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GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il)
Reynolds number: 50,000
Max Cl/Cd: 20.93 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe242-il-50000-n5.txt
Download as CSV file: xf-goe242-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 242 (MVA PR.2) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0178   0.11473   0.10838  -0.0882   0.9176   0.1441
  -9.250  -0.0277   0.11380   0.10749  -0.0930   0.9056   0.1487
  -8.750  -0.0221   0.09749   0.09108  -0.1041   0.8861   0.0732
  -8.500   0.0011   0.09385   0.08736  -0.1052   0.8800   0.0715
  -8.250   0.0074   0.09088   0.08438  -0.1058   0.8680   0.0703
  -8.000   0.0112   0.08756   0.08106  -0.1072   0.8570   0.0697
  -7.750   0.0153   0.08383   0.07732  -0.1095   0.8478   0.0696
  -7.500   0.0115   0.08092   0.07443  -0.1100   0.8349   0.0695
  -7.250   0.0108   0.07735   0.07087  -0.1120   0.8238   0.0692
  -7.000   0.0146   0.07236   0.06586  -0.1166   0.8153   0.0686
  -6.750   0.0108   0.06711   0.06057  -0.1220   0.8031   0.0674
  -6.500   0.0194   0.05806   0.05126  -0.1378   0.7935   0.0658
  -6.250   0.0569   0.04982   0.04234  -0.1562   0.7850   0.0655
  -6.000   0.1064   0.04492   0.03676  -0.1675   0.7808   0.0685
  -5.750   0.1392   0.04231   0.03364  -0.1727   0.7711   0.0703
  -5.500   0.1812   0.03972   0.03050  -0.1772   0.7665   0.0715
  -5.250   0.2115   0.03836   0.02877  -0.1789   0.7589   0.0733
  -5.000   0.2374   0.03724   0.02762  -0.1789   0.7528   0.0765
  -4.750   0.2695   0.03613   0.02632  -0.1795   0.7489   0.0796
  -4.500   0.2889   0.03591   0.02599  -0.1785   0.7408   0.0815
  -4.250   0.3169   0.03532   0.02522  -0.1782   0.7359   0.0839
  -4.000   0.3500   0.03459   0.02435  -0.1789   0.7325   0.0881
  -3.750   0.3718   0.03460   0.02442  -0.1791   0.7244   0.0935
  -3.500   0.4059   0.03411   0.02379  -0.1808   0.7199   0.1004
  -3.250   0.4505   0.03317   0.02286  -0.1848   0.7168   0.1117
  -3.000   0.4949   0.03248   0.02263  -0.1912   0.7107   0.1620
  -2.750   0.5068   0.03351   0.02470  -0.1870   0.7056   0.3159
  -2.250   0.5596   0.03568   0.02635  -0.1859   0.6968   0.4486
  -2.000   0.5766   0.03690   0.02743  -0.1839   0.6909   0.4737
  -1.750   0.5933   0.03774   0.02821  -0.1805   0.6872   0.4958
  -1.500   0.6203   0.03816   0.02844  -0.1795   0.6847   0.5206
  -1.250   0.6248   0.03965   0.02995  -0.1768   0.6775   0.5290
  -1.000   0.6545   0.03998   0.03008  -0.1781   0.6735   0.5400
  -0.750   0.6835   0.03999   0.02993  -0.1783   0.6705   0.5482
  -0.500   0.7185   0.03985   0.02959  -0.1795   0.6683   0.5592
  -0.250   0.7185   0.04198   0.03178  -0.1774   0.6600   0.5668
   0.000   0.7428   0.04243   0.03214  -0.1772   0.6564   0.5773
   0.250   0.7772   0.04246   0.03200  -0.1787   0.6538   0.5888
   0.750   0.8024   0.04525   0.03477  -0.1772   0.6420   0.5987
   1.000   0.8380   0.04543   0.03480  -0.1794   0.6389   0.6039
   1.250   0.8727   0.04521   0.03448  -0.1804   0.6367   0.6080
   1.750   0.8937   0.04855   0.03782  -0.1789   0.6230   0.6142
   2.000   0.9385   0.04801   0.03712  -0.1815   0.6205   0.6191
   2.500   0.9599   0.05072   0.03985  -0.1790   0.6056   0.6247
   2.750   1.0068   0.04968   0.03869  -0.1811   0.6033   0.6287
   3.250   1.0303   0.05267   0.04169  -0.1795   0.5877   0.6354
   3.500   1.0754   0.05139   0.04033  -0.1808   0.5856   0.6395
   4.000   1.0768   0.05618   0.04525  -0.1774   0.5665   0.6450
   4.500   1.1209   0.05745   0.04650  -0.1770   0.5534   0.6522
   5.000   1.1440   0.06031   0.04948  -0.1749   0.5369   0.6591
   5.500   1.1699   0.06312   0.05234  -0.1734   0.5202   0.6670
   6.000   1.1580   0.06984   0.05926  -0.1704   0.4948   0.6719
   6.250   1.1828   0.06979   0.05925  -0.1699   0.4891   0.6767
   6.500   1.2192   0.06849   0.05794  -0.1697   0.4865   0.6829
   6.750   1.2073   0.07259   0.06217  -0.1683   0.4721   0.6854
   7.250   1.2009   0.07913   0.06886  -0.1662   0.4476   0.6924
   7.500   1.2214   0.07961   0.06939  -0.1657   0.4415   0.6981
   7.750   1.2523   0.07855   0.06839  -0.1649   0.4389   0.7042
   8.000   1.2404   0.08315   0.07310  -0.1641   0.4252   0.7074
   8.500   1.2582   0.08699   0.07708  -0.1628   0.4094   0.7184
   9.000   1.2721   0.09152   0.08177  -0.1616   0.3942   0.7305
   9.500   1.2781   0.09752   0.08798  -0.1608   0.3795   0.7426
  10.000   1.2789   0.10452   0.09518  -0.1603   0.3652   0.7562
  10.250   1.3036   0.10410   0.09489  -0.1595   0.3632   0.7691
  10.750   1.2924   0.11339   0.10446  -0.1599   0.3489   0.7875
  11.250   1.2683   0.12553   0.11687  -0.1616   0.3356   0.8113
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