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GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il)
Reynolds number: 500,000
Max Cl/Cd: 102.94 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe115-il-500000-n5.txt
Download as CSV file: xf-goe115-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 115 (MVA MK.2) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4194   0.08650   0.08434  -0.0390   1.0000   0.0065
  -9.500  -0.4323   0.08002   0.07791  -0.0416   1.0000   0.0064
  -9.250  -0.5887   0.02888   0.02574  -0.0856   0.9735   0.0057
  -9.000  -0.5632   0.02563   0.02211  -0.0890   0.9641   0.0060
  -8.750  -0.5346   0.02365   0.01986  -0.0913   0.9531   0.0062
  -8.500  -0.5048   0.02195   0.01791  -0.0933   0.9414   0.0066
  -8.250  -0.4759   0.02022   0.01588  -0.0949   0.9279   0.0073
  -8.000  -0.4506   0.01819   0.01346  -0.0955   0.9117   0.0079
  -7.750  -0.4271   0.01658   0.01153  -0.0955   0.8953   0.0084
  -7.500  -0.4020   0.01590   0.01069  -0.0953   0.8797   0.0090
  -7.250  -0.3766   0.01550   0.01015  -0.0951   0.8654   0.0096
  -6.750  -0.3270   0.01441   0.00870  -0.0943   0.8398   0.0115
  -6.500  -0.3022   0.01385   0.00799  -0.0939   0.8278   0.0126
  -6.250  -0.2754   0.01387   0.00793  -0.0937   0.8160   0.0137
  -6.000  -0.2493   0.01366   0.00760  -0.0934   0.8042   0.0150
  -5.750  -0.2238   0.01326   0.00704  -0.0930   0.7922   0.0167
  -5.500  -0.1970   0.01322   0.00685  -0.0928   0.7801   0.0181
  -5.250  -0.1723   0.01261   0.00616  -0.0924   0.7682   0.0196
  -5.000  -0.1464   0.01232   0.00578  -0.0921   0.7562   0.0210
  -4.750  -0.1203   0.01207   0.00543  -0.0919   0.7440   0.0230
  -4.500  -0.0941   0.01182   0.00506  -0.0915   0.7315   0.0247
  -4.250  -0.0679   0.01159   0.00472  -0.0912   0.7187   0.0257
  -4.000  -0.0413   0.01150   0.00451  -0.0910   0.7058   0.0265
  -3.500   0.0098   0.01066   0.00344  -0.0903   0.6809   0.0281
  -3.250   0.0358   0.01034   0.00301  -0.0900   0.6701   0.0295
  -3.000   0.0623   0.01012   0.00269  -0.0897   0.6607   0.0302
  -2.750   0.0891   0.00993   0.00241  -0.0895   0.6518   0.0311
  -2.500   0.1160   0.00977   0.00217  -0.0894   0.6442   0.0321
  -2.250   0.1430   0.00966   0.00196  -0.0892   0.6368   0.0332
  -2.000   0.1702   0.00958   0.00180  -0.0891   0.6304   0.0341
  -1.750   0.1975   0.00951   0.00167  -0.0889   0.6240   0.0347
  -1.500   0.2247   0.00947   0.00156  -0.0888   0.6183   0.0353
  -1.250   0.2521   0.00943   0.00147  -0.0887   0.6125   0.0359
  -1.000   0.2793   0.00940   0.00140  -0.0886   0.6072   0.0376
  -0.750   0.3067   0.00936   0.00135  -0.0885   0.6027   0.0414
  -0.500   0.3341   0.00931   0.00132  -0.0884   0.5978   0.0451
  -0.250   0.3601   0.00896   0.00123  -0.0882   0.5928   0.1555
   0.000   0.3864   0.00872   0.00126  -0.0881   0.5876   0.2386
   0.250   0.4136   0.00871   0.00131  -0.0880   0.5821   0.2614
   0.500   0.4408   0.00875   0.00136  -0.0879   0.5773   0.2782
   0.750   0.4682   0.00875   0.00140  -0.0878   0.5727   0.2870
   1.000   0.4957   0.00878   0.00145  -0.0877   0.5679   0.2948
   1.250   0.5229   0.00881   0.00150  -0.0876   0.5637   0.3024
   1.500   0.5502   0.00884   0.00156  -0.0875   0.5600   0.3094
   1.750   0.5776   0.00885   0.00163  -0.0875   0.5555   0.3174
   2.000   0.6047   0.00887   0.00171  -0.0873   0.5511   0.3298
   2.500   0.6588   0.00888   0.00190  -0.0871   0.5424   0.3599
