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GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il)
Reynolds number: 50,000
Max Cl/Cd: 43.68 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe804-il-50000.txt
Download as CSV file: xf-goe804-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.4019   0.11505   0.10869  -0.0174   1.0000   0.1178
  -6.750  -0.4148   0.11494   0.10869  -0.0171   1.0000   0.1192
  -6.500  -0.4225   0.11491   0.10877  -0.0209   1.0000   0.1199
  -6.250  -0.4090   0.10780   0.10165  -0.0144   1.0000   0.1244
  -6.000  -0.4082   0.10533   0.09922  -0.0138   1.0000   0.1283
  -5.750  -0.4096   0.10367   0.09763  -0.0160   1.0000   0.1324
  -5.500  -0.4067   0.10163   0.09567  -0.0214   1.0000   0.1349
  -5.250  -0.4027   0.09732   0.09138  -0.0159   1.0000   0.1391
  -5.000  -0.3965   0.09473   0.08882  -0.0179   1.0000   0.1457
  -4.750  -0.3864   0.09167   0.08578  -0.0228   1.0000   0.1503
  -4.500  -0.3812   0.08835   0.08246  -0.0202   1.0000   0.1567
  -4.250  -0.3638   0.08510   0.07920  -0.0268   1.0000   0.1649
  -4.000  -0.3402   0.08207   0.07611  -0.0340   1.0000   0.1779
  -3.750  -0.3411   0.07855   0.07267  -0.0278   1.0000   0.1852
  -3.500  -0.3235   0.07528   0.06938  -0.0308   1.0000   0.2008
  -3.250  -0.2959   0.07171   0.06575  -0.0375   1.0000   0.2218
  -3.000  -0.2809   0.06844   0.06249  -0.0377   1.0000   0.2381
  -2.750  -0.2569   0.06518   0.05918  -0.0412   1.0000   0.2657
  -2.500  -0.2310   0.06244   0.05636  -0.0446   1.0000   0.3077
  -1.000   0.1427   0.03874   0.02978  -0.1082   1.0000   0.1973
  -0.750   0.1913   0.03693   0.02731  -0.1129   1.0000   0.1942
  -0.500   0.2328   0.03567   0.02547  -0.1159   1.0000   0.1926
  -0.250   0.2668   0.03487   0.02433  -0.1177   1.0000   0.2054
   0.000   0.2997   0.03411   0.02335  -0.1191   1.0000   0.2114
   0.250   0.3289   0.03375   0.02279  -0.1198   1.0000   0.2271
   0.500   0.3550   0.03352   0.02237  -0.1196   1.0000   0.2411
   0.750   0.3810   0.03337   0.02210  -0.1195   1.0000   0.2572
   1.000   0.4099   0.03327   0.02206  -0.1201   1.0000   0.2920
   1.250   0.4450   0.03156   0.02237  -0.1212   1.0000   0.7658
   1.500   0.4569   0.03207   0.02229  -0.1186   1.0000   1.0000
   1.750   0.4784   0.03295   0.02285  -0.1183   1.0000   1.0000
   2.000   0.4991   0.03388   0.02358  -0.1181   1.0000   1.0000
   2.250   0.5193   0.03486   0.02443  -0.1180   1.0000   1.0000
   2.500   0.5391   0.03590   0.02538  -0.1178   1.0000   1.0000
   2.750   0.5583   0.03699   0.02643  -0.1177   1.0000   1.0000
   3.000   0.5771   0.03815   0.02757  -0.1176   1.0000   1.0000
   3.250   0.5954   0.03939   0.02882  -0.1176   1.0000   1.0000
   3.500   0.6131   0.04071   0.03015  -0.1175   1.0000   1.0000
   3.750   0.6301   0.04212   0.03160  -0.1176   1.0000   1.0000
   4.000   0.6465   0.04364   0.03319  -0.1176   1.0000   1.0000
   4.250   0.6755   0.04558   0.03524  -0.1204   0.9906   1.0000
   4.500   0.7397   0.04757   0.03744  -0.1285   0.9563   1.0000
   4.750   0.8001   0.04854   0.03861  -0.1348   0.9233   1.0000
   5.000   0.8528   0.04907   0.03942  -0.1392   0.8951   1.0000
   5.250   0.8918   0.04968   0.04028  -0.1415   0.8709   1.0000
   5.500   0.9386   0.05000   0.04090  -0.1445   0.8490   1.0000
   5.750   0.9833   0.04995   0.04124  -0.1468   0.8253   1.0000
   6.000   1.0329   0.04893   0.04065  -0.1485   0.7979   1.0000
   6.250   1.1257   0.04157   0.03401  -0.1493   0.7519   1.0000
   6.500   1.1885   0.03508   0.02826  -0.1458   0.7046   1.0000
   6.750   1.2488   0.02859   0.02080  -0.1373   0.4349   1.0000
   7.000   1.2347   0.03307   0.02324  -0.1301   0.2576   1.0000
   7.250   1.2696   0.03700   0.02631  -0.1304   0.1706   1.0000
   7.500   1.3295   0.04052   0.02949  -0.1344   0.1311   1.0000
   7.750   1.3807   0.04450   0.03343  -0.1375   0.1121   1.0000
   8.000   1.4204   0.04904   0.03843  -0.1384   0.1052   1.0000
   8.250   1.4454   0.05269   0.04244  -0.1376   0.0982   1.0000
   8.500   1.4711   0.05818   0.04817  -0.1373   0.0950   1.0000
   8.750   1.4853   0.06290   0.05348  -0.1348   0.0950   1.0000
   9.000   1.4969   0.06795   0.05908  -0.1323   0.0955   1.0000
   9.250   1.4909   0.07143   0.06339  -0.1271   0.0969   1.0000
   9.500   1.4748   0.07613   0.06889  -0.1215   0.0998   1.0000
   9.750   1.4594   0.08121   0.07449  -0.1171   0.1019   1.0000
  10.000   1.4426   0.08624   0.07990  -0.1132   0.1039   1.0000
  10.250   1.4249   0.09107   0.08501  -0.1095   0.1056   1.0000
  10.500   1.4066   0.09599   0.09014  -0.1064   0.1068   1.0000
  10.750   1.3982   0.10180   0.09608  -0.1048   0.1082   1.0000
  11.000   1.2114   0.10380   0.09885  -0.0882   0.1108   1.0000
  11.250   1.1392   0.11166   0.10690  -0.0903   0.1124   1.0000
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