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GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il)
Reynolds number: 1,000,000
Max Cl/Cd: 211.36 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe804-il-1000000.txt
Download as CSV file: xf-goe804-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 804 (EA 8) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1135   0.08333   0.08152  -0.0998   0.9696   0.0118
  -8.000  -0.1027   0.08028   0.07847  -0.1022   0.9663   0.0119
  -7.750  -0.0884   0.07649   0.07469  -0.1064   0.9642   0.0120
  -7.500  -0.0726   0.07269   0.07088  -0.1107   0.9626   0.0120
  -7.250  -0.0585   0.06840   0.06660  -0.1146   0.9615   0.0127
  -7.000  -0.0345   0.06524   0.06342  -0.1199   0.9608   0.0131
  -6.250   0.1044   0.01777   0.01484  -0.1931   0.9481   0.0119
  -6.000   0.1494   0.01166   0.00773  -0.2009   0.9477   0.0130
  -5.750   0.1729   0.01112   0.00708  -0.2003   0.9447   0.0136
  -5.500   0.2019   0.01058   0.00643  -0.2009   0.9429   0.0144
  -5.250   0.2332   0.00998   0.00570  -0.2019   0.9414   0.0155
  -5.000   0.2646   0.00974   0.00539  -0.2027   0.9399   0.0164
  -4.750   0.2993   0.00868   0.00415  -0.2046   0.9387   0.0185
  -4.500   0.3318   0.00836   0.00378  -0.2058   0.9374   0.0202
  -4.250   0.3646   0.00806   0.00342  -0.2069   0.9359   0.0220
  -4.000   0.3976   0.00759   0.00288  -0.2082   0.9338   0.0252
  -3.750   0.4233   0.00750   0.00280  -0.2077   0.9295   0.0283
  -3.500   0.4540   0.00724   0.00249  -0.2083   0.9262   0.0317
  -3.250   0.4853   0.00712   0.00239  -0.2090   0.9233   0.0366
  -3.000   0.5161   0.00717   0.00242  -0.2096   0.9205   0.0396
  -2.750   0.5435   0.00690   0.00215  -0.2096   0.9174   0.0447
  -2.500   0.5718   0.00682   0.00206  -0.2097   0.9143   0.0484
  -2.250   0.6009   0.00678   0.00201  -0.2100   0.9113   0.0513
  -2.000   0.6323   0.00660   0.00179  -0.2108   0.9086   0.0542
  -1.750   0.6613   0.00646   0.00165  -0.2112   0.9056   0.0585
  -1.500   0.6886   0.00637   0.00156  -0.2110   0.9015   0.0610
  -1.250   0.7173   0.00629   0.00146  -0.2112   0.8974   0.0639
  -1.000   0.7483   0.00621   0.00135  -0.2119   0.8936   0.0666
  -0.750   0.7749   0.00613   0.00132  -0.2116   0.8894   0.0753
  -0.500   0.8024   0.00606   0.00129  -0.2115   0.8839   0.0915
  -0.250   0.8314   0.00599   0.00124  -0.2117   0.8777   0.1101
   0.000   0.8578   0.00592   0.00123  -0.2114   0.8714   0.1274
   0.250   0.8874   0.00581   0.00125  -0.2118   0.8658   0.1929
   0.500   0.9144   0.00568   0.00128  -0.2117   0.8585   0.2606
   0.750   0.9477   0.00516   0.00143  -0.2135   0.8521   0.5858
   1.000   0.9745   0.00482   0.00165  -0.2133   0.8429   0.8407
   1.250   0.9988   0.00484   0.00171  -0.2123   0.8313   0.8782
   1.500   1.0221   0.00487   0.00175  -0.2111   0.8171   0.9012
   1.750   1.0441   0.00494   0.00177  -0.2096   0.7933   0.9192
   2.000   1.0628   0.00515   0.00182  -0.2074   0.7527   0.9329
   2.250   1.0763   0.00557   0.00197  -0.2041   0.6937   0.9487
   2.500   1.0891   0.00604   0.00219  -0.2007   0.6342   1.0000
   2.750   1.1072   0.00664   0.00248  -0.1987   0.5713   1.0000
   3.000   1.1204   0.00764   0.00293  -0.1959   0.4585   1.0000
