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GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il)
Reynolds number: 200,000
Max Cl/Cd: 107.09 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe804-il-200000.txt
Download as CSV file: xf-goe804-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4130   0.11755   0.11433  -0.0165   1.0000   0.0298
  -7.500  -0.4220   0.11648   0.11331  -0.0155   1.0000   0.0299
  -7.250  -0.4342   0.11567   0.11256  -0.0139   1.0000   0.0300
  -7.000  -0.4398   0.11400   0.11092  -0.0137   1.0000   0.0300
  -6.750  -0.4403   0.11171   0.10865  -0.0151   1.0000   0.0301
  -6.500  -0.4336   0.10869   0.10565  -0.0180   0.9994   0.0301
  -6.250  -0.4225   0.10165   0.09862  -0.0143   0.9970   0.0311
  -6.000  -0.3999   0.09770   0.09464  -0.0169   0.9928   0.0327
  -5.750  -0.3803   0.09416   0.09109  -0.0216   0.9879   0.0350
  -5.500  -0.3547   0.09001   0.08692  -0.0290   0.9828   0.0371
  -5.250  -0.3121   0.08568   0.08253  -0.0454   0.9758   0.0393
  -5.000  -0.2622   0.08055   0.07727  -0.0607   0.9708   0.0398
  -4.750  -0.2418   0.07422   0.07093  -0.0660   0.9661   0.0403
  -4.500  -0.2312   0.07034   0.06706  -0.0647   0.9632   0.0414
  -4.250  -0.2030   0.06685   0.06354  -0.0683   0.9608   0.0429
  -4.000  -0.1803   0.06349   0.06014  -0.0718   0.9553   0.0449
  -3.750  -0.0904   0.05769   0.05390  -0.0937   0.9524   0.0518
  -3.500  -0.0586   0.05137   0.04756  -0.0996   0.9508   0.0537
  -3.250  -0.0239   0.04845   0.04458  -0.1036   0.9489   0.0564
  -3.000   0.0611   0.04299   0.03838  -0.1195   0.9487   0.0660
  -2.750   0.0941   0.03963   0.03514  -0.1232   0.9478   0.0688
  -2.500   0.1364   0.03698   0.03217  -0.1281   0.9444   0.0811
  -2.250   0.2152   0.03055   0.02493  -0.1394   0.9481   0.0620
  -2.000   0.2693   0.02733   0.02101  -0.1452   0.9481   0.0628
  -1.750   0.3172   0.02554   0.01858  -0.1491   0.9476   0.0656
  -1.500   0.3425   0.02461   0.01764  -0.1494   0.9419   0.0729
  -1.250   0.3802   0.02402   0.01669  -0.1513   0.9391   0.0788
  -1.000   0.4194   0.02335   0.01601  -0.1539   0.9370   0.0885
  -0.750   0.4622   0.02274   0.01529  -0.1569   0.9352   0.0958
  -0.500   0.4888   0.02252   0.01507  -0.1568   0.9284   0.1036
  -0.250   0.5276   0.02199   0.01457  -0.1591   0.9250   0.1103
   0.000   0.5709   0.02153   0.01416  -0.1622   0.9226   0.1222
   0.250   0.6042   0.02117   0.01391  -0.1634   0.9166   0.1371
   0.500   0.6437   0.02069   0.01366  -0.1658   0.9120   0.1839
   0.750   0.6731   0.01876   0.01358  -0.1656   0.9095   1.0000
   1.000   0.7056   0.01876   0.01346  -0.1664   0.9038   1.0000
   1.250   0.7393   0.01868   0.01331  -0.1674   0.8980   1.0000
   1.500   0.7806   0.01843   0.01303  -0.1698   0.8953   1.0000
   1.750   0.8104   0.01836   0.01294  -0.1700   0.8879   1.0000
   2.000   0.8493   0.01802   0.01260  -0.1718   0.8833   1.0000
   2.250   0.8914   0.01762   0.01224  -0.1742   0.8809   1.0000
   2.500   0.9191   0.01750   0.01216  -0.1739   0.8726   1.0000
   2.750   0.9687   0.01637   0.01108  -0.1771   0.8683   1.0000
   3.000   1.0264   0.01491   0.00972  -0.1817   0.8655   1.0000
   3.250   1.0520   0.01461   0.00950  -0.1807   0.8545   1.0000
   3.500   1.0859   0.01400   0.00898  -0.1811   0.8442   1.0000
   3.750   1.1235   0.01333   0.00841  -0.1822   0.8339   1.0000
   4.000   1.1508   0.01294   0.00815  -0.1814   0.8184   1.0000
   4.250   1.1837   0.01239   0.00767  -0.1815   0.7963   1.0000
   4.500   1.2142   0.01200   0.00732  -0.1811   0.7607   1.0000
   4.750   1.2615   0.01178   0.00657  -0.1836   0.6490   1.0000
   5.000   1.2697   0.01302   0.00705  -0.1792   0.5177   1.0000
   5.500   1.2709   0.01622   0.00887  -0.1689   0.2878   1.0000
   5.750   1.2748   0.01801   0.01002  -0.1649   0.1901   1.0000
   6.000   1.2811   0.01996   0.01131  -0.1614   0.1002   1.0000
   6.250   1.2947   0.02131   0.01250  -0.1589   0.0732   1.0000
   6.500   1.3053   0.02293   0.01406  -0.1559   0.0584   1.0000
   6.750   1.3196   0.02425   0.01546  -0.1534   0.0496   1.0000
   7.000   1.3316   0.02640   0.01760  -0.1508   0.0441   1.0000
   7.250   1.3514   0.02756   0.01889  -0.1492   0.0399   1.0000
   7.500   1.3699   0.02887   0.02019  -0.1478   0.0357   1.0000
   7.750   1.4025   0.03163   0.02303  -0.1487   0.0328   1.0000
   8.000   1.4371   0.03381   0.02546  -0.1497   0.0308   1.0000
   8.250   1.4651   0.03582   0.02766  -0.1496   0.0287   1.0000
   8.500   1.4851   0.03740   0.02933  -0.1486   0.0266   1.0000
   8.750   1.5163   0.04149   0.03367  -0.1495   0.0254   1.0000
   9.000   1.5389   0.04643   0.03907  -0.1486   0.0251   1.0000
   9.250   1.5526   0.05038   0.04347  -0.1463   0.0252   1.0000
   9.500   1.5626   0.05332   0.04684  -0.1430   0.0257   1.0000
   9.750   1.5424   0.06268   0.05743  -0.1345   0.0303   1.0000
  10.000   1.5325   0.06811   0.06322  -0.1300   0.0316   1.0000
  10.250   1.4800   0.08276   0.07902  -0.1189   0.0539   1.0000
  10.500   1.4542   0.08647   0.08297  -0.1140   0.0533   1.0000
  10.750   1.4289   0.09073   0.08744  -0.1104   0.0528   1.0000
  11.000   1.4024   0.09575   0.09266  -0.1081   0.0527   1.0000
  11.250   1.3750   0.10161   0.09871  -0.1073   0.0531   1.0000
  11.500   1.3473   0.10820   0.10546  -0.1081   0.0535   1.0000
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