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GOE 448 AIRFOIL (goe448-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 448 AIRFOIL (goe448-il)
Reynolds number: 1,000,000
Max Cl/Cd: 137.1 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe448-il-1000000.txt
Download as CSV file: xf-goe448-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 448 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.1963   0.09795   0.09506  -0.1319   0.7541   0.0193
 -10.000   0.1981   0.09370   0.09077  -0.1349   0.7499   0.0207
  -9.750   0.2035   0.09009   0.08717  -0.1367   0.7464   0.0209
  -9.500   0.2175   0.08840   0.08547  -0.1371   0.7423   0.0211
  -9.250   0.2306   0.08675   0.08380  -0.1380   0.7380   0.0214
  -9.000   0.2427   0.08495   0.08196  -0.1392   0.7336   0.0219
  -8.750   0.2544   0.08286   0.07987  -0.1405   0.7300   0.0226
  -8.500   0.2569   0.07876   0.07578  -0.1444   0.7260   0.0245
  -7.000   0.3338   0.01438   0.00987  -0.2278   0.7035   0.0334
  -6.750   0.3615   0.01288   0.00804  -0.2290   0.6998   0.0341
  -6.500   0.3900   0.01220   0.00726  -0.2296   0.6966   0.0351
  -6.250   0.4184   0.01183   0.00680  -0.2300   0.6929   0.0359
  -6.000   0.4466   0.01150   0.00637  -0.2302   0.6891   0.0367
  -5.750   0.4745   0.01124   0.00597  -0.2305   0.6850   0.0377
  -5.500   0.5032   0.01090   0.00554  -0.2308   0.6820   0.0386
  -5.250   0.5318   0.01050   0.00505  -0.2312   0.6786   0.0399
  -5.000   0.5602   0.01038   0.00490  -0.2314   0.6749   0.0413
  -4.750   0.5882   0.01032   0.00478  -0.2315   0.6712   0.0427
  -4.500   0.6165   0.01019   0.00457  -0.2316   0.6676   0.0443
  -4.250   0.6452   0.01014   0.00452  -0.2318   0.6644   0.0463
  -4.000   0.6737   0.01031   0.00472  -0.2319   0.6609   0.0479
  -3.750   0.7017   0.01044   0.00482  -0.2319   0.6573   0.0499
  -3.500   0.7294   0.01052   0.00482  -0.2320   0.6534   0.0518
  -3.250   0.7578   0.01075   0.00510  -0.2320   0.6503   0.0528
  -3.000   0.7860   0.01098   0.00536  -0.2321   0.6469   0.0538
  -2.750   0.8139   0.01113   0.00549  -0.2321   0.6435   0.0555
  -2.500   0.8413   0.01123   0.00550  -0.2321   0.6399   0.0575
  -2.250   0.8688   0.01112   0.00532  -0.2322   0.6363   0.0590
  -2.000   0.8966   0.01115   0.00539  -0.2324   0.6332   0.0600
  -1.750   0.9241   0.01125   0.00551  -0.2324   0.6298   0.0612
  -1.500   0.9511   0.01132   0.00556  -0.2324   0.6262   0.0628
  -1.250   0.9776   0.01136   0.00551  -0.2323   0.6219   0.0645
  -1.000   1.0049   0.01140   0.00552  -0.2323   0.6180   0.0657
  -0.750   1.0322   0.01102   0.00506  -0.2325   0.6134   0.0675
  -0.500   1.0580   0.01094   0.00496  -0.2323   0.6086   0.0689
  -0.250   1.0839   0.01096   0.00497  -0.2322   0.6042   0.0705
   0.000   1.1111   0.01092   0.00493  -0.2322   0.6008   0.0723
   0.250   1.1377   0.01086   0.00484  -0.2322   0.5970   0.0736
   0.500   1.1637   0.01082   0.00475  -0.2320   0.5932   0.0743
   0.750   1.1888   0.01090   0.00476  -0.2316   0.5894   0.0750
   1.000   1.2155   0.01095   0.00481  -0.2316   0.5865   0.0758
   1.250   1.2423   0.01070   0.00454  -0.2317   0.5830   0.0761
   1.500   1.2682   0.01054   0.00436  -0.2316   0.5791   0.0766
   1.750   1.2928   0.01048   0.00428  -0.2312   0.5751   0.0772
   2.000   1.3183   0.01043   0.00424  -0.2310   0.5714   0.0779
   2.250   1.3440   0.01039   0.00423  -0.2308   0.5673   0.0787
   2.500   1.3678   0.01044   0.00427  -0.2303   0.5624   0.0800
   2.750   1.3883   0.01055   0.00435  -0.2291   0.5572   0.0807
