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GOE 243 (MVA PR.3) AIRFOIL (goe243-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 243 (MVA PR.3) AIRFOIL (goe243-il)
Reynolds number: 50,000
Max Cl/Cd: 17.93 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe243-il-50000-n5.txt
Download as CSV file: xf-goe243-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 243 (MVA PR.3) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750   0.1110   0.12003   0.11293  -0.0974   0.8714   0.1687
  -8.250   0.0870   0.11018   0.10297  -0.1040   0.8572   0.1010
  -7.750   0.0865   0.10284   0.09559  -0.1077   0.8442   0.0902
  -7.500   0.0834   0.10200   0.09481  -0.1047   0.8344   0.0895
  -7.250   0.0917   0.09959   0.09241  -0.1048   0.8280   0.0883
  -7.000   0.1025   0.09610   0.08891  -0.1069   0.8237   0.0863
  -6.750   0.0780   0.09566   0.08855  -0.1022   0.8110   0.0851
  -6.500   0.0521   0.08980   0.08268  -0.1050   0.8036   0.0811
  -6.250   0.0322   0.08941   0.08237  -0.1005   0.7915   0.0807
  -6.000   0.0361   0.08594   0.07890  -0.1021   0.7850   0.0798
  -5.750   0.0450   0.08012   0.07301  -0.1081   0.7809   0.0786
  -5.500   0.0149   0.07821   0.07115  -0.1060   0.7666   0.0777
  -5.250   0.0577   0.06153   0.05362  -0.1415   0.7617   0.0752
  -5.000   0.0944   0.05753   0.04921  -0.1517   0.7539   0.0757
  -4.750   0.1324   0.05488   0.04623  -0.1586   0.7465   0.0773
  -4.500   0.1889   0.05178   0.04260  -0.1674   0.7426   0.0796
  -4.250   0.2447   0.04925   0.03957  -0.1741   0.7398   0.0812
  -4.000   0.2558   0.04924   0.03950  -0.1731   0.7288   0.0818
  -3.750   0.2866   0.04820   0.03841  -0.1735   0.7232   0.0831
  -3.500   0.3237   0.04695   0.03708  -0.1743   0.7197   0.0848
  -3.250   0.3376   0.04716   0.03725  -0.1730   0.7099   0.0863
  -3.000   0.3662   0.04667   0.03662  -0.1732   0.7031   0.0893
  -2.750   0.4017   0.04566   0.03563  -0.1736   0.6994   0.0931
  -2.500   0.4195   0.04590   0.03588  -0.1727   0.6904   0.0963
  -2.250   0.4448   0.04581   0.03572  -0.1724   0.6827   0.0997
  -2.000   0.4848   0.04482   0.03481  -0.1740   0.6791   0.1050
  -1.750   0.5132   0.04482   0.03481  -0.1753   0.6710   0.1123
  -1.500   0.5510   0.04448   0.03457  -0.1789   0.6627   0.1246
  -1.250   0.6118   0.04294   0.03428  -0.1860   0.6593   0.2408
  -0.750   0.6479   0.04540   0.03650  -0.1827   0.6417   0.3719
  -0.500   0.6678   0.04594   0.03699  -0.1786   0.6376   0.3997
  -0.250   0.6675   0.04811   0.03918  -0.1753   0.6251   0.4140
   0.250   0.7110   0.04875   0.03967  -0.1691   0.6164   0.4562
   0.750   0.7332   0.05094   0.04180  -0.1648   0.5985   0.4701
   1.000   0.7886   0.04967   0.04022  -0.1698   0.5960   0.4769
   1.500   0.8191   0.05183   0.04230  -0.1686   0.5783   0.4823
   1.750   0.8611   0.05081   0.04112  -0.1701   0.5758   0.4863
   2.250   0.8930   0.05367   0.04389  -0.1707   0.5582   0.4947
   2.500   0.9386   0.05265   0.04268  -0.1730   0.5560   0.5016
   3.000   0.9540   0.05650   0.04657  -0.1708   0.5382   0.5089
   3.250   0.9968   0.05558   0.04550  -0.1725   0.5361   0.5164
   4.750   1.0669   0.06691   0.05679  -0.1698   0.4941   0.5486
   5.250   1.0847   0.07157   0.06143  -0.1693   0.4786   0.5618
   5.500   1.1243   0.06969   0.05948  -0.1687   0.4768   0.5699
   6.000   1.1244   0.07610   0.06595  -0.1673   0.4585   0.5827
   6.250   1.1698   0.07323   0.06297  -0.1667   0.4568   0.5932
   6.750   1.1717   0.07892   0.06873  -0.1649   0.4382   0.6054
   7.250   1.1771   0.08428   0.07412  -0.1634   0.4198   0.6199
   7.500   1.2107   0.08261   0.07239  -0.1624   0.4169   0.6302
   8.000   1.1537   0.09719   0.08726  -0.1617   0.3895   0.6351
   8.250   1.1693   0.09819   0.08827  -0.1610   0.3838   0.6434
   8.500   1.1993   0.09715   0.08716  -0.1603   0.3810   0.6558
   8.750   1.2332   0.09530   0.08529  -0.1592   0.3790   0.6674
   9.250   1.2097   0.10538   0.09552  -0.1591   0.3568   0.6774
   9.750   1.2279   0.10906   0.09926  -0.1582   0.3421   0.6948
  10.000   1.2040   0.11623   0.10656  -0.1590   0.3271   0.6973
  10.250   1.2296   0.11550   0.10580  -0.1581   0.3242   0.7094
  10.500   1.2581   0.11422   0.10447  -0.1570   0.3222   0.7214
  11.000   1.2516   0.12234   0.11271  -0.1578   0.3036   0.7349
  11.500   1.2378   0.13242   0.12290  -0.1599   0.2847   0.7470
  12.000   1.2444   0.13909   0.12963  -0.1612   0.2722   0.7633
  12.250   1.2669   0.13869   0.12922  -0.1605   0.2706   0.7768
  13.250   1.2143   0.16764   0.15848  -0.1718   0.2458   0.7968
  13.500   1.2204   0.17098   0.16188  -0.1731   0.2434   0.8086
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