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GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 505 AIRFOIL (goe505-il)
Reynolds number: 50,000
Max Cl/Cd: 29.83 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe505-il-50000-n5.txt
Download as CSV file: xf-goe505-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 505 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2913   0.10938   0.10305  -0.0466   0.9662   0.0832
  -7.750  -0.2916   0.10609   0.09977  -0.0486   0.9614   0.0828
  -7.500  -0.2953   0.10302   0.09672  -0.0499   0.9561   0.0823
  -7.250  -0.3041   0.10014   0.09388  -0.0503   0.9496   0.0817
  -7.000  -0.3028   0.09637   0.09009  -0.0531   0.9446   0.0812
  -6.750  -0.3108   0.09318   0.08691  -0.0530   0.9374   0.0807
  -6.500  -0.3093   0.08886   0.08254  -0.0555   0.9314   0.0794
  -6.250  -0.3119   0.08463   0.07825  -0.0568   0.9248   0.0783
  -6.000  -0.3117   0.07969   0.07320  -0.0588   0.9180   0.0771
  -5.750  -0.3064   0.07370   0.06698  -0.0619   0.9125   0.0760
  -5.500  -0.3071   0.06824   0.06127  -0.0624   0.9052   0.0753
  -5.250  -0.2913   0.06428   0.05707  -0.0639   0.9003   0.0758
  -5.000  -0.2812   0.06232   0.05500  -0.0628   0.8938   0.0772
  -4.750  -0.2654   0.05952   0.05197  -0.0630   0.8879   0.0788
  -4.500  -0.2455   0.05591   0.04797  -0.0641   0.8833   0.0806
  -4.250  -0.2364   0.05282   0.04450  -0.0626   0.8758   0.0813
  -4.000  -0.2136   0.04932   0.04043  -0.0631   0.8710   0.0826
  -3.750  -0.1971   0.04683   0.03743  -0.0620   0.8644   0.0838
  -3.500  -0.1738   0.04446   0.03446  -0.0616   0.8584   0.0859
  -3.250  -0.1407   0.04296   0.03265  -0.0628   0.8540   0.0892
  -3.000  -0.1257   0.04239   0.03200  -0.0609   0.8446   0.0927
  -2.750  -0.0896   0.04108   0.03026  -0.0622   0.8395   0.0997
  -2.500  -0.0698   0.04034   0.02943  -0.0609   0.8298   0.1043
  -2.250  -0.0279   0.03920   0.02801  -0.0629   0.8236   0.1145
  -2.000  -0.0043   0.03865   0.02747  -0.0621   0.8120   0.1250
  -1.750   0.0346   0.03801   0.02670  -0.0635   0.8036   0.1471
  -1.500   0.0648   0.03772   0.02641  -0.0637   0.7931   0.1687
  -1.250   0.0861   0.03774   0.02638  -0.0624   0.7817   0.1957
  -1.000   0.1231   0.03737   0.02592  -0.0634   0.7746   0.2262
  -0.750   0.1452   0.03718   0.02566  -0.0624   0.7625   0.2425
  -0.500   0.1908   0.03642   0.02477  -0.0649   0.7571   0.2639
  -0.250   0.2108   0.03631   0.02458  -0.0635   0.7441   0.2793
   0.000   0.2350   0.03609   0.02431  -0.0628   0.7324   0.2958
   0.250   0.2748   0.03534   0.02355  -0.0642   0.7257   0.3175
   0.500   0.2947   0.03519   0.02339  -0.0627   0.7125   0.3355
   0.750   0.3174   0.03491   0.02311  -0.0617   0.6998   0.3558
   1.000   0.3442   0.03442   0.02263  -0.0611   0.6887   0.3800
   1.250   0.3762   0.03353   0.02182  -0.0611   0.6799   0.4111
   1.500   0.3965   0.03301   0.02147  -0.0596   0.6666   0.4454