   3.250   1.1398   0.00832   0.00330  -0.1943   0.3984   1.0000
   3.500   1.1578   0.00916   0.00371  -0.1926   0.3087   1.0000
   3.750   1.1755   0.01007   0.00421  -0.1908   0.2292   1.0000
   4.000   1.1986   0.01051   0.00452  -0.1900   0.2017   1.0000
   4.250   1.2201   0.01110   0.00486  -0.1889   0.1508   1.0000
   4.500   1.2393   0.01192   0.00537  -0.1874   0.0966   1.0000
   4.750   1.2608   0.01250   0.00579  -0.1864   0.0650   1.0000
   5.000   1.2843   0.01288   0.00613  -0.1856   0.0559   1.0000
   5.250   1.3075   0.01327   0.00650  -0.1848   0.0490   1.0000
   5.500   1.3311   0.01360   0.00684  -0.1841   0.0419   1.0000
   5.750   1.3531   0.01410   0.00725  -0.1830   0.0294   1.0000
   6.000   1.3748   0.01462   0.00774  -0.1819   0.0220   1.0000
   6.250   1.3954   0.01529   0.00841  -0.1805   0.0174   1.0000
   6.500   1.4176   0.01568   0.00884  -0.1796   0.0161   1.0000
   6.750   1.4385   0.01617   0.00934  -0.1783   0.0144   1.0000
   7.000   1.4561   0.01704   0.01028  -0.1763   0.0125   1.0000
   7.250   1.4753   0.01765   0.01096  -0.1747   0.0119   1.0000
   7.500   1.4946   0.01819   0.01155  -0.1732   0.0112   1.0000
   7.750   1.5132   0.01880   0.01223  -0.1715   0.0105   1.0000
   8.000   1.5314   0.01945   0.01292  -0.1699   0.0099   1.0000
   8.250   1.5489   0.02016   0.01367  -0.1681   0.0093   1.0000
   8.500   1.5570   0.02190   0.01556  -0.1646   0.0084   1.0000
   8.750   1.5744   0.02260   0.01634  -0.1628   0.0081   1.0000
   9.000   1.5912   0.02337   0.01718  -0.1610   0.0079   1.0000
   9.250   1.6067   0.02426   0.01815  -0.1590   0.0075   1.0000
   9.500   1.6212   0.02528   0.01926  -0.1569   0.0072   1.0000
   9.750   1.6356   0.02631   0.02039  -0.1547   0.0069   1.0000
  10.000   1.6493   0.02740   0.02156  -0.1526   0.0066   1.0000
  10.250   1.6620   0.02861   0.02287  -0.1503   0.0065   1.0000
  10.500   1.6745   0.02977   0.02411  -0.1482   0.0062   1.0000
  10.750   1.6847   0.03123   0.02567  -0.1457   0.0060   1.0000
  11.000   1.6900   0.03352   0.02813  -0.1426   0.0057   1.0000
  11.250   1.6857   0.03802   0.03300  -0.1384   0.0055   1.0000
  11.500   1.6945   0.03938   0.03450  -0.1360   0.0054   1.0000
  11.750   1.7021   0.04096   0.03621  -0.1336   0.0053   1.0000
  12.000   1.7097   0.04243   0.03782  -0.1313   0.0051   1.0000
  12.250   1.7133   0.04456   0.04011  -0.1287   0.0050   1.0000
  12.500   1.7161   0.04672   0.04242  -0.1262   0.0048   1.0000
  12.750   1.7150   0.04948   0.04536  -0.1235   0.0047   1.0000
  13.000   1.7101   0.05278   0.04889  -0.1208   0.0047   1.0000
  13.250   1.7073   0.05573   0.05200  -0.1186   0.0045   1.0000
  13.500   1.6941   0.06033   0.05684  -0.1160   0.0045   1.0000
  13.750   1.6885   0.06380   0.06047  -0.1144   0.0044   1.0000
  14.000   1.6743   0.06875   0.06564  -0.1130   0.0043   1.0000
  14.250   1.6570   0.07454   0.07165  -0.1122   0.0044   1.0000
  14.500   1.6391   0.08074   0.07807  -0.1123   0.0043   1.0000
  14.750   1.6236   0.08694   0.08445  -0.1133   0.0043   1.0000
  15.000   1.5990   0.09542   0.09317  -0.1158   0.0043   1.0000
  15.250   1.5714   0.10536   0.10335  -0.1200   0.0043   1.0000
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