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GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 241 (MVA PR.1) AIRFOIL (goe241-il)
Reynolds number: 100,000
Max Cl/Cd: 49.01 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe241-il-100000-n5.txt
Download as CSV file: xf-goe241-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 241 (MVA PR.1) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.1250   0.11084   0.10544  -0.1109   0.8798   0.0792
 -10.500   0.1322   0.10821   0.10279  -0.1122   0.8722   0.0816
 -10.250   0.1137   0.10572   0.10030  -0.1178   0.8642   0.0846
 -10.000   0.1357   0.10256   0.09714  -0.1160   0.8570   0.0859
  -9.750   0.1548   0.10007   0.09460  -0.1156   0.8511   0.0880
  -9.500   0.1639   0.09781   0.09234  -0.1161   0.8430   0.0904
  -9.250   0.1674   0.09527   0.08977  -0.1177   0.8356   0.0934
  -8.750   0.1602   0.08428   0.07870  -0.1240   0.8211   0.0669
  -8.500   0.1746   0.08191   0.07627  -0.1240   0.8147   0.0636
  -8.000   0.1469   0.06912   0.06344  -0.1326   0.7985   0.0584
  -7.750   0.1520   0.06588   0.06015  -0.1340   0.7926   0.0580
  -7.500   0.1496   0.06243   0.05673  -0.1357   0.7829   0.0574
  -7.250   0.1437   0.05524   0.04941  -0.1443   0.7756   0.0563
  -7.000   0.1526   0.04448   0.03811  -0.1671   0.7661   0.0551
  -6.750   0.1856   0.03965   0.03273  -0.1777   0.7585   0.0551
  -6.500   0.2250   0.03635   0.02892  -0.1847   0.7533   0.0557
  -6.250   0.2536   0.03439   0.02660  -0.1881   0.7437   0.0568
  -6.000   0.2911   0.03237   0.02410  -0.1921   0.7370   0.0579
  -5.750   0.3236   0.03090   0.02227  -0.1942   0.7291   0.0584
  -5.500   0.3534   0.02963   0.02082  -0.1954   0.7206   0.0589
  -5.250   0.3859   0.02842   0.01946  -0.1966   0.7143   0.0596
  -5.000   0.4114   0.02765   0.01865  -0.1966   0.7045   0.0603
  -4.750   0.4430   0.02676   0.01764  -0.1974   0.6977   0.0614
  -4.500   0.4700   0.02618   0.01698  -0.1976   0.6883   0.0631
  -4.250   0.5007   0.02552   0.01615  -0.1981   0.6804   0.0650
  -4.000   0.5286   0.02504   0.01555  -0.1981   0.6713   0.0662
  -3.750   0.5556   0.02445   0.01502  -0.1978   0.6628   0.0674
  -3.500   0.5826   0.02406   0.01465  -0.1975   0.6543   0.0688
  -3.250   0.6101   0.02376   0.01434  -0.1974   0.6456   0.0706
  -3.000   0.6396   0.02351   0.01400  -0.1976   0.6380   0.0735
  -2.750   0.6679   0.02329   0.01379  -0.1979   0.6292   0.0765
  -2.250   0.7306   0.02284   0.01315  -0.1998   0.6134   0.0835
  -2.000   0.7650   0.02250   0.01268  -0.2015   0.6061   0.0896
  -1.750   0.7970   0.02228   0.01239  -0.2028   0.5983   0.0987
  -1.500   0.8308   0.02192   0.01202  -0.2046   0.5907   0.1200
  -1.250   0.8681   0.02141   0.01219  -0.2074   0.5847   0.3492
  -1.000   0.8929   0.02184   0.01264  -0.2067   0.5775   0.3872
  -0.750   0.9200   0.02221   0.01290  -0.2064   0.5715   0.4120
  -0.500   0.9481   0.02259   0.01313  -0.2061   0.5667   0.4307
  -0.250   0.9698   0.02312   0.01372  -0.2047   0.5601   0.4428
   0.000   0.9948   0.02352   0.01405  -0.2040   0.5539   0.4570
   0.250   1.0226   0.02386   0.01423  -0.2037   0.5485   0.4713
   0.500   1.0442   0.02425   0.01464  -0.2026   0.5415   0.4783
   0.750   1.0695   0.02448   0.01480  -0.2022   0.5353   0.4837
   1.000   1.0995   0.02461   0.01472  -0.2027   0.5302   0.4900
   1.250   1.1239   0.02489   0.01496  -0.2024   0.5242   0.4958
