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GOE 180 (MVA H.26) AIRFOIL (goe180-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 180 (MVA H.26) AIRFOIL (goe180-il)
Reynolds number: 50,000
Max Cl/Cd: 33.25 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe180-il-50000.txt
Download as CSV file: xf-goe180-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 180 (MVA H.26) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3496   0.10401   0.09720  -0.0204   1.0000   0.1760
  -7.750  -0.3522   0.10210   0.09539  -0.0205   1.0000   0.1828
  -7.500  -0.3741   0.10269   0.09619  -0.0229   1.0000   0.1855
  -7.250  -0.3490   0.09634   0.08978  -0.0192   1.0000   0.1935
  -7.000  -0.3619   0.09561   0.08922  -0.0211   1.0000   0.2001
  -6.750  -0.3513   0.09132   0.08498  -0.0188   1.0000   0.2067
  -6.500  -0.3606   0.09041   0.08419  -0.0217   1.0000   0.2159
  -6.250  -0.3492   0.08621   0.08005  -0.0180   1.0000   0.2263
  -5.750  -0.3542   0.08196   0.07599  -0.0203   1.0000   0.2483
  -5.500  -0.3530   0.07996   0.07405  -0.0211   1.0000   0.2628
  -5.250  -0.3454   0.07624   0.07040  -0.0162   1.0000   0.2753
  -5.000  -0.3436   0.07390   0.06812  -0.0161   1.0000   0.2919
  -4.750  -0.3409   0.07131   0.06560  -0.0156   1.0000   0.3095
  -4.500  -0.3366   0.06836   0.06271  -0.0121   1.0000   0.3271
  -4.250  -0.3338   0.06625   0.06066  -0.0113   1.0000   0.3553
  -3.750  -0.3317   0.06136   0.05598  -0.0013   1.0000   0.4199
  -3.000  -0.3427   0.05531   0.05031   0.0210   1.0000   0.5634
  -2.750  -0.3474   0.05335   0.04845   0.0286   1.0000   0.6124
  -2.500  -0.3498   0.05121   0.04641   0.0357   1.0000   0.6567
  -2.250  -0.0942   0.03941   0.03159  -0.0528   1.0000   0.2029
  -2.000  -0.0620   0.03705   0.02877  -0.0552   1.0000   0.1809
  -1.750  -0.0312   0.03532   0.02647  -0.0572   1.0000   0.1677
  -1.500  -0.0073   0.03416   0.02503  -0.0583   1.0000   0.1630
  -1.250   0.0446   0.03273   0.02309  -0.0638   0.9913   0.1619
  -1.000   0.1054   0.03155   0.02140  -0.0704   0.9770   0.1677
  -0.750   0.1622   0.03043   0.01994  -0.0761   0.9626   0.1735
  -0.500   0.2161   0.02960   0.01889  -0.0808   0.9482   0.1885
  -0.250   0.2673   0.02876   0.01811  -0.0851   0.9340   0.2287
   0.000   0.3083   0.02516   0.01673  -0.0862   0.9222   1.0000
   0.250   0.3543   0.02567   0.01659  -0.0897   0.9064   1.0000
   0.500   0.3964   0.02617   0.01674  -0.0927   0.8912   1.0000
   0.750   0.4356   0.02668   0.01699  -0.0952   0.8765   1.0000
   1.000   0.4724   0.02720   0.01732  -0.0972   0.8627   1.0000
   1.250   0.5083   0.02774   0.01770  -0.0990   0.8498   1.0000
   1.500   0.5450   0.02819   0.01803  -0.1007   0.8379   1.0000
   1.750   0.5826   0.02856   0.01830  -0.1023   0.8267   1.0000
   2.000   0.6089   0.02926   0.01894  -0.1024   0.8134   1.0000
   2.250   0.6393   0.02966   0.01929  -0.1026   0.7993   1.0000
   2.500   0.6731   0.02972   0.01929  -0.1027   0.7841   1.0000
   2.750   0.7065   0.02966   0.01921  -0.1025   0.7688   1.0000
   3.000   0.7367   0.02979   0.01932  -0.1020   0.7540   1.0000
   3.250   0.7634   0.03022   0.01975  -0.1014   0.7402   1.0000
