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GOE 9K AIRFOIL (goe09k-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 9K AIRFOIL (goe09k-il)
Reynolds number: 50,000
Max Cl/Cd: 20.11 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe09k-il-50000.txt
Download as CSV file: xf-goe09k-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 9K 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6318   0.11220   0.10558   0.0067   1.0000   0.1391
  -8.000  -0.6129   0.10535   0.09868   0.0095   1.0000   0.1508
  -7.750  -0.6230   0.10435   0.09782   0.0044   1.0000   0.1536
  -7.500  -0.6101   0.09869   0.09217   0.0073   1.0000   0.1657
  -7.250  -0.6046   0.09465   0.08819   0.0066   1.0000   0.1741
  -7.000  -0.6074   0.09304   0.08664  -0.0004   1.0000   0.1828
  -6.750  -0.5994   0.08875   0.08237   0.0000   1.0000   0.1974
  -6.500  -0.5932   0.08515   0.07880  -0.0016   1.0000   0.2129
  -6.250  -0.5828   0.08007   0.07379   0.0025   1.0000   0.2330
  -6.000  -0.5786   0.07761   0.07130  -0.0014   1.0000   0.2575
  -5.750  -0.5716   0.07379   0.06755   0.0003   1.0000   0.2880
  -5.500  -0.5625   0.06950   0.06335   0.0061   1.0000   0.3220
  -5.250  -0.4928   0.04999   0.04443   0.0133   1.0000   0.4092
  -4.750  -0.4253   0.05256   0.04617   0.0405   1.0000   0.8018
  -4.500  -0.3768   0.04703   0.04051   0.0356   1.0000   0.8678
  -4.250  -0.4068   0.04661   0.04032   0.0402   1.0000   0.8235
  -4.000  -0.4345   0.04591   0.03980   0.0434   1.0000   0.7793
  -3.750  -0.4051   0.04024   0.03306  -0.0190   1.0000   0.3132
  -3.500  -0.3305   0.03470   0.02557  -0.0292   1.0000   0.1358
  -3.250  -0.2979   0.03151   0.02162  -0.0289   1.0000   0.1112
  -3.000  -0.2672   0.02902   0.01834  -0.0280   1.0000   0.0989
  -2.750  -0.2398   0.02601   0.01506  -0.0271   1.0000   0.0939
  -2.500  -0.2109   0.02367   0.01223  -0.0259   1.0000   0.0903
  -2.250  -0.1822   0.02167   0.00983  -0.0248   1.0000   0.0973
  -2.000  -0.1540   0.01971   0.00769  -0.0235   1.0000   0.1102
  -1.750  -0.1273   0.01783   0.00584  -0.0224   1.0000   0.1527
  -1.500  -0.0853   0.01345   0.00360  -0.0230   1.0000   1.0000
  -1.250  -0.0611   0.01341   0.00292  -0.0221   1.0000   1.0000
  -1.000  -0.0372   0.01338   0.00234  -0.0212   1.0000   1.0000
  -0.750  -0.0133   0.01337   0.00199  -0.0204   1.0000   1.0000
  -0.500   0.0104   0.01338   0.00174  -0.0197   1.0000   1.0000
  -0.250   0.0341   0.01340   0.00158  -0.0189   1.0000   1.0000
   0.000   0.0578   0.01343   0.00146  -0.0182   1.0000   1.0000
   0.250   0.0814   0.01347   0.00144  -0.0175   1.0000   1.0000
   0.500   0.1050   0.01352   0.00150  -0.0168   1.0000   1.0000
   0.750   0.1284   0.01359   0.00165  -0.0160   1.0000   1.0000
   1.000   0.1519   0.01367   0.00184  -0.0153   1.0000   1.0000
   1.250   0.1752   0.01377   0.00211  -0.0146   1.0000   1.0000
   1.500   0.1986   0.01388   0.00246  -0.0138   1.0000   1.0000
   1.750   0.2219   0.01401   0.00301  -0.0131   1.0000   1.0000
   2.000   0.2452   0.01417   0.00361  -0.0122   1.0000   1.0000
   2.250   0.2685   0.01435   0.00433  -0.0114   1.0000   1.0000
   2.500   0.2924   0.01454   0.00543  -0.0102   1.0000   1.0000
   2.750   0.3960   0.02206   0.00988  -0.0201   0.0903   1.0000
   3.000   0.4290   0.02457   0.01253  -0.0194   0.0854   1.0000
   3.250   0.4597   0.02706   0.01539  -0.0184   0.0848   1.0000
   3.500   0.4886   0.02995   0.01863  -0.0173   0.0861   1.0000
   3.750   0.5188   0.03242   0.02193  -0.0158   0.0959   1.0000
   4.000   0.5481   0.03576   0.02586  -0.0145   0.1120   1.0000
   4.250   0.5817   0.03916   0.03026  -0.0135   0.1473   1.0000
   4.500   0.6282   0.04414   0.03653  -0.0162   0.2461   1.0000
   4.750   0.6679   0.05582   0.05008  -0.0721   0.6279   1.0000
   5.000   0.6303   0.05828   0.05231  -0.0742   0.6879   1.0000
   5.250   0.5884   0.05980   0.05360  -0.0737   0.7517   1.0000
   6.500   0.7559   0.08242   0.07647  -0.0461   0.3474   1.0000
   6.750   0.7665   0.08649   0.08051  -0.0408   0.3029   1.0000
   7.000   0.7702   0.09031   0.08429  -0.0389   0.2724   1.0000
   7.250   0.7813   0.09501   0.08894  -0.0353   0.2436   1.0000
   7.500   0.7787   0.09850   0.09239  -0.0370   0.2283   1.0000
   7.750   0.7801   0.10250   0.09635  -0.0376   0.2133   1.0000
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