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GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 244 (MVA PR.4) AIRFOIL (goe244-il)
Reynolds number: 50,000
Max Cl/Cd: 24.97 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe244-il-50000-n5.txt
Download as CSV file: xf-goe244-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 244 (MVA PR.4) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750   0.1257   0.12518   0.11847  -0.0903   0.8339   0.1348
  -7.500   0.1121   0.12556   0.11890  -0.0898   0.8267   0.1375
  -7.250   0.0907   0.12638   0.11980  -0.0874   0.8164   0.1382
  -7.000   0.1303   0.12022   0.11361  -0.0895   0.8136   0.1407
  -6.750   0.1284   0.11889   0.11233  -0.0866   0.8034   0.1427
  -6.500   0.1379   0.11664   0.11007  -0.0868   0.7965   0.1465
  -6.250   0.1257   0.11643   0.10990  -0.0854   0.7878   0.1508
  -6.000   0.0974   0.11749   0.11105  -0.0823   0.7768   0.1522
  -5.750   0.1280   0.11247   0.10600  -0.0841   0.7737   0.1544
  -5.500   0.1129   0.11228   0.10590  -0.0788   0.7616   0.1557
  -5.250   0.1286   0.10962   0.10323  -0.0792   0.7566   0.1609
  -5.000   0.1089   0.10998   0.10367  -0.0762   0.7452   0.1650
  -4.000   0.1308   0.09297   0.08648  -0.0901   0.7164   0.0883
  -3.750   0.1240   0.09220   0.08577  -0.0877   0.7042   0.0868
  -3.500   0.1605   0.08510   0.07854  -0.1001   0.6991   0.0799
  -3.000   0.2863   0.06747   0.06035  -0.1405   0.6846   0.0725
  -2.750   0.3921   0.05946   0.05175  -0.1649   0.6813   0.0737
  -2.500   0.4889   0.05388   0.04547  -0.1826   0.6788   0.0759
  -2.250   0.5322   0.05241   0.04358  -0.1888   0.6674   0.0766
  -2.000   0.5897   0.05000   0.04069  -0.1948   0.6624   0.0780
  -1.750   0.6442   0.04774   0.03796  -0.1990   0.6592   0.0799
  -1.500   0.6624   0.04804   0.03822  -0.1987   0.6460   0.0816
  -1.250   0.7065   0.04647   0.03652  -0.2008   0.6414   0.0860
  -1.000   0.7304   0.04659   0.03648  -0.2009   0.6300   0.0897
  -0.750   0.7700   0.04548   0.03535  -0.2024   0.6236   0.0949
  -0.500   0.8208   0.04379   0.03352  -0.2052   0.6200   0.1026
  -0.250   0.8393   0.04457   0.03428  -0.2051   0.6059   0.1107
   0.000   0.8979   0.04272   0.03281  -0.2101   0.6015   0.1590
   0.250   0.9154   0.04372   0.03400  -0.2095   0.5884   0.2544
   0.500   0.9466   0.04343   0.03389  -0.2087   0.5826   0.3489
   0.750   0.9521   0.04500   0.03559  -0.2054   0.5701   0.3819
   1.000   0.9807   0.04484   0.03531  -0.2041   0.5639   0.4176
   1.250   0.9920   0.04604   0.03648  -0.2020   0.5529   0.4343
   1.500   1.0200   0.04592   0.03620  -0.2013   0.5460   0.4522
   1.750   1.0507   0.04572   0.03580  -0.2013   0.5397   0.4665
   2.000   1.0663   0.04698   0.03693  -0.2007   0.5294   0.4785
   2.250   1.1029   0.04631   0.03603  -0.2011   0.5250   0.4920
   2.500   1.1121   0.04804   0.03773  -0.1998   0.5154   0.5018
   2.750   1.1407   0.04821   0.03770  -0.2000   0.5094   0.5169
   3.000   1.1787   0.04743   0.03671  -0.2006   0.5056   0.5343
   3.250   1.1768   0.05004   0.03938  -0.1982   0.4960   0.5435
   3.500   1.2029   0.05030   0.03951  -0.1980   0.4907   0.5609
   3.750   1.2397   0.04964   0.03868  -0.1984   0.4873   0.5809
   4.000   1.2358   0.05264   0.04175  -0.1962   0.4793   0.5925
   4.250   1.2496   0.05403   0.04312  -0.1951   0.4739   0.6079
   4.500   1.2787   0.05406   0.04304  -0.1950   0.4705   0.6280
   4.750   1.3159   0.05343   0.04225  -0.1955   0.4680   0.6518
   5.000   1.2756   0.06014   0.04925  -0.1914   0.4581   0.6542
   5.250   1.2913   0.06142   0.05051  -0.1905   0.4538   0.6724
   5.500   1.3212   0.06118   0.05019  -0.1903   0.4511   0.6952
   5.750   1.3578   0.06032   0.04925  -0.1905   0.4491   0.7225
   6.250   1.2763   0.07602   0.06544  -0.1848   0.4320   0.7275
   6.500   1.3028   0.07597   0.06539  -0.1843   0.4304   0.7562
   6.750   1.3335   0.07531   0.06474  -0.1839   0.4291   0.7970
   9.750   1.1576   0.14843   0.13889  -0.1870   0.3562   1.0000
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