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GOE 565 AIRFOIL (goe565-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 565 AIRFOIL (goe565-il)
Reynolds number: 200,000
Max Cl/Cd: 69.05 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe565-il-200000-n5.txt
Download as CSV file: xf-goe565-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 565 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4585   0.08820   0.08454  -0.0334   1.0000   0.0181
  -9.250  -0.4653   0.08363   0.08003  -0.0350   1.0000   0.0184
  -9.000  -0.4748   0.07905   0.07551  -0.0365   1.0000   0.0185
  -8.750  -0.4901   0.07440   0.07095  -0.0376   1.0000   0.0186
  -8.500  -0.5114   0.06990   0.06656  -0.0384   1.0000   0.0186
  -8.250  -0.5325   0.06296   0.05968  -0.0427   1.0000   0.0184
  -8.000  -0.5791   0.04545   0.04189  -0.0522   1.0000   0.0180
  -7.750  -0.5950   0.02914   0.02420  -0.0578   0.9965   0.0194
  -7.500  -0.5718   0.02449   0.01872  -0.0595   0.9930   0.0216
  -7.250  -0.5402   0.02479   0.01905  -0.0607   0.9900   0.0231
  -7.000  -0.5096   0.02356   0.01753  -0.0621   0.9872   0.0256
  -6.750  -0.4814   0.02150   0.01496  -0.0629   0.9841   0.0286
  -6.500  -0.4507   0.02156   0.01504  -0.0639   0.9807   0.0309
  -6.250  -0.4190   0.02074   0.01391  -0.0650   0.9780   0.0346
  -6.000  -0.3895   0.01983   0.01277  -0.0658   0.9747   0.0375
  -5.750  -0.3593   0.01951   0.01242  -0.0667   0.9709   0.0404
  -5.500  -0.3268   0.01892   0.01162  -0.0678   0.9683   0.0438
  -5.250  -0.2958   0.01856   0.01103  -0.0685   0.9650   0.0461
  -5.000  -0.2679   0.01730   0.00969  -0.0690   0.9610   0.0492
  -4.750  -0.2353   0.01667   0.00899  -0.0701   0.9583   0.0517
  -4.500  -0.2013   0.01599   0.00820  -0.0715   0.9563   0.0536
  -4.250  -0.1747   0.01543   0.00756  -0.0713   0.9509   0.0551
  -4.000  -0.1420   0.01494   0.00696  -0.0723   0.9478   0.0573
  -3.750  -0.1075   0.01450   0.00645  -0.0737   0.9455   0.0590
  -3.500  -0.0802   0.01388   0.00583  -0.0737   0.9400   0.0611
  -3.250  -0.0481   0.01342   0.00536  -0.0745   0.9356   0.0636
  -3.000  -0.0137   0.01302   0.00493  -0.0758   0.9312   0.0663
  -2.750   0.0155   0.01269   0.00457  -0.0759   0.9234   0.0694
  -2.500   0.0501   0.01235   0.00421  -0.0772   0.9192   0.0739
  -2.250   0.0761   0.01213   0.00402  -0.0767   0.9112   0.0822
  -2.000   0.1081   0.01186   0.00377  -0.0775   0.9063   0.0981
  -1.750   0.1354   0.01156   0.00355  -0.0773   0.8991   0.1206
  -1.500   0.1643   0.01108   0.00336  -0.0776   0.8926   0.1876
  -1.250   0.1918   0.01072   0.00328  -0.0776   0.8854   0.2816
  -1.000   0.2201   0.01038   0.00317  -0.0775   0.8770   0.3477
  -0.750   0.2457   0.00997   0.00308  -0.0770   0.8652   0.4378
  -0.500   0.2709   0.00954   0.00303  -0.0762   0.8529   0.5546
  -0.250   0.2961   0.00919   0.00296  -0.0752   0.8402   0.6509
   0.000   0.3211   0.00881   0.00287  -0.0740   0.8271   0.7420
   0.500   0.4181   0.00836   0.00268  -0.0818   0.8003   1.0000
   0.750   0.4443   0.00840   0.00263  -0.0812   0.7852   1.0000
   1.000   0.4701   0.00846   0.00259  -0.0805   0.7681   1.0000
   1.250   0.4958   0.00853   0.00257  -0.0798   0.7502   1.0000
   1.500   0.5214   0.00863   0.00258  -0.0791   0.7316   1.0000
   1.750   0.5466   0.00875   0.00259  -0.0783   0.7109   1.0000
   2.000   0.5713   0.00889   0.00264  -0.0774   0.6871   1.0000
   2.250   0.5958   0.00904   0.00271  -0.0765   0.6621   1.0000
