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GOE 284 AIRFOIL (goe284-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 284 AIRFOIL (goe284-il)
Reynolds number: 100,000
Max Cl/Cd: 34.1 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe284-il-100000.txt
Download as CSV file: xf-goe284-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 284 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1306   0.10443   0.09966  -0.0663   0.9420   0.1489
  -9.500  -0.1184   0.10157   0.09675  -0.0677   0.9199   0.1543
  -9.250  -0.1704   0.09868   0.09388  -0.0767   0.8926   0.1597
  -9.000  -0.1278   0.09548   0.09058  -0.0697   0.8757   0.1622
  -8.750  -0.1132   0.09338   0.08842  -0.0674   0.8580   0.1660
  -8.250  -0.1412   0.08671   0.08168  -0.0732   0.8291   0.1772
  -8.000  -0.1128   0.08469   0.07959  -0.0694   0.8174   0.1806
  -7.750  -0.2138   0.06459   0.05907  -0.0944   0.8096   0.1441
  -7.500  -0.2048   0.06078   0.05522  -0.0943   0.8007   0.1456
  -7.250  -0.1963   0.05716   0.05148  -0.0948   0.7914   0.1467
  -7.000  -0.1883   0.05351   0.04762  -0.0951   0.7851   0.1484
  -6.750  -0.1801   0.04981   0.04371  -0.0964   0.7760   0.1515
  -6.500  -0.1772   0.04470   0.03801  -0.0976   0.7696   0.1564
  -6.250  -0.1630   0.04190   0.03486  -0.0976   0.7642   0.1622
  -6.000  -0.1387   0.04185   0.03491  -0.0972   0.7559   0.1689
  -5.750  -0.1237   0.03923   0.03156  -0.0974   0.7500   0.1751
  -5.500  -0.0978   0.03886   0.03146  -0.0967   0.7453   0.1822
  -5.250  -0.0765   0.03779   0.03020  -0.0969   0.7384   0.1882
  -5.000  -0.0547   0.03614   0.02812  -0.0971   0.7330   0.1911
  -4.750  -0.0306   0.03483   0.02635  -0.0970   0.7288   0.1928
  -4.500  -0.0060   0.03317   0.02451  -0.0970   0.7253   0.1948
  -4.250   0.0178   0.03239   0.02369  -0.0972   0.7195   0.1964
  -4.000   0.0431   0.03175   0.02298  -0.0972   0.7142   0.1988
  -3.750   0.0696   0.03102   0.02208  -0.0972   0.7100   0.2010
  -3.500   0.0971   0.03029   0.02111  -0.0971   0.7067   0.2028
  -3.250   0.1228   0.02994   0.02062  -0.0972   0.7028   0.2049
  -3.000   0.1472   0.02982   0.02038  -0.0973   0.6980   0.2076
  -2.750   0.1735   0.02959   0.01995  -0.0973   0.6935   0.2101
  -2.500   0.2009   0.02908   0.01933  -0.0972   0.6897   0.2125
  -2.250   0.2292   0.02864   0.01886  -0.0972   0.6868   0.2156
  -2.000   0.2539   0.02876   0.01901  -0.0971   0.6830   0.2195
  -1.750   0.2750   0.02918   0.01946  -0.0969   0.6776   0.2239
  -1.500   0.3004   0.02928   0.01948  -0.0968   0.6732   0.2288
  -1.250   0.3285   0.02896   0.01919  -0.0967   0.6697   0.2340
  -1.000   0.3582   0.02864   0.01887  -0.0965   0.6664   0.2409
  -0.750   0.3759   0.02938   0.01966  -0.0958   0.6597   0.2482
  -0.500   0.3982   0.02949   0.01992  -0.0952   0.6536   0.2577
  -0.250   0.4284   0.02903   0.01949  -0.0949   0.6494   0.2731
   0.000   0.4594   0.02845   0.01901  -0.0946   0.6460   0.2972
   0.250   0.4699   0.02951   0.02040  -0.0934   0.6384   0.3312
   0.500   0.4859   0.02857   0.02077  -0.0916   0.6330   0.5794
   0.750   0.5640   0.02718   0.02002  -0.0975   0.6290   1.0000
   1.000   0.5944   0.02706   0.01963  -0.0971   0.6256   1.0000
   1.250   0.5915   0.02900   0.02165  -0.0941   0.6163   1.0000
   1.500   0.6172   0.02912   0.02161  -0.0935   0.6111   1.0000
   1.750   0.6517   0.02873   0.02101  -0.0935   0.6075   1.0000
   2.000   0.6592   0.03017   0.02246  -0.0914   0.5997   1.0000
   2.250   0.6782   0.03075   0.02297  -0.0902   0.5926   1.0000
   2.500   0.7147   0.03021   0.02226  -0.0905   0.5888   1.0000
   2.750   0.7522   0.02976   0.02161  -0.0909   0.5856   1.0000
   3.000   0.7446   0.03204   0.02404  -0.0875   0.5735   1.0000
   3.250   0.7821   0.03143   0.02328  -0.0879   0.5695   1.0000
   3.500   0.8217   0.03081   0.02248  -0.0886   0.5663   1.0000
   3.750   0.8149   0.03301   0.02484  -0.0851   0.5539   1.0000
   4.000   0.8542   0.03227   0.02396  -0.0857   0.5499   1.0000
   4.250   0.8958   0.03151   0.02302  -0.0866   0.5466   1.0000
   4.500   0.8893   0.03358   0.02526  -0.0830   0.5338   1.0000
   4.750   0.9297   0.03279   0.02433  -0.0838   0.5299   1.0000
   5.000   0.9365   0.03416   0.02577  -0.0815   0.5203   1.0000
   5.250   0.9639   0.03415   0.02570  -0.0811   0.5137   1.0000
   5.500   1.0058   0.03329   0.02472  -0.0821   0.5099   1.0000
   5.750   1.0017   0.03522   0.02677  -0.0787   0.4984   1.0000
   6.000   1.0389   0.03457   0.02603  -0.0792   0.4934   1.0000
   6.250   1.0847   0.03353   0.02483  -0.0807   0.4901   1.0000
   6.500   1.0714   0.03587   0.02736  -0.0763   0.4779   1.0000
   6.750   1.1124   0.03504   0.02642  -0.0773   0.4738   1.0000
   7.000   1.1605   0.03403   0.02525  -0.0792   0.4708   1.0000
   7.250   1.1306   0.03726   0.02875  -0.0732   0.4585   1.0000
   7.500   1.1757   0.03630   0.02768  -0.0747   0.4552   1.0000
   7.750   1.1325   0.04044   0.03203  -0.0677   0.4442   1.0000
   8.000   1.1660   0.04012   0.03169  -0.0680   0.4401   1.0000
   8.250   1.2191   0.03884   0.03032  -0.0703   0.4377   1.0000
   8.500   1.0948   0.04955   0.04132  -0.0596   0.4221   1.0000
   8.750   1.1499   0.04707   0.03879  -0.0603   0.4213   1.0000
   9.000   1.2133   0.04439   0.03605  -0.0621   0.4204   1.0000
   9.250   1.2803   0.04196   0.03352  -0.0650   0.4184   1.0000
   9.500   0.6446   0.12627   0.11870  -0.0719   0.4419   1.0000
   9.750   0.6584   0.12874   0.12119  -0.0722   0.4400   1.0000
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