   3.000   1.4122   0.01055   0.00439  -0.2285   0.5532   0.0814
   3.250   1.4345   0.01061   0.00446  -0.2277   0.5491   0.0821
   3.500   1.4561   0.01074   0.00457  -0.2267   0.5449   0.0826
   3.750   1.4782   0.01089   0.00472  -0.2259   0.5407   0.0832
   4.000   1.5029   0.01098   0.00484  -0.2256   0.5367   0.0838
   4.250   1.5259   0.01113   0.00499  -0.2250   0.5320   0.0844
   4.500   1.5467   0.01135   0.00520  -0.2240   0.5271   0.0850
   4.750   1.5696   0.01152   0.00539  -0.2235   0.5229   0.0857
   5.000   1.5924   0.01169   0.00558  -0.2229   0.5183   0.0865
   5.250   1.6131   0.01193   0.00581  -0.2219   0.5132   0.0889
   5.500   1.6330   0.01220   0.00610  -0.2208   0.5071   0.0911
   5.750   1.6528   0.01249   0.00639  -0.2198   0.4994   0.0936
   6.000   1.6701   0.01288   0.00677  -0.2183   0.4912   0.0964
   6.250   1.6879   0.01327   0.00716  -0.2169   0.4823   0.1047
   6.500   1.7060   0.01365   0.00765  -0.2157   0.4741   0.1856
   6.750   1.7208   0.01419   0.00826  -0.2140   0.4636   0.2648
   7.000   1.7394   0.01390   0.00899  -0.2132   0.4531   1.0000
   7.250   1.7526   0.01459   0.00964  -0.2112   0.4423   1.0000
   7.500   1.7634   0.01542   0.01041  -0.2089   0.4290   1.0000
   7.750   1.7732   0.01634   0.01126  -0.2065   0.4155   1.0000
   8.000   1.7816   0.01738   0.01223  -0.2040   0.4004   1.0000
   8.500   1.7913   0.01998   0.01468  -0.1982   0.3669   1.0000
   8.750   1.7948   0.02145   0.01607  -0.1953   0.3505   1.0000
   9.000   1.7971   0.02304   0.01759  -0.1924   0.3346   1.0000
   9.250   1.7984   0.02477   0.01925  -0.1894   0.3185   1.0000
   9.500   1.7978   0.02671   0.02111  -0.1864   0.3004   1.0000
   9.750   1.7905   0.02921   0.02348  -0.1827   0.2768   1.0000
  10.000   1.7774   0.03225   0.02635  -0.1785   0.2463   1.0000
  10.250   1.7493   0.03668   0.03052  -0.1731   0.2009   1.0000
  10.500   1.7231   0.04117   0.03482  -0.1683   0.1650   1.0000
  10.750   1.7107   0.04466   0.03821  -0.1650   0.1437   1.0000
  11.000   1.6952   0.04851   0.04191  -0.1617   0.1160   1.0000
  11.250   1.6663   0.05383   0.04702  -0.1576   0.0743   1.0000
  11.500   1.6365   0.05952   0.05255  -0.1537   0.0336   1.0000
  11.750   1.6287   0.06306   0.05608  -0.1517   0.0177   1.0000
  12.000   1.6322   0.06544   0.05851  -0.1504   0.0163   1.0000
  12.250   1.6347   0.06796   0.06108  -0.1492   0.0151   1.0000
  12.500   1.6376   0.07044   0.06362  -0.1480   0.0143   1.0000
  12.750   1.6413   0.07284   0.06608  -0.1470   0.0139   1.0000
  13.000   1.6440   0.07539   0.06869  -0.1459   0.0134   1.0000
  13.250   1.6459   0.07803   0.07140  -0.1449   0.0130   1.0000
  13.500   1.6466   0.08086   0.07428  -0.1438   0.0125   1.0000
  13.750   1.6448   0.08402   0.07752  -0.1428   0.0119   1.0000
  14.000   1.6421   0.08727   0.08085  -0.1417   0.0115   1.0000
  14.250   1.6437   0.09004   0.08368  -0.1409   0.0113   1.0000
  14.500   1.6454   0.09279   0.08650  -0.1401   0.0111   1.0000
  14.750   1.6456   0.09578   0.08956  -0.1394   0.0108   1.0000
  15.000   1.6460   0.09874   0.09258  -0.1388   0.0105   1.0000
  15.250   1.6453   0.10188   0.09579  -0.1382   0.0103   1.0000
  15.500   1.6447   0.10499   0.09895  -0.1376   0.0100   1.0000
  15.750   1.6425   0.10833   0.10237  -0.1372   0.0098   1.0000
  16.000   1.6401   0.11171   0.10582  -0.1367   0.0096   1.0000
  16.250   1.6348   0.11556   0.10974  -0.1364   0.0094   1.0000
  16.500   1.6245   0.12014   0.11443  -0.1362   0.0091   1.0000
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