248   1.0000
   6.750   1.0662   0.02709   0.01582  -0.0603   0.3038   1.0000
   7.000   1.0875   0.02790   0.01672  -0.0594   0.2827   1.0000
   7.250   1.1086   0.02879   0.01767  -0.0584   0.2648   1.0000
   7.500   1.1300   0.02976   0.01872  -0.0575   0.2506   1.0000
   7.750   1.1516   0.03079   0.01988  -0.0567   0.2395   1.0000
   8.000   1.1735   0.03184   0.02101  -0.0559   0.2308   1.0000
   8.250   1.1948   0.03296   0.02236  -0.0551   0.2216   1.0000
   8.500   1.2130   0.03390   0.02342  -0.0540   0.2093   1.0000
   8.750   1.2275   0.03476   0.02438  -0.0527   0.1931   1.0000
   9.000   1.2414   0.03575   0.02554  -0.0514   0.1783   1.0000
   9.250   1.2558   0.03686   0.02684  -0.0501   0.1669   1.0000
   9.500   1.2671   0.03808   0.02823  -0.0487   0.1529   1.0000
   9.750   1.2758   0.03949   0.02980  -0.0471   0.1376   1.0000
  10.000   1.2822   0.04114   0.03163  -0.0455   0.1224   1.0000
  10.250   1.2829   0.04315   0.03374  -0.0436   0.1051   1.0000
  10.750   1.2809   0.04804   0.03897  -0.0403   0.0737   1.0000
  11.000   1.2771   0.05111   0.04217  -0.0395   0.0626   1.0000
  11.250   1.2705   0.05471   0.04583  -0.0393   0.0561   1.0000
  11.500   1.2623   0.05879   0.05001  -0.0397   0.0524   1.0000
  11.750   1.2534   0.06327   0.05459  -0.0406   0.0497   1.0000
  12.000   1.2434   0.06817   0.05958  -0.0421   0.0478   1.0000
  12.250   1.2325   0.07340   0.06489  -0.0438   0.0464   1.0000
  12.500   1.2223   0.07869   0.07026  -0.0456   0.0452   1.0000
  12.750   1.2133   0.08391   0.07565  -0.0473   0.0441   1.0000
  13.000   1.2045   0.08914   0.08105  -0.0489   0.0433   1.0000
  13.250   1.1960   0.09442   0.08649  -0.0506   0.0425   1.0000
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