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GOE 10K AIRFOIL (goe10k-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 10K AIRFOIL (goe10k-il)
Reynolds number: 100,000
Max Cl/Cd: 27.78 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe10k-il-100000.txt
Download as CSV file: xf-goe10k-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 10K 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5449   0.10512   0.10016  -0.0120   1.0000   0.0551
  -8.250  -0.5503   0.10288   0.09801  -0.0147   1.0000   0.0554
  -8.000  -0.5529   0.10024   0.09544  -0.0184   1.0000   0.0555
  -7.750  -0.5365   0.09376   0.08893  -0.0118   1.0000   0.0590
  -7.500  -0.5370   0.09079   0.08601  -0.0124   1.0000   0.0606
  -7.250  -0.5358   0.08743   0.08271  -0.0152   1.0000   0.0630
  -7.000  -0.5321   0.08417   0.07945  -0.0215   1.0000   0.0645
  -6.750  -0.5266   0.07986   0.07516  -0.0241   1.0000   0.0656
  -6.500  -0.5201   0.07613   0.07145  -0.0213   1.0000   0.0688
  -6.250  -0.5090   0.07248   0.06772  -0.0263   1.0000   0.0731
  -6.000  -0.5006   0.06801   0.06323  -0.0274   1.0000   0.0756
  -5.750  -0.4899   0.06455   0.05974  -0.0273   1.0000   0.0804
  -5.500  -0.4754   0.06043   0.05545  -0.0305   1.0000   0.0856
  -5.250  -0.4550   0.05910   0.05362  -0.0335   1.0000   0.0963
  -5.000  -0.4497   0.05317   0.04807  -0.0304   1.0000   0.1009
  -4.750  -0.4328   0.04965   0.04434  -0.0316   1.0000   0.1129
  -4.500  -0.4165   0.04639   0.04092  -0.0316   1.0000   0.1259
  -4.250  -0.4001   0.04316   0.03755  -0.0312   1.0000   0.1401
  -4.000  -0.3835   0.04010   0.03441  -0.0304   1.0000   0.1568
  -3.750  -0.3666   0.03727   0.03145  -0.0296   1.0000   0.1845
  -3.500  -0.3510   0.03461   0.02877  -0.0281   1.0000   0.2175
  -3.250  -0.2949   0.02814   0.02046  -0.0293   1.0000   0.0756
  -3.000  -0.2659   0.02493   0.01639  -0.0273   1.0000   0.0551
  -2.750  -0.2410   0.02232   0.01341  -0.0261   1.0000   0.0542
  -2.500  -0.2148   0.01999   0.01069  -0.0249   1.0000   0.0528
  -2.250  -0.1885   0.01819   0.00852  -0.0236   1.0000   0.0565
  -2.000  -0.1633   0.01650   0.00680  -0.0225   1.0000   0.0665
  -1.750  -0.1401   0.01505   0.00551  -0.0213   1.0000   0.0930
  -1.500  -0.0810   0.01073   0.00387  -0.0268   1.0000   1.0000
  -1.250  -0.0586   0.01076   0.00352  -0.0257   1.0000   1.0000
  -1.000  -0.0362   0.01080   0.00327  -0.0246   1.0000   1.0000
  -0.750  -0.0139   0.01086   0.00309  -0.0236   1.0000   1.0000
  -0.500   0.0085   0.01093   0.00293  -0.0227   1.0000   1.0000
  -0.250   0.0307   0.01101   0.00287  -0.0217   1.0000   1.0000
   0.000   0.0529   0.01111   0.00286  -0.0208   1.0000   1.0000
   0.250   0.0751   0.01122   0.00287  -0.0198   1.0000   1.0000
   0.500   0.0973   0.01135   0.00294  -0.0190   1.0000   1.0000
   0.750   0.1194   0.01149   0.00305  -0.0181   1.0000   1.0000
   1.000   0.1415   0.01164   0.00321  -0.0172   1.0000   1.0000
   1.250   0.1634   0.01181   0.00341  -0.0164   1.0000   1.0000
   1.500   0.1853   0.01200   0.00364  -0.0155   1.0000   1.0000
   1.750   0.2071   0.01220   0.00393  -0.0147   1.0000   1.0000
   2.000   0.2287   0.01243   0.00429  -0.0138   1.0000   1.0000
   2.250   0.2503   0.01267   0.00468  -0.0130   1.0000   1.0000
   2.500   0.2716   0.01295   0.00512  -0.0122   1.0000   1.0000
   2.750   0.2928   0.01324   0.00566  -0.0114   1.0000   1.0000
   3.000   0.3138   0.01357   0.00624  -0.0106   1.0000   1.0000
   3.250   0.5075   0.01827   0.00801  -0.0375   0.0560   1.0000
   3.500   0.5335   0.02010   0.00995  -0.0362   0.0497   1.0000
   3.750   0.5607   0.02260   0.01255  -0.0354   0.0449   1.0000
   4.000   0.5887   0.02566   0.01590  -0.0344   0.0457   1.0000
   4.250   0.6170   0.02795   0.01897  -0.0320   0.0520   1.0000
   4.500   0.6418   0.03181   0.02300  -0.0308   0.0574   1.0000
   5.250   0.7256   0.04518   0.03928  -0.0235   0.1758   1.0000
   5.500   0.7394   0.04866   0.04276  -0.0217   0.1560   1.0000
   6.250   0.7728   0.06009   0.05454  -0.0178   0.1134   1.0000
   6.500   0.7772   0.06316   0.05802  -0.0173   0.1026   1.0000
   6.750   0.7920   0.07126   0.06570  -0.0166   0.0982   1.0000
   7.000   0.7878   0.07135   0.06651  -0.0170   0.0906   1.0000
   7.250   0.8056   0.07934   0.07409  -0.0154   0.0854   1.0000
   7.500   0.7929   0.08029   0.07558  -0.0172   0.0832   1.0000
   7.750   0.7905   0.08422   0.07962  -0.0189   0.0796   1.0000
   8.000   0.8049   0.08988   0.08514  -0.0160   0.0750   1.0000
   8.250   0.7928   0.09333   0.08872  -0.0191   0.0745   1.0000
   8.500   0.7809   0.09710   0.09250  -0.0218   0.0740   1.0000
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