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GOE 225 (MVA H.35) AIRFOIL (goe225-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 225 (MVA H.35) AIRFOIL (goe225-il)
Reynolds number: 200,000
Max Cl/Cd: 87.55 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe225-il-200000.txt
Download as CSV file: xf-goe225-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 225 (MVA H.35) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500   0.0131   0.09400   0.09016  -0.1055   0.9450   0.0720
  -8.250   0.0270   0.09109   0.08724  -0.1100   0.9421   0.0756
  -8.000  -0.0067   0.09129   0.08751  -0.1131   0.9293   0.0772
  -7.750   0.0172   0.08630   0.08250  -0.1143   0.9279   0.0781
  -7.500   0.0472   0.08291   0.07909  -0.1153   0.9266   0.0792
  -7.250   0.0706   0.08000   0.07615  -0.1173   0.9243   0.0808
  -7.000   0.0645   0.07924   0.07543  -0.1144   0.9161   0.0819
  -6.750   0.0738   0.07704   0.07323  -0.1160   0.9114   0.0841
  -6.500   0.0669   0.07353   0.06972  -0.1328   0.8992   0.0884
  -6.250   0.0786   0.07014   0.06635  -0.1296   0.8963   0.0892
  -6.000   0.0998   0.06802   0.06422  -0.1278   0.8941   0.0903
  -5.750   0.1747   0.03810   0.03361  -0.1816   0.8903   0.0654
  -5.500   0.2561   0.02691   0.02102  -0.2045   0.8898   0.0633
  -5.250   0.2734   0.02609   0.01996  -0.2038   0.8816   0.0646
  -5.000   0.3148   0.02429   0.01775  -0.2072   0.8789   0.0666
  -4.750   0.3556   0.02270   0.01583  -0.2099   0.8765   0.0682
  -4.500   0.3933   0.02167   0.01479  -0.2118   0.8743   0.0706
  -4.250   0.4255   0.02108   0.01410  -0.2125   0.8707   0.0737
  -4.000   0.4516   0.02071   0.01357  -0.2122   0.8640   0.0776
  -3.750   0.4856   0.02006   0.01299  -0.2132   0.8602   0.0837
  -3.500   0.5221   0.01925   0.01213  -0.2145   0.8573   0.0937
  -3.250   0.5537   0.01869   0.01156  -0.2151   0.8526   0.1108
  -3.000   0.5814   0.01833   0.01120  -0.2151   0.8458   0.1266
  -2.750   0.6148   0.01777   0.01062  -0.2159   0.8416   0.1401
  -2.500   0.6494   0.01722   0.01002  -0.2167   0.8383   0.1514
  -2.250   0.6738   0.01716   0.00997  -0.2160   0.8295   0.1621
  -2.000   0.7058   0.01671   0.00956  -0.2164   0.8244   0.1767
  -1.750   0.7396   0.01624   0.00909  -0.2170   0.8205   0.1923
  -1.500   0.7647   0.01611   0.00905  -0.2163   0.8105   0.2088
  -1.250   0.7973   0.01565   0.00866  -0.2166   0.8051   0.2388
  -1.000   0.8247   0.01551   0.00860  -0.2162   0.7960   0.2857
  -0.750   0.8550   0.01526   0.00834  -0.2161   0.7888   0.3216
  -0.500   0.8821   0.01514   0.00825  -0.2156   0.7789   0.3449
  -0.250   0.9121   0.01486   0.00793  -0.2154   0.7706   0.3641
   0.000   0.9384   0.01473   0.00782  -0.2148   0.7583   0.3791
   0.250   0.9665   0.01455   0.00760  -0.2144   0.7470   0.3935
   0.500   0.9955   0.01434   0.00733  -0.2142   0.7356   0.4086
   0.750   1.0221   0.01424   0.00724  -0.2136   0.7205   0.4230
   1.000   1.0491   0.01416   0.00714  -0.2131   0.7051   0.4367
   1.250   1.0763   0.01413   0.00705  -0.2127   0.6898   0.4511
   1.500   1.1037   0.01415   0.00698  -0.2123   0.6747   0.4652
   1.750   1.1307   0.01425   0.00700  -0.2120   0.6606   0.4815
   2.000   1.1576   0.01440   0.00709  -0.2116   0.6477   0.4992
   2.250   1.1847   0.01458   0.00719  -0.2113   0.6362   0.5176
   2.500   1.2113   0.01478   0.00736  -0.2110   0.6250   0.5364
