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GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 408 AIRFOIL (goe408-il)
Reynolds number: 50,000
Max Cl/Cd: 35.77 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe408-il-50000.txt
Download as CSV file: xf-goe408-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 408 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3874   0.11618   0.10905  -0.0202   1.0000   0.1216
  -8.750  -0.3958   0.11524   0.10822  -0.0217   1.0000   0.1240
  -8.500  -0.4105   0.11498   0.10811  -0.0232   1.0000   0.1249
  -8.250  -0.3831   0.10737   0.10044  -0.0203   1.0000   0.1335
  -8.000  -0.3902   0.10575   0.09894  -0.0208   1.0000   0.1374
  -7.750  -0.4062   0.10516   0.09849  -0.0213   1.0000   0.1389
  -7.500  -0.3933   0.09992   0.09329  -0.0198   1.0000   0.1435
  -7.250  -0.3940   0.09723   0.09066  -0.0188   1.0000   0.1496
  -7.000  -0.4065   0.09626   0.08982  -0.0215   1.0000   0.1536
  -6.750  -0.3973   0.09157   0.08519  -0.0190   1.0000   0.1583
  -6.500  -0.3975   0.08903   0.08271  -0.0191   1.0000   0.1664
  -6.250  -0.3983   0.08594   0.07970  -0.0193   1.0000   0.1718
  -6.000  -0.3957   0.08329   0.07709  -0.0187   1.0000   0.1816
  -5.750  -0.3923   0.07987   0.07373  -0.0172   1.0000   0.1903
  -5.500  -0.3923   0.07720   0.07110  -0.0173   1.0000   0.2019
  -5.250  -0.3907   0.07451   0.06846  -0.0165   1.0000   0.2160
  -5.000  -0.3880   0.07152   0.06554  -0.0142   1.0000   0.2327
  -4.750   0.0006   0.04809   0.04090  -0.0280   1.0000   1.0000
  -4.500   0.0098   0.04613   0.03900  -0.0283   1.0000   1.0000
  -4.250   0.0188   0.04421   0.03713  -0.0286   1.0000   1.0000
  -4.000  -0.1674   0.05129   0.04504   0.0123   1.0000   0.8548
  -3.750  -0.2123   0.05120   0.04523   0.0201   1.0000   0.8113
  -3.500  -0.2525   0.05065   0.04495   0.0270   1.0000   0.7821
  -3.250  -0.2814   0.04965   0.04416   0.0334   1.0000   0.7781
  -3.000  -0.4151   0.05302   0.04782   0.0260   1.0000   0.5310
  -2.750  -0.4231   0.05096   0.04588   0.0337   1.0000   0.5776
  -2.500  -0.4278   0.04853   0.04357   0.0417   1.0000   0.6213
  -2.250  -0.4317   0.04636   0.04148   0.0469   1.0000   0.6526
  -2.000  -0.4324   0.04394   0.03912   0.0518   1.0000   0.6808
  -1.750  -0.4289   0.04172   0.03692   0.0535   1.0000   0.6954
  -1.500  -0.4207   0.03947   0.03464   0.0538   1.0000   0.7045
  -1.250  -0.3845   0.03739   0.03228   0.0440   1.0000   0.6730
  -1.000  -0.2122   0.03739   0.02918  -0.0018   1.0000   0.3039
  -0.750  -0.1841   0.03630   0.02746  -0.0021   1.0000   0.2574
  -0.500  -0.1606   0.03562   0.02620  -0.0014   1.0000   0.2281
  -0.250  -0.1406   0.03487   0.02508  -0.0004   1.0000   0.2128
   0.000  -0.0981   0.03416   0.02408  -0.0038   0.9908   0.2089
   0.250  -0.0442   0.03400   0.02332  -0.0088   0.9770   0.1998
   0.500   0.0101   0.03360   0.02260  -0.0142   0.9632   0.1955
   0.750   0.0729   0.03326   0.02186  -0.0212   0.9493   0.1961
   1.000   0.1411   0.03285   0.02128  -0.0296   0.9351   0.2056
   1.250   0.2027   0.03263   0.02092  -0.0363   0.9210   0.2123
   1.500   0.2599   0.03237   0.02069  -0.0423   0.9069   0.2249
   1.750   0.3177   0.03196   0.02056  -0.0486   0.8925   0.2639
   2.000   0.4459   0.03029   0.02013  -0.0678   0.8822   1.0000