   2.750   0.6858   0.00890   0.00199  -0.0870   0.5374   0.3715
   3.000   0.7126   0.00893   0.00211  -0.0868   0.5331   0.3876
   3.250   0.7391   0.00891   0.00221  -0.0866   0.5236   0.4163
   3.500   0.7644   0.00879   0.00235  -0.0862   0.5142   0.4998
   4.000   0.8307   0.00807   0.00267  -0.0888   0.4655   1.0000
   4.250   0.8520   0.00850   0.00284  -0.0877   0.4012   1.0000
   4.500   0.8674   0.00952   0.00336  -0.0857   0.3043   1.0000
   4.750   0.8790   0.01098   0.00412  -0.0833   0.1662   1.0000
   5.000   0.8900   0.01247   0.00503  -0.0808   0.0433   1.0000
   5.250   0.9122   0.01293   0.00543  -0.0799   0.0267   1.0000
   5.500   0.9346   0.01336   0.00584  -0.0790   0.0185   1.0000
   5.750   0.9567   0.01380   0.00629  -0.0781   0.0148   1.0000
   6.000   0.9771   0.01439   0.00698  -0.0768   0.0122   1.0000
   6.250   0.9992   0.01480   0.00743  -0.0758   0.0110   1.0000
   6.500   1.0201   0.01528   0.00796  -0.0747   0.0099   1.0000
   6.750   1.0400   0.01583   0.00856  -0.0735   0.0091   1.0000
   7.000   1.0573   0.01655   0.00933  -0.0718   0.0083   1.0000
   7.250   1.0706   0.01753   0.01041  -0.0695   0.0077   1.0000
   7.500   1.0871   0.01822   0.01120  -0.0677   0.0074   1.0000
   7.750   1.1020   0.01898   0.01204  -0.0657   0.0071   1.0000
   8.000   1.1175   0.01963   0.01275  -0.0639   0.0065   1.0000
   8.250   1.1297   0.02034   0.01351  -0.0615   0.0061   1.0000
   8.500   1.1416   0.02107   0.01428  -0.0591   0.0058   1.0000
   8.750   1.1512   0.02197   0.01525  -0.0565   0.0056   1.0000
   9.000   1.1595   0.02302   0.01636  -0.0539   0.0054   1.0000
   9.250   1.1641   0.02448   0.01790  -0.0510   0.0051   1.0000
   9.500   1.1716   0.02589   0.01941  -0.0486   0.0050   1.0000
   9.750   1.1809   0.02727   0.02094  -0.0466   0.0049   1.0000
  10.000   1.1917   0.02859   0.02240  -0.0448   0.0047   1.0000
  10.250   1.2015   0.03025   0.02420  -0.0429   0.0046   1.0000
  10.500   1.2118   0.03203   0.02613  -0.0412   0.0045   1.0000
  10.750   1.2220   0.03394   0.02823  -0.0396   0.0043   1.0000
  11.000   1.2311   0.03616   0.03065  -0.0379   0.0042   1.0000
  11.250   1.2383   0.03822   0.03290  -0.0363   0.0040   1.0000
  11.500   1.2443   0.03981   0.03461  -0.0350   0.0038   1.0000
  11.750   1.2485   0.04178   0.03672  -0.0337   0.0037   1.0000
  12.000   1.2467   0.04548   0.04073  -0.0319   0.0037   1.0000
  12.250   1.2517   0.04647   0.04173  -0.0314   0.0035   1.0000
  12.500   1.2522   0.04879   0.04416  -0.0306   0.0034   1.0000
  12.750   1.2474   0.05225   0.04787  -0.0298   0.0034   1.0000
  13.000   1.2488   0.05424   0.04989  -0.0298   0.0033   1.0000
  13.250   1.2390   0.05848   0.05437  -0.0295   0.0033   1.0000
  13.500   1.2286   0.06280   0.05888  -0.0297   0.0033   1.0000
  13.750   1.2140   0.06799   0.06430  -0.0304   0.0032   1.0000
  14.000   1.1907   0.07479   0.07136  -0.0320   0.0032   1.0000
  14.250   1.1766   0.08044   0.07719  -0.0338   0.0032   1.0000
  14.500   1.1587   0.08711   0.08406  -0.0363   0.0032   1.0000
  14.750   1.1368   0.09505   0.09220  -0.0398   0.0032   1.0000
  15.000   1.1176   0.10310   0.10044  -0.0438   0.0033   1.0000
  15.250   1.0958   0.11234   0.10985  -0.0490   0.0032   1.0000
  15.500   1.0635   0.12564   0.12336  -0.0566   0.0033   1.0000
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