   3.500   0.7897   0.03069   0.02024  -0.1008   0.7267   1.0000
   3.750   0.8164   0.03115   0.02075  -0.1001   0.7133   1.0000
   4.000   0.8435   0.03155   0.02119  -0.0993   0.6996   1.0000
   4.250   0.8707   0.03192   0.02161  -0.0985   0.6854   1.0000
   4.500   0.8973   0.03232   0.02209  -0.0975   0.6706   1.0000
   4.750   0.9231   0.03274   0.02258  -0.0963   0.6546   1.0000
   5.000   0.9488   0.03316   0.02307  -0.0950   0.6377   1.0000
   5.250   0.9754   0.03351   0.02350  -0.0937   0.6203   1.0000
   5.500   1.0047   0.03358   0.02363  -0.0924   0.6022   1.0000
   5.750   1.0280   0.03402   0.02413  -0.0905   0.5808   1.0000
   6.000   1.0533   0.03421   0.02435  -0.0886   0.5586   1.0000
   6.250   1.0816   0.03421   0.02436  -0.0869   0.5378   1.0000
   6.500   1.0996   0.03522   0.02550  -0.0851   0.5160   1.0000
   6.750   1.1238   0.03586   0.02619  -0.0836   0.4970   1.0000
   7.000   1.1483   0.03657   0.02696  -0.0823   0.4795   1.0000
   7.250   1.1716   0.03741   0.02791  -0.0810   0.4624   1.0000
   7.500   1.1875   0.03884   0.02953  -0.0793   0.4449   1.0000
   7.750   1.2053   0.04012   0.03099  -0.0777   0.4285   1.0000
   8.000   1.2239   0.04145   0.03249  -0.0763   0.4134   1.0000
   8.250   1.2439   0.04281   0.03405  -0.0750   0.4000   1.0000
   8.500   1.2681   0.04385   0.03522  -0.0739   0.3873   1.0000
   8.750   1.2771   0.04616   0.03784  -0.0721   0.3746   1.0000
   9.000   1.2802   0.04908   0.04107  -0.0700   0.3630   1.0000
   9.250   1.3251   0.04656   0.03846  -0.0689   0.3432   1.0000
   9.500   1.3480   0.04337   0.03521  -0.0656   0.3108   1.0000
   9.750   1.3665   0.04161   0.03331  -0.0627   0.2818   1.0000
  10.000   1.3775   0.04143   0.03304  -0.0596   0.2532   1.0000
  10.250   1.3765   0.04242   0.03392  -0.0555   0.2186   1.0000
  10.500   1.3667   0.04445   0.03569  -0.0506   0.1814   1.0000
  10.750   1.3576   0.04663   0.03767  -0.0463   0.1555   1.0000
  11.000   1.3498   0.04911   0.04021  -0.0425   0.1390   1.0000
  11.250   1.3503   0.05177   0.04283  -0.0397   0.1256   1.0000
  11.500   1.3614   0.05475   0.04572  -0.0380   0.1145   1.0000
  11.750   1.3601   0.05798   0.04926  -0.0357   0.1079   1.0000
  12.000   1.3676   0.06116   0.05245  -0.0342   0.1014   1.0000
  12.250   1.3569   0.06503   0.05672  -0.0322   0.0987   1.0000
  12.500   1.3480   0.06908   0.06107  -0.0308   0.0962   1.0000
  12.750   1.3375   0.07348   0.06573  -0.0299   0.0946   1.0000
  13.000   1.3225   0.07840   0.07091  -0.0296   0.0937   1.0000
  13.250   1.2934   0.08488   0.07771  -0.0309   0.0944   1.0000
  13.500   1.2462   0.09447   0.08766  -0.0355   0.0975   1.0000
  13.750   1.2076   0.10465   0.09803  -0.0408   0.1003   1.0000
  14.000   1.1769   0.11471   0.10818  -0.0461   0.1022   1.0000
  14.250   1.0492   0.15538   0.14858  -0.0736   0.1284   1.0000
  14.500   1.0395   0.16377   0.15689  -0.0778   0.1286   1.0000
  14.750   1.0341   0.17127   0.16435  -0.0814   0.1288   1.0000
  15.000   1.0351   0.17776   0.17084  -0.0839   0.1294   1.0000
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