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GOE 226 (MVA H.36) AIRFOIL (goe226-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 226 (MVA H.36) AIRFOIL (goe226-il)
Reynolds number: 50,000
Max Cl/Cd: 28.63 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe226-il-50000-n5.txt
Download as CSV file: xf-goe226-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 226 (MVA H.36) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.0462   0.11803   0.11098  -0.0802   0.9281   0.1331
  -8.750  -0.0456   0.11720   0.11016  -0.0845   0.9216   0.1375
  -8.500  -0.0533   0.11683   0.10982  -0.0861   0.9117   0.1382
  -8.250  -0.0209   0.11081   0.10376  -0.0874   0.9097   0.1406
  -8.000   0.0014   0.10719   0.10010  -0.0899   0.9066   0.1430
  -7.750  -0.0009   0.10595   0.09890  -0.0882   0.8967   0.1444
  -7.500   0.0107   0.10342   0.09635  -0.0901   0.8916   0.1460
  -7.250   0.0085   0.10222   0.09519  -0.0891   0.8829   0.1481
  -6.750  -0.0243   0.09699   0.08994  -0.0924   0.8619   0.1073
  -6.500  -0.0080   0.09404   0.08697  -0.0930   0.8578   0.1059
  -6.250  -0.0007   0.09170   0.08463  -0.0933   0.8522   0.1038
  -6.000  -0.0071   0.09025   0.08322  -0.0917   0.8431   0.1019
  -5.750   0.0082   0.08644   0.07936  -0.0964   0.8385   0.0992
  -5.500  -0.0057   0.08502   0.07799  -0.0949   0.8277   0.0978
  -5.250   0.0136   0.08171   0.07462  -0.0992   0.8227   0.0985
  -5.000   0.0173   0.07961   0.07252  -0.1000   0.8139   0.0992
  -4.750   0.0388   0.07598   0.06882  -0.1050   0.8068   0.0999
  -4.500   0.0829   0.07004   0.06270  -0.1163   0.8030   0.0996
  -4.250   0.0937   0.06690   0.05949  -0.1196   0.7911   0.1000
  -4.000   0.1659   0.05793   0.05008  -0.1398   0.7875   0.1044
  -3.750   0.2521   0.04845   0.03969  -0.1627   0.7837   0.1097
  -3.500   0.2707   0.04783   0.03905  -0.1625   0.7746   0.1129
  -3.250   0.3337   0.04382   0.03433  -0.1727   0.7716   0.1198
  -3.000   0.3830   0.04174   0.03192  -0.1776   0.7688   0.1270
  -2.750   0.3988   0.04153   0.03157  -0.1772   0.7586   0.1314
  -2.500   0.4433   0.03992   0.02956  -0.1808   0.7546   0.1403
  -2.250   0.4852   0.03881   0.02830  -0.1831   0.7516   0.1500
  -2.000   0.5001   0.03901   0.02841  -0.1821   0.7408   0.1569
  -1.750   0.5403   0.03811   0.02731  -0.1840   0.7368   0.1705
  -1.500   0.5606   0.03831   0.02758  -0.1832   0.7281   0.1804
  -1.250   0.5926   0.03794   0.02715  -0.1839   0.7219   0.1957
  -1.000   0.6328   0.03722   0.02632  -0.1854   0.7183   0.2166
  -0.750   0.6476   0.03781   0.02693  -0.1839   0.7072   0.2315
  -0.500   0.6857   0.03721   0.02620  -0.1850   0.7028   0.2582
  -0.250   0.7054   0.03759   0.02658  -0.1840   0.6931   0.2786
   0.000   0.7372   0.03731   0.02632  -0.1842   0.6872   0.3062
   0.250   0.7763   0.03661   0.02556  -0.1851   0.6837   0.3391
   0.500   0.7885   0.03744   0.02641  -0.1832   0.6714   0.3595
   0.750   0.8261   0.03685   0.02573  -0.1838   0.6673   0.3916
   1.000   0.8391   0.03766   0.02658  -0.1819   0.6556   0.4117
   1.250   0.8737   0.03724   0.02614  -0.1821   0.6508   0.4467
   1.750   0.9191   0.03775   0.02670  -0.1802   0.6343   0.5021
   2.000   0.9582   0.03697   0.02587  -0.1809   0.6308   0.5293
   2.250   0.9645   0.03824   0.02719  -0.1784   0.6178   0.5457
   2.500   1.0025   0.03756   0.02648  -0.1791   0.6138   0.5751
   2.750   1.0070   0.03899   0.02800  -0.1765   0.6017   0.5947
   3.000   1.0412   0.03853   0.02755  -0.1768   0.5971   0.6311
   3.500   1.0751   0.03959   0.02885  -0.1741   0.5808   0.7211
   3.750   1.1065   0.03865   0.02799  -0.1735   0.5772   1.0000
   4.000   1.1010   0.04133   0.03066  -0.1707   0.5644   1.0000
   4.250   1.1377   0.04098   0.03011  -0.1714   0.5609   1.0000
   4.500   1.1307   0.04395   0.03309  -0.1686   0.5490   1.0000
   4.750   1.1632   0.04374   0.03275  -0.1687   0.5450   1.0000
   5.250   1.1838   0.04699   0.03594  -0.1658   0.5295   1.0000
   5.500   1.2213   0.04623   0.03507  -0.1660   0.5267   1.0000
   5.750   1.2022   0.05051   0.03944  -0.1629   0.5143   1.0000
   6.000   1.2375   0.04977   0.03862  -0.1628   0.5112   1.0000
   6.500   1.2520   0.05359   0.04247  -0.1597   0.4959   1.0000
   6.750   1.2890   0.05258   0.04140  -0.1595   0.4932   1.0000
   7.250   1.3007   0.05673   0.04563  -0.1564   0.4783   1.0000
   7.750   1.3032   0.06216   0.05117  -0.1534   0.4628   1.0000
   8.000   1.3419   0.06075   0.04973  -0.1530   0.4608   1.0000
   8.500   1.2797   0.07448   0.06372  -0.1494   0.4361   1.0000
   8.750   1.2907   0.07626   0.06556  -0.1483   0.4301   1.0000
   9.000   1.3210   0.07548   0.06479  -0.1474   0.4276   1.0000
   9.250   1.3572   0.07402   0.06335  -0.1465   0.4258   1.0000
   9.750   1.3333   0.08375   0.07327  -0.1444   0.4080   1.0000
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