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GOE 596 AIRFOIL (goe596-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 596 AIRFOIL (goe596-il)
Reynolds number: 50,000
Max Cl/Cd: 35.52 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe596-il-50000.txt
Download as CSV file: xf-goe596-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 596 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3608   0.11780   0.11059  -0.0275   1.0000   0.1827
  -9.250  -0.3358   0.11150   0.10425  -0.0257   1.0000   0.1907
  -9.000  -0.3448   0.11059   0.10344  -0.0266   1.0000   0.1976
  -8.750  -0.3366   0.10662   0.09953  -0.0262   1.0000   0.2027
  -8.500  -0.3332   0.10414   0.09711  -0.0257   1.0000   0.2116
  -8.250  -0.3628   0.10523   0.09843  -0.0266   1.0000   0.2149
  -8.000  -0.3300   0.09884   0.09198  -0.0246   1.0000   0.2263
  -7.750  -0.3609   0.09968   0.09304  -0.0243   1.0000   0.2306
  -7.500  -0.3342   0.09435   0.08767  -0.0226   1.0000   0.2428
  -7.250  -0.3687   0.09509   0.08868  -0.0215   1.0000   0.2465
  -7.000  -0.3521   0.09098   0.08459  -0.0190   1.0000   0.2607
  -6.750  -0.3466   0.08794   0.08162  -0.0167   1.0000   0.2723
  -6.500  -0.3806   0.08835   0.08224  -0.0161   1.0000   0.2787
  -6.250  -0.3732   0.08518   0.07914  -0.0127   1.0000   0.2935
  -6.000  -0.3700   0.08244   0.07648  -0.0096   1.0000   0.3070
  -5.750  -0.3743   0.08026   0.07441  -0.0068   1.0000   0.3198
  -5.500  -0.3821   0.07838   0.07263  -0.0040   1.0000   0.3340
  -5.250  -0.3882   0.07648   0.07083  -0.0010   1.0000   0.3505
  -5.000  -0.3936   0.07465   0.06909   0.0023   1.0000   0.3694
  -4.750  -0.4134   0.07404   0.06857   0.0038   1.0000   0.3922
  -4.500  -0.4051   0.07095   0.06559   0.0098   1.0000   0.4144
  -4.250   0.0867   0.04280   0.03607  -0.0349   1.0000   1.0000
  -4.000   0.0788   0.04234   0.03577  -0.0314   1.0000   0.9951
  -3.750   0.0226   0.04485   0.03857  -0.0170   1.0000   0.9652
  -3.500  -0.0329   0.04681   0.04081  -0.0041   1.0000   0.9340
  -3.250  -0.0909   0.04862   0.04289   0.0080   1.0000   0.9042
  -3.000  -0.1483   0.05007   0.04458   0.0190   1.0000   0.8780
  -2.750  -0.2002   0.05094   0.04567   0.0280   1.0000   0.8511
  -2.500  -0.2623   0.05191   0.04688   0.0383   1.0000   0.8297
  -2.250  -0.2270   0.04313   0.03539  -0.0345   0.9962   0.2117
  -2.000  -0.1705   0.04003   0.03139  -0.0408   0.9864   0.1800
  -1.750  -0.1252   0.03808   0.02895  -0.0449   0.9761   0.1729
  -1.500  -0.0791   0.03674   0.02693  -0.0486   0.9655   0.1656
  -1.250  -0.0340   0.03552   0.02535  -0.0521   0.9553   0.1625
  -1.000   0.0058   0.03466   0.02416  -0.0545   0.9441   0.1617
  -0.750   0.0439   0.03416   0.02333  -0.0567   0.9327   0.1658
  -0.500   0.0838   0.03363   0.02270  -0.0590   0.9218   0.1725
  -0.250   0.1327   0.03329   0.02213  -0.0626   0.9112   0.1808
   0.000   0.1665   0.03302   0.02186  -0.0638   0.8990   0.1932
   0.250   0.2021   0.03276   0.02170  -0.0654   0.8872   0.2206
   0.500   0.2724   0.02981   0.02083  -0.0716   0.8791   1.0000
   0.750   0.2998   0.03045   0.02104  -0.0718   0.8657   1.0000
   1.000   0.3276   0.03114   0.02145  -0.0723   0.8526   1.0000
   1.250   0.3575   0.03182   0.02192  -0.0731   0.8400   1.0000