   2.000   0.5356   0.03101   0.02047  -0.0745   0.6442   1.0000
   2.250   0.5651   0.03057   0.01981  -0.0739   0.6328   1.0000
   2.500   0.5885   0.03041   0.01946  -0.0726   0.6184   1.0000
   2.750   0.6137   0.03021   0.01908  -0.0716   0.6041   1.0000
   3.000   0.6404   0.03001   0.01869  -0.0708   0.5901   1.0000
   3.250   0.6688   0.02980   0.01828  -0.0703   0.5765   1.0000
   3.500   0.6991   0.02958   0.01786  -0.0700   0.5635   1.0000
   3.750   0.7312   0.02935   0.01741  -0.0701   0.5508   1.0000
   4.000   0.7549   0.02953   0.01743  -0.0692   0.5368   1.0000
   4.250   0.7775   0.02980   0.01755  -0.0682   0.5236   1.0000
   4.500   0.8019   0.03006   0.01766  -0.0675   0.5120   1.0000
   4.750   0.8328   0.03014   0.01754  -0.0677   0.5020   1.0000
   5.000   0.8498   0.03073   0.01807  -0.0661   0.4908   1.0000
   5.250   0.8739   0.03112   0.01835  -0.0655   0.4815   1.0000
   5.500   0.8976   0.03155   0.01868  -0.0649   0.4724   1.0000
   5.750   0.9181   0.03212   0.01921  -0.0639   0.4639   1.0000
   6.000   0.9428   0.03258   0.01960  -0.0635   0.4562   1.0000
   6.250   0.9635   0.03320   0.02018  -0.0626   0.4488   1.0000
   6.500   0.9844   0.03380   0.02076  -0.0617   0.4412   1.0000
   6.750   1.0089   0.03433   0.02125  -0.0613   0.4343   1.0000
   7.000   1.0232   0.03515   0.02212  -0.0596   0.4271   1.0000
   7.250   1.0567   0.03543   0.02229  -0.0605   0.4206   1.0000
   7.500   1.0596   0.03659   0.02359  -0.0572   0.4133   1.0000
   7.750   1.0848   0.03705   0.02400  -0.0570   0.4066   1.0000
   8.000   1.0958   0.03804   0.02506  -0.0549   0.4001   1.0000
   8.250   1.1088   0.03894   0.02602  -0.0531   0.3935   1.0000
   8.500   1.1411   0.03926   0.02629  -0.0538   0.3879   1.0000
   8.750   1.1351   0.04088   0.02810  -0.0498   0.3816   1.0000
   9.000   1.1517   0.04172   0.02899  -0.0486   0.3758   1.0000
   9.250   1.1794   0.04224   0.02949  -0.0487   0.3709   1.0000
   9.500   1.1677   0.04428   0.03177  -0.0444   0.3652   1.0000
   9.750   1.1794   0.04544   0.03301  -0.0428   0.3600   1.0000
  10.000   1.2144   0.04563   0.03318  -0.0437   0.3556   1.0000
  10.250   1.1903   0.04852   0.03633  -0.0387   0.3503   1.0000
  10.500   1.1839   0.05081   0.03877  -0.0358   0.3452   1.0000
  10.750   1.2062   0.05152   0.03954  -0.0353   0.3410   1.0000
  11.000   1.2117   0.05324   0.04139  -0.0336   0.3367   1.0000
  11.250   1.1476   0.05987   0.04827  -0.0278   0.3299   1.0000
  11.500   1.1563   0.06150   0.05001  -0.0266   0.3254   1.0000
  11.750   1.2006   0.06042   0.04896  -0.0272   0.3224   1.0000
  12.000   1.0332   0.07990   0.06867  -0.0231   0.3084   1.0000
  12.250   1.0621   0.07934   0.06818  -0.0222   0.3063   1.0000
  12.750   0.9654   0.10026   0.08925  -0.0253   0.2887   1.0000
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