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GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 241 (MVA PR.1) AIRFOIL (goe241-il)
Reynolds number: 50,000
Max Cl/Cd: 18.83 at α=0.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe241-il-50000-n5.txt
Download as CSV file: xf-goe241-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 241 (MVA PR.1) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000   0.1145   0.11402   0.10716  -0.1010   0.8705   0.1764
  -8.750   0.1240   0.11172   0.10487  -0.1012   0.8619   0.1803
  -8.250   0.1057   0.10170   0.09472  -0.1079   0.8445   0.1056
  -8.000   0.0918   0.09734   0.09036  -0.1103   0.8349   0.0952
  -7.750   0.1082   0.09435   0.08734  -0.1110   0.8288   0.0932
  -7.500   0.1042   0.09238   0.08540  -0.1097   0.8177   0.0917
  -7.250   0.1118   0.08863   0.08163  -0.1119   0.8123   0.0905
  -7.000   0.0940   0.08737   0.08044  -0.1089   0.7985   0.0896
  -6.500   0.0568   0.07522   0.06822  -0.1196   0.7772   0.0844
  -6.250   0.0622   0.07056   0.06347  -0.1246   0.7686   0.0838
  -6.000   0.0708   0.06505   0.05779  -0.1326   0.7584   0.0830
  -5.750   0.1185   0.05654   0.04867  -0.1506   0.7544   0.0820
  -5.500   0.1366   0.05348   0.04525  -0.1558   0.7419   0.0818
  -5.250   0.1903   0.04931   0.04045  -0.1653   0.7375   0.0827
  -5.000   0.2475   0.04599   0.03643  -0.1735   0.7345   0.0849
  -4.750   0.2584   0.04550   0.03592  -0.1722   0.7218   0.0859
  -4.500   0.2994   0.04367   0.03389  -0.1748   0.7175   0.0874
  -4.250   0.3203   0.04308   0.03317  -0.1746   0.7078   0.0883
  -4.000   0.3529   0.04199   0.03190  -0.1755   0.7013   0.0897
  -3.750   0.3936   0.04065   0.03034  -0.1772   0.6976   0.0925
  -3.500   0.4071   0.04086   0.03044  -0.1757   0.6862   0.0947
  -3.250   0.4410   0.03993   0.02945  -0.1763   0.6813   0.0978
  -3.000   0.4798   0.03887   0.02833  -0.1775   0.6781   0.1011
  -2.750   0.4880   0.03957   0.02905  -0.1753   0.6661   0.1030
  -2.500   0.5269   0.03879   0.02811  -0.1768   0.6619   0.1083
  -2.250   0.5502   0.03886   0.02825  -0.1771   0.6536   0.1137
  -2.000   0.5820   0.03865   0.02798  -0.1785   0.6468   0.1212
  -1.750   0.6313   0.03759   0.02692  -0.1827   0.6432   0.1365
  -1.250   0.6867   0.03821   0.02865  -0.1850   0.6288   0.3526
  -1.000   0.7153   0.03876   0.02906  -0.1837   0.6248   0.4088
  -0.750   0.7216   0.04039   0.03065  -0.1807   0.6162   0.4322
  -0.500   0.7356   0.04148   0.03170  -0.1779   0.6097   0.4536
  -0.250   0.7609   0.04190   0.03203  -0.1758   0.6063   0.4769
   0.000   0.7576   0.04394   0.03412  -0.1721   0.5977   0.4897
   0.250   0.7668   0.04524   0.03543  -0.1691   0.5915   0.5072
   0.500   0.7954   0.04531   0.03538  -0.1683   0.5883   0.5254
   0.750   0.8414   0.04469   0.03449  -0.1711   0.5861   0.5358
   1.250   0.8506   0.04840   0.03819  -0.1678   0.5706   0.5435
   1.500   0.8925   0.04797   0.03753  -0.1701   0.5684   0.5522
   2.000   0.8917   0.05334   0.04297  -0.1669   0.5527   0.5602
   2.250   0.9301   0.05288   0.04233  -0.1683   0.5504   0.5683
   2.500   0.9712   0.05203   0.04132  -0.1695   0.5486   0.5757
   3.000   0.9660   0.05813   0.04746  -0.1666   0.5316   0.5858
   3.250   1.0141   0.05614   0.04529  -0.1676   0.5299   0.5945
   3.750   1.0269   0.06004   0.04914  -0.1654   0.5123   0.6065
   4.250   1.0390   0.06390   0.05299  -0.1629   0.4948   0.6183
   4.500   1.0651   0.06389   0.05288  -0.1626   0.4901   0.6261
   5.250   1.1129   0.06722   0.05615  -0.1607   0.4728   0.6481
   5.750   1.1094   0.07356   0.06259  -0.1586   0.4554   0.6594
   6.750   1.1047   0.08648   0.07572  -0.1553   0.4193   0.6831
   7.000   1.1307   0.08624   0.07543  -0.1548   0.4160   0.6935
   7.500   1.1389   0.09125   0.08055  -0.1534   0.3994   0.7085
   8.000   1.1402   0.09739   0.08680  -0.1523   0.3817   0.7235
   8.500   1.1103   0.10881   0.09838  -0.1525   0.3593   0.7337
   9.000   1.1277   0.11333   0.10302  -0.1520   0.3487   0.7567
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