   1.500   0.3931   0.03245   0.02236  -0.0747   0.8284   1.0000
   1.750   0.4314   0.03297   0.02274  -0.0765   0.8168   1.0000
   2.000   0.4518   0.03381   0.02348  -0.0759   0.8036   1.0000
   2.250   0.4752   0.03463   0.02423  -0.0757   0.7909   1.0000
   2.500   0.5042   0.03535   0.02488  -0.0761   0.7788   1.0000
   2.750   0.5520   0.03555   0.02504  -0.0788   0.7687   1.0000
   3.000   0.5665   0.03663   0.02609  -0.0774   0.7552   1.0000
   3.250   0.5835   0.03771   0.02715  -0.0764   0.7422   1.0000
   3.500   0.6043   0.03873   0.02816  -0.0758   0.7298   1.0000
   3.750   0.6377   0.03931   0.02877  -0.0765   0.7189   1.0000
   4.000   0.6702   0.03988   0.02937  -0.0770   0.7077   1.0000
   4.250   0.6788   0.04145   0.03095  -0.0752   0.6946   1.0000
   4.500   0.6904   0.04299   0.03251  -0.0738   0.6822   1.0000
   4.750   0.7136   0.04406   0.03365  -0.0734   0.6710   1.0000
   5.000   0.7583   0.04399   0.03367  -0.0746   0.6608   1.0000
   5.250   0.7566   0.04631   0.03602  -0.0722   0.6475   1.0000
   5.500   0.7648   0.04812   0.03786  -0.0705   0.6342   1.0000
   5.750   0.7818   0.04942   0.03925  -0.0694   0.6209   1.0000
   6.000   0.8085   0.05008   0.04001  -0.0687   0.6079   1.0000
   6.250   0.8807   0.04760   0.03777  -0.0701   0.5972   1.0000
   6.500   0.8758   0.05036   0.04059  -0.0677   0.5828   1.0000
   6.750   0.8648   0.05370   0.04396  -0.0653   0.5690   1.0000
   7.000   0.8628   0.05656   0.04687  -0.0637   0.5556   1.0000
   7.250   0.8719   0.05868   0.04909  -0.0625   0.5432   1.0000
   7.500   0.9063   0.05877   0.04937  -0.0616   0.5313   1.0000
   7.750   0.9346   0.05925   0.05006  -0.0606   0.5191   1.0000
   8.000   0.9082   0.06457   0.05536  -0.0592   0.5054   1.0000
   8.250   0.8971   0.06869   0.05951  -0.0583   0.4927   1.0000
   8.500   0.9010   0.07158   0.06251  -0.0575   0.4807   1.0000
   8.750   0.9236   0.07282   0.06392  -0.0565   0.4687   1.0000
   9.000   0.9339   0.07441   0.06565  -0.0550   0.4522   1.0000
   9.250   1.2207   0.03437   0.02595  -0.0424   0.3249   1.0000
   9.500   1.2069   0.03542   0.02657  -0.0361   0.2674   1.0000
   9.750   1.1923   0.03738   0.02803  -0.0306   0.2250   1.0000
  10.000   1.1868   0.03966   0.02993  -0.0268   0.1955   1.0000
  10.250   1.1975   0.04191   0.03175  -0.0247   0.1733   1.0000
  10.500   1.2161   0.04424   0.03403  -0.0235   0.1565   1.0000
  10.750   1.2419   0.04662   0.03636  -0.0231   0.1430   1.0000
  11.000   1.2820   0.04951   0.03917  -0.0243   0.1317   1.0000
  11.250   1.2851   0.05214   0.04225  -0.0219   0.1269   1.0000
  11.500   1.3041   0.05506   0.04533  -0.0212   0.1212   1.0000
  11.750   1.3219   0.05877   0.04922  -0.0208   0.1174   1.0000
  12.000   1.3123   0.06199   0.05284  -0.0178   0.1160   1.0000
  12.250   1.2990   0.06549   0.05669  -0.0151   0.1147   1.0000
  12.500   1.2823   0.06937   0.06088  -0.0131   0.1139   1.0000
  12.750   1.2612   0.07380   0.06560  -0.0119   0.1137   1.0000
  13.000   1.2350   0.07901   0.07108  -0.0116   0.1142   1.0000
  13.250   1.2044   0.08520   0.07751  -0.0127   0.1151   1.0000
  13.500   1.1733   0.09243   0.08493  -0.0150   0.1164   1.0000
  13.750   1.1439   0.10042   0.09305  -0.0183   0.1177   1.0000
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