   2.250   0.4914   0.03056   0.02015  -0.0711   0.8665   1.0000
   2.500   0.5305   0.03088   0.02036  -0.0733   0.8500   1.0000
   2.750   0.5683   0.03118   0.02060  -0.0751   0.8335   1.0000
   3.000   0.6083   0.03138   0.02078  -0.0772   0.8177   1.0000
   3.250   0.6502   0.03148   0.02091  -0.0794   0.8021   1.0000
   3.500   0.6931   0.03156   0.02104  -0.0817   0.7865   1.0000
   3.750   0.7355   0.03164   0.02118  -0.0838   0.7702   1.0000
   4.000   0.7758   0.03164   0.02130  -0.0853   0.7534   1.0000
   4.250   0.8223   0.03126   0.02103  -0.0872   0.7355   1.0000
   4.500   0.8750   0.03043   0.02031  -0.0895   0.7154   1.0000
   4.750   0.8982   0.03078   0.02078  -0.0877   0.6931   1.0000
   5.000   0.9432   0.03022   0.02031  -0.0887   0.6719   1.0000
   5.250   0.9613   0.03081   0.02100  -0.0863   0.6501   1.0000
   5.500   0.9936   0.03077   0.02109  -0.0856   0.6284   1.0000
   5.750   1.0158   0.03118   0.02161  -0.0836   0.6064   1.0000
   6.000   1.0437   0.03131   0.02184  -0.0823   0.5835   1.0000
   6.250   1.0640   0.03180   0.02245  -0.0800   0.5601   1.0000
   6.500   1.0949   0.03179   0.02252  -0.0790   0.5355   1.0000
   6.750   1.1130   0.03239   0.02323  -0.0764   0.5100   1.0000
   7.000   1.1327   0.03312   0.02407  -0.0741   0.4857   1.0000
   7.250   1.1580   0.03346   0.02443  -0.0724   0.4597   1.0000
   7.500   1.1805   0.03355   0.02447  -0.0701   0.4313   1.0000
   7.750   1.1997   0.03364   0.02455  -0.0674   0.4023   1.0000
   8.000   1.2123   0.03405   0.02504  -0.0639   0.3748   1.0000
   8.250   1.2241   0.03429   0.02528  -0.0602   0.3456   1.0000
   8.500   1.2339   0.03450   0.02540  -0.0562   0.3134   1.0000
   8.750   1.2323   0.03504   0.02593  -0.0505   0.2769   1.0000
   9.000   1.2263   0.03603   0.02661  -0.0443   0.2336   1.0000
   9.250   1.2216   0.03798   0.02820  -0.0389   0.1928   1.0000
   9.500   1.2234   0.04042   0.03037  -0.0348   0.1611   1.0000
   9.750   1.2321   0.04302   0.03283  -0.0320   0.1387   1.0000
  10.000   1.2460   0.04593   0.03583  -0.0299   0.1236   1.0000
  10.250   1.2603   0.04870   0.03861  -0.0281   0.1127   1.0000
  10.500   1.2668   0.05156   0.04182  -0.0253   0.1053   1.0000
  10.750   1.2833   0.05537   0.04574  -0.0242   0.1003   1.0000
  11.000   1.2760   0.05878   0.04966  -0.0201   0.0981   1.0000
  11.250   1.2667   0.06218   0.05344  -0.0161   0.0965   1.0000
  11.500   1.2525   0.06549   0.05707  -0.0121   0.0952   1.0000
  11.750   1.2379   0.06876   0.06057  -0.0086   0.0935   1.0000
  12.000   1.2139   0.07299   0.06512  -0.0057   0.0944   1.0000
  12.250   1.1871   0.07770   0.07009  -0.0042   0.0954   1.0000
  12.500   1.1563   0.08340   0.07601  -0.0041   0.0964   1.0000
  12.750   1.1284   0.08980   0.08257  -0.0056   0.0982   1.0000
  13.000   1.1025   0.09676   0.08964  -0.0080   0.0996   1.0000
  13.250   1.0820   0.10400   0.09694  -0.0107   0.1008   1.0000
  13.500   0.9808   0.12965   0.12252  -0.0295   0.1159   1.0000
  13.750   0.9425   0.14600   0.13869  -0.0393   0.1301   1.0000
  14.000   0.9396   0.15208   0.14476  -0.0412   0.1293   1.0000
  14.250   0.9432   0.15726   0.14995  -0.0419   0.1284   1.0000
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