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GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il)
Reynolds number: 500,000
Max Cl/Cd: 86.8 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe143-il-500000-n5.txt
Download as CSV file: xf-goe143-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 143 (MVA H.20) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4485   0.08761   0.08542  -0.0115   1.0000   0.0120
  -8.250  -0.4509   0.08266   0.08050  -0.0147   1.0000   0.0126
  -8.000  -0.4570   0.07311   0.07098  -0.0246   1.0000   0.0136
  -7.750  -0.4425   0.07021   0.06808  -0.0282   1.0000   0.0139
  -7.500  -0.4270   0.06745   0.06532  -0.0314   1.0000   0.0143
  -7.000  -0.3985   0.04873   0.04636  -0.0520   0.9975   0.0181
  -6.750  -0.3649   0.04684   0.04440  -0.0560   0.9932   0.0185
  -6.500  -0.3272   0.02901   0.02572  -0.0713   0.9853   0.0235
  -6.250  -0.2933   0.02897   0.02565  -0.0730   0.9755   0.0240
  -6.000  -0.2613   0.02858   0.02519  -0.0744   0.9632   0.0245
  -5.750  -0.2323   0.02750   0.02399  -0.0753   0.9506   0.0255
  -5.500  -0.2063   0.01800   0.01338  -0.0781   0.9385   0.0296
  -5.250  -0.1799   0.01630   0.01138  -0.0783   0.9239   0.0306
  -5.000  -0.1534   0.01588   0.01085  -0.0780   0.9068   0.0311
  -4.750  -0.1272   0.01563   0.01050  -0.0775   0.8881   0.0318
  -4.500  -0.1010   0.01508   0.00977  -0.0771   0.8698   0.0325
  -4.250  -0.0745   0.01428   0.00874  -0.0767   0.8526   0.0331
  -4.000  -0.0476   0.01352   0.00775  -0.0764   0.8376   0.0338
  -3.750  -0.0205   0.01286   0.00690  -0.0762   0.8232   0.0344
  -3.500   0.0069   0.01227   0.00612  -0.0760   0.8100   0.0350
  -3.250   0.0345   0.01178   0.00548  -0.0758   0.7971   0.0357
  -3.000   0.0622   0.01145   0.00502  -0.0756   0.7841   0.0365
  -2.500   0.1177   0.01087   0.00420  -0.0753   0.7555   0.0374
  -2.250   0.1453   0.01029   0.00352  -0.0751   0.7398   0.0385
  -2.000   0.1731   0.01001   0.00317  -0.0750   0.7211   0.0394
  -1.750   0.2009   0.00985   0.00292  -0.0748   0.6997   0.0403
  -1.500   0.2285   0.00973   0.00271  -0.0747   0.6761   0.0413
  -1.000   0.2838   0.00959   0.00233  -0.0743   0.6222   0.0435
  -0.750   0.3114   0.00956   0.00217  -0.0742   0.5960   0.0448
  -0.500   0.3391   0.00957   0.00206  -0.0741   0.5694   0.0462
  -0.250   0.3668   0.00962   0.00200  -0.0740   0.5445   0.0474
   0.000   0.3947   0.00954   0.00183  -0.0739   0.5227   0.0500
   0.250   0.4224   0.00957   0.00176  -0.0738   0.4981   0.0525
   0.500   0.4499   0.00966   0.00173  -0.0738   0.4697   0.0549
   0.750   0.4775   0.00976   0.00171  -0.0737   0.4440   0.0575
   1.000   0.5052   0.00985   0.00171  -0.0736   0.4248   0.0599
   1.250   0.5332   0.00988   0.00172  -0.0736   0.4113   0.0657
   1.750   0.5889   0.00999   0.00183  -0.0735   0.3840   0.0940
   2.000   0.6167   0.01005   0.00189  -0.0735   0.3714   0.1113
   2.250   0.6445   0.00993   0.00199  -0.0736   0.3574   0.2277
   2.500   0.6667   0.00835   0.00216  -0.0727   0.3433   1.0000
   2.750   0.6944   0.00852   0.00224  -0.0726   0.3293   1.0000
   3.000   0.7219   0.00870   0.00234  -0.0725   0.3166   1.0000
