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GOE 440 AIRFOIL (goe440-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 440 AIRFOIL (goe440-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.53 at α=0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe440-il-1000000.txt
Download as CSV file: xf-goe440-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250   0.1265   0.13606   0.13400  -0.0947   0.8348   0.0012
 -12.000   0.1352   0.13304   0.13094  -0.0958   0.8240   0.0013
 -11.750   0.1440   0.13020   0.12805  -0.0969   0.8108   0.0013
 -11.500   0.1528   0.12744   0.12521  -0.0980   0.7954   0.0013
 -11.250   0.1616   0.12471   0.12240  -0.0992   0.7785   0.0013
 -11.000   0.1707   0.12201   0.11961  -0.1003   0.7620   0.0014
 -10.750   0.1798   0.11933   0.11685  -0.1015   0.7476   0.0014
 -10.500   0.1890   0.11667   0.11412  -0.1028   0.7353   0.0014
 -10.000   0.2081   0.11133   0.10868  -0.1054   0.7141   0.0015
  -9.750   0.2177   0.10870   0.10599  -0.1066   0.7050   0.0015
  -9.500   0.2274   0.10608   0.10332  -0.1079   0.6961   0.0015
  -9.250   0.2374   0.10345   0.10067  -0.1093   0.6878   0.0015
  -9.000   0.2472   0.10085   0.09803  -0.1106   0.6796   0.0016
  -8.750   0.2573   0.09825   0.09541  -0.1120   0.6721   0.0016
  -8.500   0.2675   0.09570   0.09282  -0.1133   0.6650   0.0016
  -8.250   0.2778   0.09312   0.09022  -0.1148   0.6579   0.0017
  -8.000   0.2881   0.09060   0.08766  -0.1161   0.6506   0.0017
  -7.750   0.2987   0.08805   0.08510  -0.1176   0.6434   0.0018
  -7.500   0.3091   0.08557   0.08258  -0.1190   0.6359   0.0018
  -7.250   0.3199   0.08306   0.08007  -0.1205   0.6284   0.0019
  -7.000   0.3306   0.08062   0.07759  -0.1219   0.6206   0.0019
  -6.750   0.3416   0.07815   0.07510  -0.1235   0.6127   0.0020
  -6.500   0.3525   0.07572   0.07264  -0.1250   0.6053   0.0021
  -6.250   0.3636   0.07330   0.07021  -0.1265   0.5972   0.0021
  -6.000   0.3744   0.07092   0.06780  -0.1280   0.5892   0.0022
  -5.750   0.3839   0.06873   0.06559  -0.1292   0.5801   0.0023
  -5.500   0.3963   0.06639   0.06323  -0.1313   0.5710   0.0023
  -5.250   0.4119   0.06388   0.06068  -0.1341   0.5610   0.0025
  -5.000   0.4296   0.06128   0.05803  -0.1375   0.5498   0.0026
  -4.750   0.4507   0.05856   0.05528  -0.1419   0.5389   0.0027
  -4.500   0.4745   0.05566   0.05232  -0.1471   0.5279   0.0027
  -4.250   0.5009   0.05261   0.04920  -0.1530   0.5160   0.0028
  -4.000   0.5294   0.04944   0.04596  -0.1590   0.5036   0.0028
  -3.750   0.5624   0.04597   0.04240  -0.1660   0.4913   0.0028
  -3.500   0.6010   0.04159   0.03793  -0.1750   0.4800   0.0029
  -1.750   0.9347   0.01701   0.01144  -0.2250   0.4248   0.0061
  -1.500   0.9715   0.01582   0.00997  -0.2273   0.4193   0.0077
  -1.250   1.0004   0.01591   0.00987  -0.2272   0.4141   0.0100
  -1.000   1.0433   0.01371   0.00733  -0.2309   0.4102   0.0152
  -0.750   1.0811   0.01247   0.00586  -0.2322   0.4057   0.0050
  -0.500   1.1171   0.01181   0.00497  -0.2340   0.4007   0.0039
  -0.250   1.1486   0.01163   0.00464  -0.2350   0.3971   0.0043
   0.000   1.1786   0.01156   0.00448  -0.2356   0.3933   0.0156
   0.250   1.2099   0.01134   0.00461  -0.2372   0.3837   0.2498
   0.500   1.2375   0.01139   0.00470  -0.2378   0.3726   0.3408
   0.750   1.2640   0.01154   0.00483  -0.2380   0.3635   0.3737
   1.000   1.2871   0.01191   0.00503  -0.2376   0.3418   0.3917
   1.250   1.3028   0.01276   0.00550  -0.2360   0.2906   0.4067
   1.500   1.3118   0.01401   0.00633  -0.2332   0.2302   0.4202
   1.750   1.2959   0.01656   0.00823  -0.2261   0.1197   0.4281
   2.000   1.2979   0.01778   0.00932  -0.2219   0.0242   0.4454
   2.250   1.3198   0.01805   0.00975  -0.2215   0.0200   0.5064
   2.500   1.3408   0.01838   0.01024  -0.2208   0.0145   0.5869
   2.750   1.3612   0.01873   0.01069  -0.2201   0.0240   0.6270
   3.000   1.3807   0.01914   0.01129  -0.2192   0.0194   0.6920
   3.250   1.3980   0.01962   0.01208  -0.2180   0.0109   0.7951
   3.500   1.4012   0.02044   0.01328  -0.2143   0.0090   1.0000
   3.750   1.4182   0.02106   0.01391  -0.2130   0.0087   1.0000
   4.000   1.4376   0.02153   0.01437  -0.2121   0.0069   1.0000
   4.250   1.4496   0.02251   0.01539  -0.2103   0.0058   1.0000
   4.500   1.4517   0.02420   0.01722  -0.2072   0.0052   1.0000
   4.750   1.4567   0.02574   0.01885  -0.2046   0.0050   1.0000
   5.000   1.4795   0.02603   0.01910  -0.2043   0.0045   1.0000
   5.250   1.4905   0.02719   0.02031  -0.2025   0.0040   1.0000
   5.500   1.4976   0.02869   0.02188  -0.2005   0.0035   1.0000
   5.750   1.5015   0.03048   0.02376  -0.1982   0.0032   1.0000
   6.000   1.5001   0.03280   0.02617  -0.1955   0.0030   1.0000
   6.250   1.4910   0.03592   0.02945  -0.1925   0.0028   1.0000
   6.500   1.4750   0.03992   0.03360  -0.1894   0.0028   1.0000
   6.750   1.4599   0.04420   0.03800  -0.1869   0.0027   1.0000
   7.000   1.4568   0.04741   0.04130  -0.1854   0.0027   1.0000
   7.250   1.4564   0.05045   0.04443  -0.1842   0.0027   1.0000
   7.500   1.4785   0.05091   0.04488  -0.1839   0.0025   1.0000
   7.750   1.4835   0.05339   0.04742  -0.1830   0.0023   1.0000
   8.000   1.4772   0.05734   0.05146  -0.1819   0.0022   1.0000
   8.250   1.4688   0.06163   0.05585  -0.1808   0.0021   1.0000
   8.500   1.4591   0.06619   0.06051  -0.1799   0.0021   1.0000
   8.750   1.4485   0.07099   0.06541  -0.1791   0.0020   1.0000
   9.000   1.4374   0.07598   0.07051  -0.1784   0.0019   1.0000
   9.250   1.4260   0.08104   0.07567  -0.1779   0.0019   1.0000
   9.500   1.4154   0.08606   0.08077  -0.1774   0.0018   1.0000
   9.750   1.4055   0.09106   0.08585  -0.1771   0.0018   1.0000
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