   2.500   0.6197   0.00922   0.00278  -0.0755   0.6320   1.0000
   2.750   0.6434   0.00943   0.00287  -0.0745   0.5996   1.0000
   3.000   0.6665   0.00968   0.00298  -0.0733   0.5671   1.0000
   3.250   0.6891   0.00998   0.00314  -0.0722   0.5344   1.0000
   3.500   0.7105   0.01037   0.00333  -0.0708   0.4938   1.0000
   3.750   0.7312   0.01082   0.00355  -0.0694   0.4456   1.0000
   4.000   0.7520   0.01128   0.00380  -0.0680   0.3983   1.0000
   4.250   0.7737   0.01171   0.00407  -0.0669   0.3619   1.0000
   4.500   0.7959   0.01212   0.00437  -0.0658   0.3303   1.0000
   4.750   0.8177   0.01258   0.00469  -0.0648   0.2960   1.0000
   5.000   0.8391   0.01309   0.00505  -0.0637   0.2580   1.0000
   5.250   0.8599   0.01366   0.00543  -0.0625   0.2163   1.0000
   5.500   0.8816   0.01417   0.00583  -0.0615   0.1910   1.0000
   5.750   0.9036   0.01466   0.00625  -0.0606   0.1741   1.0000
   6.000   0.9260   0.01511   0.00672  -0.0597   0.1599   1.0000
   6.250   0.9484   0.01557   0.00718  -0.0588   0.1440   1.0000
   6.500   0.9705   0.01605   0.00764  -0.0578   0.1171   1.0000
   6.750   0.9886   0.01696   0.00824  -0.0564   0.0761   1.0000
   7.000   1.0079   0.01776   0.00896  -0.0551   0.0563   1.0000
   7.250   1.0275   0.01851   0.00971  -0.0538   0.0472   1.0000
   7.500   1.0469   0.01926   0.01048  -0.0525   0.0420   1.0000
   7.750   1.0656   0.02007   0.01135  -0.0511   0.0381   1.0000
   8.000   1.0846   0.02080   0.01221  -0.0497   0.0351   1.0000
   8.250   1.1015   0.02171   0.01319  -0.0481   0.0318   1.0000
   8.500   1.1150   0.02290   0.01444  -0.0461   0.0290   1.0000
   8.750   1.1326   0.02369   0.01541  -0.0445   0.0270   1.0000
   9.000   1.1486   0.02460   0.01643  -0.0428   0.0246   1.0000
   9.250   1.1634   0.02555   0.01745  -0.0411   0.0225   1.0000
   9.500   1.1712   0.02708   0.01902  -0.0384   0.0209   1.0000
   9.750   1.1845   0.02809   0.02019  -0.0363   0.0199   1.0000
  10.000   1.1964   0.02924   0.02148  -0.0342   0.0187   1.0000
  10.250   1.2076   0.03038   0.02275  -0.0320   0.0175   1.0000
  10.500   1.2183   0.03143   0.02390  -0.0300   0.0163   1.0000
  10.750   1.2275   0.03259   0.02518  -0.0280   0.0155   1.0000
  11.000   1.2326   0.03427   0.02694  -0.0257   0.0148   1.0000
  11.250   1.2381   0.03618   0.02900  -0.0235   0.0143   1.0000
  11.500   1.2440   0.03807   0.03110  -0.0215   0.0138   1.0000
  11.750   1.2481   0.04015   0.03340  -0.0196   0.0134   1.0000
  12.000   1.2506   0.04234   0.03579  -0.0178   0.0129   1.0000
  12.250   1.2512   0.04472   0.03838  -0.0162   0.0126   1.0000
  12.500   1.2506   0.04709   0.04094  -0.0149   0.0121   1.0000
  12.750   1.2489   0.04963   0.04366  -0.0139   0.0117   1.0000
  13.000   1.2466   0.05228   0.04645  -0.0133   0.0114   1.0000
  13.250   1.2419   0.05545   0.04979  -0.0131   0.0112   1.0000
  13.500   1.2354   0.05906   0.05358  -0.0133   0.0110   1.0000
  13.750   1.2285   0.06286   0.05752  -0.0141   0.0108   1.0000
  14.000   1.2189   0.06733   0.06216  -0.0154   0.0107   1.0000
  14.250   1.2073   0.07241   0.06743  -0.0173   0.0105   1.0000
  14.500   1.1932   0.07830   0.07351  -0.0200   0.0104   1.0000
  14.750   1.1772   0.08501   0.08043  -0.0235   0.0104   1.0000
  15.000   1.1602   0.09236   0.08797  -0.0277   0.0104   1.0000
  15.250   1.1420   0.10050   0.09629  -0.0326   0.0104   1.0000
  15.500   1.1198   0.11021   0.10622  -0.0386   0.0106   1.0000
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