   2.750   1.2377   0.01500   0.00757  -0.2107   0.6147   0.5565
   3.000   1.2653   0.01524   0.00771  -0.2106   0.6054   0.5791
   3.250   1.2902   0.01544   0.00797  -0.2100   0.5944   0.6022
   3.500   1.3162   0.01566   0.00818  -0.2097   0.5842   0.6270
   3.750   1.3416   0.01586   0.00838  -0.2092   0.5744   0.6545
   4.000   1.3663   0.01603   0.00864  -0.2086   0.5659   0.6916
   4.250   1.3859   0.01583   0.00876  -0.2067   0.5582   1.0000
   4.500   1.4127   0.01622   0.00906  -0.2066   0.5505   1.0000
   4.750   1.4379   0.01656   0.00938  -0.2062   0.5427   1.0000
   5.000   1.4652   0.01698   0.00968  -0.2061   0.5358   1.0000
   5.250   1.4887   0.01731   0.01006  -0.2054   0.5281   1.0000
   5.500   1.5150   0.01770   0.01036  -0.2051   0.5211   1.0000
   5.750   1.5383   0.01807   0.01078  -0.2044   0.5137   1.0000
   6.000   1.5623   0.01843   0.01113  -0.2037   0.5065   1.0000
   6.250   1.5875   0.01884   0.01151  -0.2033   0.4998   1.0000
   6.500   1.6088   0.01919   0.01194  -0.2021   0.4918   1.0000
   6.750   1.6344   0.01959   0.01225  -0.2018   0.4848   1.0000
   7.000   1.6529   0.01994   0.01274  -0.2001   0.4765   1.0000
   7.250   1.6754   0.02030   0.01306  -0.1992   0.4686   1.0000
   7.500   1.6925   0.02067   0.01354  -0.1973   0.4594   1.0000
   7.750   1.7126   0.02103   0.01383  -0.1959   0.4504   1.0000
   8.000   1.7255   0.02141   0.01435  -0.1933   0.4401   1.0000
   8.250   1.7420   0.02183   0.01476  -0.1913   0.4309   1.0000
   8.500   1.7529   0.02226   0.01528  -0.1883   0.4205   1.0000
   8.750   1.7619   0.02276   0.01582  -0.1850   0.4102   1.0000
   9.000   1.7710   0.02334   0.01636  -0.1818   0.3998   1.0000
   9.250   1.7773   0.02403   0.01714  -0.1783   0.3876   1.0000
   9.500   1.7852   0.02480   0.01797  -0.1752   0.3756   1.0000
   9.750   1.7927   0.02568   0.01884  -0.1723   0.3638   1.0000
  10.000   1.7990   0.02669   0.01983  -0.1692   0.3513   1.0000
  10.250   1.8051   0.02779   0.02097  -0.1664   0.3379   1.0000
  10.500   1.8107   0.02900   0.02220  -0.1636   0.3245   1.0000
  10.750   1.8156   0.03032   0.02352  -0.1608   0.3115   1.0000
  11.000   1.8198   0.03177   0.02495  -0.1581   0.2991   1.0000
  11.500   1.8267   0.03493   0.02811  -0.1528   0.2749   1.0000
  11.750   1.8304   0.03659   0.02980  -0.1504   0.2640   1.0000
  12.000   1.8326   0.03840   0.03159  -0.1480   0.2546   1.0000
  12.250   1.8365   0.04015   0.03340  -0.1458   0.2448   1.0000
  12.500   1.8387   0.04205   0.03535  -0.1435   0.2360   1.0000
  12.750   1.8393   0.04417   0.03749  -0.1413   0.2269   1.0000
  13.000   1.8415   0.04624   0.03965  -0.1394   0.2175   1.0000
  13.250   1.8391   0.04879   0.04222  -0.1373   0.2076   1.0000
  13.500   1.8362   0.05151   0.04500  -0.1354   0.1964   1.0000
  13.750   1.8324   0.05448   0.04803  -0.1336   0.1835   1.0000
  14.000   1.8251   0.05797   0.05154  -0.1320   0.1685   1.0000
  14.250   1.8128   0.06219   0.05575  -0.1304   0.1509   1.0000
  14.500   1.7968   0.06709   0.06059  -0.1291   0.1261   1.0000
  14.750   1.7739   0.07305   0.06642  -0.1281   0.0996   1.0000
  15.000   1.7504   0.07931   0.07256  -0.1275   0.0819   1.0000
  15.250   1.7303   0.08528   0.07851  -0.1272   0.0735   1.0000
  15.500   1.7122   0.09116   0.08443  -0.1271   0.0684   1.0000
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