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GOE 440 AIRFOIL (goe440-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 440 AIRFOIL (goe440-il)
Reynolds number: 100,000
Max Cl/Cd: 53.16 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe440-il-100000.txt
Download as CSV file: xf-goe440-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 440 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000   0.2936   0.10260   0.09885  -0.1282   0.8598   0.0340
  -7.750   0.3045   0.09990   0.09611  -0.1293   0.8518   0.0353
  -7.500   0.3098   0.09802   0.09424  -0.1294   0.8408   0.0365
  -7.250   0.3155   0.09635   0.09257  -0.1299   0.8307   0.0377
  -7.000   0.3234   0.09497   0.09117  -0.1322   0.8232   0.0387
  -6.750   0.3218   0.09467   0.09090  -0.1325   0.8109   0.0390
  -6.500   0.3196   0.09439   0.09066  -0.1327   0.7992   0.0393
  -6.250   0.3458   0.08650   0.08269  -0.1320   0.7954   0.0417
  -6.000   0.3512   0.08422   0.08041  -0.1308   0.7843   0.0439
  -5.750   0.3558   0.08237   0.07855  -0.1304   0.7745   0.0461
  -5.500   0.3693   0.07995   0.07607  -0.1329   0.7671   0.0491
  -5.250   0.3785   0.07904   0.07517  -0.1369   0.7554   0.0509
  -5.000   0.4016   0.07805   0.07413  -0.1470   0.7441   0.0518
  -4.750   0.4076   0.07224   0.06826  -0.1390   0.7385   0.0558
  -4.500   0.4196   0.07010   0.06607  -0.1403   0.7270   0.0601
  -4.250   0.4649   0.06825   0.06411  -0.1579   0.7154   0.0651
  -4.000   0.4696   0.06378   0.05958  -0.1513   0.7090   0.0688
  -3.750   0.4878   0.06145   0.05720  -0.1537   0.6971   0.0754
  -3.500   0.5249   0.05789   0.05354  -0.1639   0.6858   0.0816
  -3.250   0.5805   0.05382   0.04920  -0.1782   0.6754   0.0947
  -3.000   0.5869   0.05137   0.04673  -0.1729   0.6668   0.1007
  -2.750   0.6226   0.04823   0.04348  -0.1793   0.6554   0.1155
  -2.500   0.6761   0.04471   0.03964  -0.1905   0.6445   0.1547
  -2.250   0.6979   0.04276   0.03761  -0.1892   0.6366   0.1879
  -1.500   0.9147   0.03073   0.02281  -0.2213   0.6075   0.0654
  -1.250   0.9496   0.02897   0.02062  -0.2224   0.5974   0.0521
  -1.000   0.9868   0.02744   0.01868  -0.2239   0.5894   0.0514
  -0.750   1.0196   0.02624   0.01729  -0.2246   0.5811   0.0533
  -0.500   1.0512   0.02548   0.01649  -0.2252   0.5734   0.0592
  -0.250   1.0964   0.02375   0.01593  -0.2289   0.5657   0.5132
   0.000   1.1129   0.02381   0.01620  -0.2258   0.5586   0.7247
   0.250   1.1252   0.02353   0.01600  -0.2223   0.5520   0.8517
   0.500   1.1544   0.02375   0.01579  -0.2231   0.5453   1.0000
   0.750   1.1822   0.02425   0.01587  -0.2237   0.5381   1.0000
   1.000   1.2141   0.02462   0.01583  -0.2249   0.5325   1.0000
   1.250   1.2361   0.02528   0.01640  -0.2246   0.5251   1.0000
   1.500   1.2675   0.02558   0.01639  -0.2256   0.5197   1.0000
   1.750   1.2885   0.02632   0.01712  -0.2251   0.5130   1.0000
   2.000   1.3106   0.02593   0.01645  -0.2241   0.4976   1.0000
   2.250   1.3301   0.02574   0.01604  -0.2227   0.4823   1.0000
   2.500   1.3427   0.02526   0.01515  -0.2199   0.4591   1.0000
   2.750   1.3534   0.02552   0.01530  -0.2173   0.4434   1.0000
   3.000   1.3516   0.02590   0.01560  -0.2126   0.4206   1.0000
   3.250   1.3551   0.02645   0.01603  -0.2090   0.4035   1.0000
   3.500   1.3561   0.02717   0.01669  -0.2051   0.3870   1.0000
   3.750   1.3549   0.02820   0.01759  -0.2013   0.3660   1.0000
   4.000   1.3632   0.02913   0.01844  -0.1990   0.3535   1.0000
   4.250   1.3740   0.03007   0.01935  -0.1972   0.3422   1.0000
   4.500   1.3844   0.03107   0.02032  -0.1955   0.3307   1.0000
   4.750   1.3940   0.03219   0.02139  -0.1937   0.3193   1.0000
   5.000   1.4007   0.03355   0.02270  -0.1917   0.3037   1.0000
   5.250   1.4199   0.03419   0.02344  -0.1910   0.3085   1.0000
   5.500   1.4475   0.03436   0.02382  -0.1911   0.3208   1.0000
   5.750   1.4710   0.03479   0.02438  -0.1908   0.3273   1.0000
   6.000   1.4911   0.03542   0.02513  -0.1902   0.3296   1.0000
   6.250   1.5144   0.03592   0.02578  -0.1898   0.3345   1.0000
   6.500   1.5286   0.03690   0.02685  -0.1886   0.3322   1.0000
   6.750   1.5374   0.03816   0.02817  -0.1869   0.3268   1.0000
   7.000   1.5437   0.03967   0.02975  -0.1851   0.3194   1.0000
   7.250   1.5467   0.04145   0.03155  -0.1831   0.3108   1.0000
   7.500   1.5432   0.04387   0.03397  -0.1809   0.2963   1.0000
   7.750   1.5414   0.04634   0.03644  -0.1789   0.2829   1.0000
   8.000   1.5373   0.04914   0.03928  -0.1771   0.2687   1.0000
   8.250   1.5326   0.05217   0.04230  -0.1754   0.2550   1.0000
   8.500   1.5266   0.05551   0.04563  -0.1738   0.2418   1.0000
   8.750   1.5184   0.05924   0.04936  -0.1724   0.2286   1.0000
   9.000   1.5080   0.06342   0.05355  -0.1711   0.2153   1.0000
   9.250   1.4940   0.06822   0.05835  -0.1701   0.2013   1.0000
   9.500   1.4742   0.07396   0.06410  -0.1692   0.1848   1.0000
   9.750   1.4502   0.08051   0.07066  -0.1685   0.1668   1.0000
  10.000   1.4273   0.08717   0.07735  -0.1682   0.1508   1.0000
  10.250   1.4052   0.09390   0.08413  -0.1682   0.1361   1.0000
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