   3.250   0.7494   0.00889   0.00245  -0.0724   0.3024   1.0000
   3.500   0.7768   0.00910   0.00258  -0.0723   0.2867   1.0000
   3.750   0.8040   0.00932   0.00273  -0.0722   0.2692   1.0000
   4.000   0.8310   0.00958   0.00289  -0.0721   0.2496   1.0000
   4.250   0.8576   0.00988   0.00308  -0.0719   0.2269   1.0000
   4.500   0.8838   0.01026   0.00333  -0.0717   0.1979   1.0000
   4.750   0.9095   0.01072   0.00362  -0.0715   0.1665   1.0000
   5.000   0.9353   0.01116   0.00393  -0.0713   0.1437   1.0000
   5.500   0.9875   0.01186   0.00453  -0.0708   0.1205   1.0000
   5.750   1.0135   0.01222   0.00484  -0.0706   0.1108   1.0000
   6.000   1.0393   0.01258   0.00516  -0.0703   0.1039   1.0000
   6.250   1.0656   0.01284   0.00546  -0.0701   0.0999   1.0000
   6.500   1.0915   0.01316   0.00576  -0.0698   0.0941   1.0000
   6.750   1.1171   0.01351   0.00610  -0.0696   0.0879   1.0000
   7.000   1.1427   0.01384   0.00642  -0.0693   0.0803   1.0000
   7.250   1.1676   0.01426   0.00680  -0.0689   0.0671   1.0000
   7.500   1.1877   0.01540   0.00770  -0.0680   0.0254   1.0000
   7.750   1.2112   0.01599   0.00833  -0.0675   0.0198   1.0000
   8.000   1.2352   0.01649   0.00888  -0.0669   0.0173   1.0000
   8.250   1.2582   0.01711   0.00955  -0.0663   0.0149   1.0000
   8.500   1.2814   0.01767   0.01019  -0.0657   0.0134   1.0000
   8.750   1.3045   0.01821   0.01080  -0.0651   0.0123   1.0000
   9.000   1.3267   0.01883   0.01148  -0.0644   0.0113   1.0000
   9.250   1.3474   0.01963   0.01234  -0.0635   0.0104   1.0000
   9.500   1.3674   0.02047   0.01327  -0.0625   0.0097   1.0000
   9.750   1.3879   0.02118   0.01408  -0.0616   0.0092   1.0000
  10.000   1.4077   0.02193   0.01492  -0.0607   0.0086   1.0000
  10.250   1.4267   0.02270   0.01576  -0.0596   0.0081   1.0000
  10.500   1.4444   0.02356   0.01668  -0.0585   0.0077   1.0000
  10.750   1.4590   0.02466   0.01787  -0.0569   0.0073   1.0000
  11.000   1.4703   0.02597   0.01930  -0.0550   0.0070   1.0000
  11.250   1.4827   0.02705   0.02050  -0.0533   0.0068   1.0000
  11.500   1.4909   0.02822   0.02180  -0.0509   0.0066   1.0000
  11.750   1.4960   0.02954   0.02323  -0.0483   0.0064   1.0000
  12.000   1.4997   0.03105   0.02487  -0.0460   0.0062   1.0000
  12.250   1.5022   0.03280   0.02674  -0.0440   0.0061   1.0000
  12.500   1.5038   0.03479   0.02886  -0.0425   0.0059   1.0000
  12.750   1.5048   0.03705   0.03123  -0.0414   0.0058   1.0000
  13.000   1.5052   0.03957   0.03387  -0.0408   0.0056   1.0000
  13.250   1.5041   0.04246   0.03689  -0.0406   0.0055   1.0000
  13.500   1.5024   0.04566   0.04020  -0.0408   0.0054   1.0000
  13.750   1.4984   0.04935   0.04402  -0.0415   0.0053   1.0000
  14.000   1.4924   0.05360   0.04840  -0.0427   0.0052   1.0000
  14.250   1.4831   0.05851   0.05346  -0.0444   0.0052   1.0000
  14.500   1.4723   0.06386   0.05895  -0.0464   0.0051   1.0000
  14.750   1.4591   0.06967   0.06490  -0.0486   0.0050   1.0000
  15.000   1.4438   0.07589   0.07125  -0.0510   0.0050   1.0000
  15.250   1.4282   0.08216   0.07765  -0.0534   0.0050   1.0000
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