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GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il)
Reynolds number: 100,000
Max Cl/Cd: 70.63 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe804-il-100000.txt
Download as CSV file: xf-goe804-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.4090   0.10842   0.10399  -0.0138   1.0000   0.0554
  -6.500  -0.4138   0.10652   0.10213  -0.0121   1.0000   0.0563
  -6.250  -0.4170   0.10441   0.10007  -0.0110   1.0000   0.0574
  -6.000  -0.4179   0.10213   0.09783  -0.0107   1.0000   0.0585
  -5.750  -0.4176   0.09969   0.09543  -0.0111   1.0000   0.0599
  -5.500  -0.4152   0.09710   0.09287  -0.0125   1.0000   0.0618
  -5.250  -0.4079   0.09454   0.09033  -0.0164   1.0000   0.0637
  -5.000  -0.3740   0.09193   0.08764  -0.0338   1.0000   0.0653
  -4.750  -0.3648   0.08717   0.08290  -0.0351   1.0000   0.0660
  -4.500  -0.3687   0.08351   0.07931  -0.0292   1.0000   0.0671
  -4.250  -0.3624   0.08047   0.07629  -0.0276   1.0000   0.0689
  -4.000  -0.3477   0.07736   0.07315  -0.0296   1.0000   0.0730
  -3.750  -0.2904   0.07193   0.06751  -0.0477   1.0000   0.0799
  -3.500  -0.2868   0.06892   0.06457  -0.0444   1.0000   0.0818
  -3.250  -0.2077   0.06447   0.05964  -0.0648   1.0000   0.0928
  -3.000  -0.2047   0.06046   0.05579  -0.0616   1.0000   0.0942
  -2.750  -0.1437   0.05704   0.05195  -0.0739   1.0000   0.1065
  -2.500  -0.1359   0.05335   0.04844  -0.0718   1.0000   0.1090
  -2.250  -0.0976   0.05023   0.04516  -0.0775   1.0000   0.1230
  -2.000  -0.0601   0.04738   0.04217  -0.0825   1.0000   0.1379
  -1.750  -0.0235   0.04482   0.03949  -0.0868   1.0000   0.1544
  -1.500   0.0181   0.04252   0.03698  -0.0922   1.0000   0.1808
  -1.000   0.1461   0.03543   0.02850  -0.1087   1.0000   0.1306
  -0.750   0.2012   0.03274   0.02505  -0.1141   1.0000   0.1150
  -0.500   0.2424   0.03141   0.02321  -0.1170   1.0000   0.1153
  -0.250   0.2764   0.03077   0.02224  -0.1187   1.0000   0.1239
   0.000   0.3068   0.03047   0.02174  -0.1198   1.0000   0.1304
   0.250   0.3516   0.03037   0.02151  -0.1234   0.9957   0.1427
   0.500   0.4033   0.03035   0.02142  -0.1281   0.9870   0.1556
   0.750   0.4497   0.03040   0.02150  -0.1320   0.9777   0.1735
   1.000   0.4964   0.03040   0.02160  -0.1358   0.9695   0.2005
   1.250   0.5318   0.02848   0.02168  -0.1371   0.9629   1.0000
   1.500   0.5687   0.02899   0.02179  -0.1389   0.9527   1.0000
   1.750   0.6066   0.02957   0.02221  -0.1412   0.9451   1.0000
   2.000   0.6431   0.03003   0.02258  -0.1433   0.9364   1.0000
   2.250   0.6768   0.03040   0.02291  -0.1448   0.9257   1.0000
   2.500   0.7142   0.03070   0.02319  -0.1467   0.9157   1.0000
   2.750   0.7606   0.03084   0.02332  -0.1501   0.9079   1.0000
   3.000   0.7921   0.03102   0.02354  -0.1509   0.8964   1.0000
   3.250   0.8254   0.03120   0.02380  -0.1520   0.8857   1.0000
   3.500   0.8739   0.03101   0.02370  -0.1554   0.8796   1.0000
   3.750   0.9061   0.03094   0.02373  -0.1560   0.8673   1.0000
   4.000   0.9412   0.03070   0.02366  -0.1568   0.8552   1.0000
   4.250   0.9805   0.03013   0.02324  -0.1580   0.8430   1.0000
   4.500   1.0269   0.02879   0.02209  -0.1597   0.8292   1.0000
   4.750   1.0822   0.02630   0.01988  -0.1615   0.8131   1.0000
   5.000   1.1284   0.02425   0.01810  -0.1623   0.7980   1.0000
   5.250   1.1649   0.02256   0.01666  -0.1614   0.7779   1.0000
   5.500   1.1986   0.02084   0.01520  -0.1597   0.7446   1.0000
   5.750   1.2713   0.01800   0.01214  -0.1634   0.6227   1.0000
   6.000   1.2828   0.02001   0.01250  -0.1590   0.3801   1.0000
   6.250   1.2717   0.02314   0.01424  -0.1524   0.2033   1.0000
   6.500   1.2747   0.02570   0.01603  -0.1483   0.1263   1.0000
   6.750   1.2824   0.02797   0.01815  -0.1448   0.1017   1.0000
   7.000   1.2966   0.03001   0.02008  -0.1425   0.0849   1.0000
   7.250   1.3215   0.03223   0.02227  -0.1417   0.0739   1.0000
   7.500   1.3574   0.03482   0.02486  -0.1430   0.0640   1.0000
   7.750   1.4095   0.03904   0.02899  -0.1471   0.0578   1.0000
   8.000   1.4375   0.04177   0.03223  -0.1464   0.0543   1.0000
   8.250   1.4623   0.04481   0.03573  -0.1454   0.0516   1.0000
   8.500   1.4843   0.04874   0.04018  -0.1437   0.0510   1.0000
   8.750   1.4998   0.05322   0.04526  -0.1412   0.0516   1.0000
   9.000   1.5089   0.05799   0.05060  -0.1380   0.0526   1.0000
   9.250   1.5121   0.06253   0.05564  -0.1343   0.0529   1.0000
   9.500   1.5110   0.06713   0.06070  -0.1304   0.0534   1.0000
   9.750   1.5055   0.07189   0.06588  -0.1263   0.0540   1.0000
  10.000   1.5025   0.07791   0.07216  -0.1234   0.0558   1.0000
  10.250   1.4037   0.07801   0.07295  -0.1057   0.0586   1.0000
  10.500   1.3268   0.08331   0.07896  -0.0959   0.0630   1.0000
  10.750   1.2920   0.08937   0.08529  -0.0928   0.0654   1.0000
  11.000   1.2641   0.09527   0.09138  -0.0910   0.0670   1.0000
  11.250   1.2330   0.10109   0.09738  -0.0901   0.0678   1.0000
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