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GOE 495 AIRFOIL (goe495-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 495 AIRFOIL (goe495-il)
Reynolds number: 200,000
Max Cl/Cd: 95.79 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe495-il-200000.txt
Download as CSV file: xf-goe495-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 495 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3669   0.09151   0.08830  -0.0235   1.0000   0.0410
  -7.000  -0.3849   0.09087   0.08774  -0.0198   1.0000   0.0415
  -6.750  -0.3982   0.08959   0.08653  -0.0184   1.0000   0.0425
  -6.500  -0.3738   0.08508   0.08202  -0.0333   0.9954   0.0443
  -6.250  -0.3450   0.07758   0.07449  -0.0452   0.9899   0.0450
  -6.000  -0.3352   0.07479   0.07172  -0.0408   0.9872   0.0468
  -5.750  -0.3079   0.07169   0.06859  -0.0445   0.9840   0.0504
  -5.500  -0.2440   0.06097   0.05764  -0.0727   0.9757   0.0575
  -5.250  -0.2306   0.05896   0.05570  -0.0693   0.9727   0.0593
  -5.000  -0.1309   0.03471   0.03143  -0.0859   0.9571   0.0717
  -4.750  -0.1170   0.03316   0.02991  -0.0840   0.9496   0.0745
  -4.500  -0.0747   0.02712   0.02363  -0.0952   0.9468   0.0864
  -4.250  -0.0402   0.02859   0.02351  -0.1123   0.9585   0.0588
  -4.000   0.0035   0.02355   0.01782  -0.1166   0.9572   0.0517
  -3.750   0.0344   0.02139   0.01514  -0.1176   0.9515   0.0542
  -3.500   0.0722   0.01950   0.01272  -0.1196   0.9481   0.0558
  -3.250   0.1108   0.01773   0.01060  -0.1219   0.9457   0.0590
  -3.000   0.1507   0.01672   0.00952  -0.1243   0.9437   0.0634
  -2.750   0.1794   0.01603   0.00871  -0.1243   0.9375   0.0666
  -2.500   0.2157   0.01525   0.00785  -0.1259   0.9337   0.0724
  -2.250   0.2554   0.01458   0.00719  -0.1282   0.9312   0.0798
  -2.000   0.2975   0.01390   0.00655  -0.1309   0.9294   0.0945
  -1.750   0.3249   0.01334   0.00629  -0.1309   0.9221   0.1631
  -1.500   0.3627   0.01294   0.00604  -0.1329   0.9186   0.2293
  -1.250   0.4019   0.01255   0.00581  -0.1351   0.9159   0.2836
  -1.000   0.4298   0.01234   0.00581  -0.1351   0.9087   0.3509
  -0.750   0.4641   0.01192   0.00569  -0.1363   0.9041   0.4488
  -0.500   0.4999   0.01135   0.00553  -0.1376   0.9009   0.5728
  -0.250   0.5259   0.01043   0.00543  -0.1365   0.8931   1.0000
   0.000   0.5612   0.01031   0.00516  -0.1377   0.8881   1.0000
   0.250   0.5893   0.01034   0.00509  -0.1374   0.8798   1.0000
   0.500   0.6223   0.01024   0.00490  -0.1381   0.8737   1.0000
   0.750   0.6496   0.01028   0.00488  -0.1376   0.8644   1.0000
   1.000   0.6813   0.01018   0.00471  -0.1379   0.8569   1.0000
   1.250   0.7084   0.01017   0.00465  -0.1373   0.8460   1.0000
   1.500   0.7354   0.01019   0.00462  -0.1367   0.8348   1.0000
   1.750   0.7632   0.01019   0.00460  -0.1362   0.8240   1.0000
   2.000   0.7912   0.01018   0.00454  -0.1357   0.8128   1.0000
   2.250   0.8183   0.01021   0.00454  -0.1351   0.8010   1.0000
   2.500   0.8442   0.01028   0.00462  -0.1344   0.7882   1.0000
   2.750   0.8702   0.01035   0.00468  -0.1336   0.7751   1.0000
   3.000   0.8963   0.01042   0.00477  -0.1330   0.7620   1.0000
   3.250   0.9222   0.01049   0.00484  -0.1322   0.7478   1.0000
   3.500   0.9478   0.01053   0.00490  -0.1313   0.7315   1.0000
   3.750   0.9730   0.01056   0.00491  -0.1303   0.7121   1.0000
   4.000   0.9969   0.01060   0.00491  -0.1290   0.6866   1.0000
   4.250   1.0204   0.01070   0.00495  -0.1276   0.6578   1.0000
   4.500   1.0432   0.01089   0.00508  -0.1262   0.6247   1.0000
   4.750   1.0659   0.01116   0.00528  -0.1249   0.5922   1.0000
   5.000   1.0879   0.01152   0.00553  -0.1234   0.5565   1.0000
   5.250   1.1082   0.01196   0.00583  -0.1217   0.5103   1.0000
   5.500   1.1256   0.01260   0.00621  -0.1196   0.4428   1.0000
   5.750   1.1370   0.01374   0.00681  -0.1167   0.3367   1.0000
   6.000   1.1422   0.01569   0.00787  -0.1133   0.1914   1.0000
   6.250   1.1495   0.01778   0.00920  -0.1102   0.0912   1.0000
   6.500   1.1646   0.01905   0.01034  -0.1081   0.0693   1.0000
   6.750   1.1802   0.02023   0.01153  -0.1060   0.0598   1.0000
   7.000   1.1934   0.02166   0.01292  -0.1037   0.0525   1.0000
   7.250   1.2107   0.02270   0.01409  -0.1018   0.0473   1.0000
   7.500   1.2257   0.02409   0.01549  -0.0998   0.0432   1.0000
   7.750   1.2415   0.02624   0.01766  -0.0979   0.0399   1.0000
   8.000   1.2616   0.02742   0.01896  -0.0966   0.0367   1.0000
   8.250   1.2824   0.02902   0.02064  -0.0955   0.0342   1.0000
   8.500   1.3060   0.03129   0.02297  -0.0949   0.0322   1.0000
   8.750   1.3342   0.03565   0.02758  -0.0952   0.0304   1.0000
   9.000   1.3507   0.03673   0.02896  -0.0932   0.0289   1.0000
   9.250   1.3685   0.03915   0.03171  -0.0916   0.0278   1.0000
   9.500   1.3834   0.04230   0.03525  -0.0897   0.0274   1.0000
   9.750   1.3934   0.04596   0.03934  -0.0872   0.0273   1.0000
  10.000   1.3978   0.05017   0.04400  -0.0843   0.0276   1.0000
  10.250   1.3960   0.05476   0.04900  -0.0810   0.0283   1.0000
  10.500   1.3889   0.05940   0.05400  -0.0776   0.0290   1.0000
  10.750   1.3765   0.06385   0.05874  -0.0739   0.0295   1.0000
  11.000   1.3864   0.06925   0.06429  -0.0730   0.0313   1.0000
  11.500   1.1902   0.07734   0.07368  -0.0565   0.0368   1.0000
  11.750   1.1597   0.08368   0.08022  -0.0569   0.0371   1.0000
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