   1.500   1.1474   0.02519   0.01525  -0.2018   0.5185   0.5002
   1.750   1.1742   0.02541   0.01537  -0.2017   0.5137   0.5061
   2.000   1.2022   0.02566   0.01548  -0.2020   0.5090   0.5135
   2.250   1.2236   0.02603   0.01588  -0.2011   0.5036   0.5178
   2.500   1.2471   0.02633   0.01618  -0.2005   0.4985   0.5228
   2.750   1.2740   0.02659   0.01632  -0.2005   0.4942   0.5298
   3.000   1.2987   0.02693   0.01660  -0.2003   0.4896   0.5362
   3.250   1.3173   0.02735   0.01709  -0.1990   0.4840   0.5410
   3.500   1.3395   0.02767   0.01738  -0.1982   0.4784   0.5470
   3.750   1.3669   0.02791   0.01747  -0.1983   0.4737   0.5540
   4.000   1.3831   0.02841   0.01807  -0.1967   0.4685   0.5588
   4.250   1.4015   0.02888   0.01858  -0.1955   0.4636   0.5650
   4.500   1.4231   0.02928   0.01893  -0.1948   0.4591   0.5717
   4.750   1.4481   0.02955   0.01915  -0.1944   0.4552   0.5771
   5.000   1.4616   0.03014   0.01980  -0.1924   0.4507   0.5830
   5.250   1.4742   0.03077   0.02049  -0.1904   0.4460   0.5892
   5.500   1.4909   0.03128   0.02104  -0.1890   0.4415   0.5944
   5.750   1.5127   0.03167   0.02138  -0.1883   0.4374   0.6010
   6.000   1.5290   0.03230   0.02203  -0.1869   0.4331   0.6070
   6.250   1.5374   0.03320   0.02306  -0.1845   0.4279   0.6122
   6.500   1.5507   0.03393   0.02383  -0.1828   0.4230   0.6184
   6.750   1.5700   0.03440   0.02425  -0.1819   0.4187   0.6246
   7.000   1.5804   0.03530   0.02524  -0.1799   0.4138   0.6301
   7.250   1.5851   0.03654   0.02660  -0.1774   0.4080   0.6360
   7.500   1.5967   0.03741   0.02750  -0.1757   0.4028   0.6420
   7.750   1.6156   0.03787   0.02791  -0.1748   0.3983   0.6485
   8.000   1.6109   0.03983   0.03009  -0.1717   0.3916   0.6539
   8.250   1.6169   0.04114   0.03147  -0.1697   0.3854   0.6598
   8.500   1.6321   0.04182   0.03212  -0.1685   0.3803   0.6670
   8.750   1.6232   0.04439   0.03490  -0.1657   0.3725   0.6726
   9.000   1.6296   0.04580   0.03636  -0.1640   0.3662   0.6792
   9.250   1.6299   0.04782   0.03850  -0.1620   0.3594   0.6860
   9.500   1.6269   0.05024   0.04103  -0.1601   0.3518   0.6932
   9.750   1.6357   0.05155   0.04236  -0.1588   0.3460   0.7022
  10.000   1.6244   0.05500   0.04600  -0.1567   0.3378   0.7100
  10.250   1.6320   0.05653   0.04756  -0.1555   0.3321   0.7225
  10.500   1.6244   0.05985   0.05105  -0.1540   0.3248   0.7352
  10.750   1.6257   0.06219   0.05351  -0.1528   0.3188   0.7583
  11.000   1.6283   0.06357   0.05498  -0.1510   0.3143   1.0000
  11.250   1.6174   0.06773   0.05928  -0.1499   0.3078   1.0000
  11.500   1.6221   0.07000   0.06155  -0.1492   0.3033   1.0000
  11.750   1.6374   0.07094   0.06241  -0.1485   0.3001   1.0000
  12.000   1.6288   0.07501   0.06661  -0.1477   0.2953   1.0000
  12.250   1.6257   0.07844   0.07011  -0.1471   0.2911   1.0000
  12.500   1.6322   0.08058   0.07227  -0.1465   0.2880   1.0000
  12.750   1.6483   0.08142   0.07306  -0.1460   0.2856   1.0000
  13.000   1.6610   0.08272   0.07435  -0.1454   0.2832   1.0000
  13.250   1.6376   0.08904   0.08088  -0.1451   0.2788   1.0000
  13.500   1.6296   0.09332   0.08528  -0.1449   0.2753   1.0000
  13.750   1.6339   0.09585   0.08785  -0.1446   0.2729   1.0000
  14.000   1.6458   0.09728   0.08930  -0.1442   0.2711   1.0000
  14.250   1.6632   0.09790   0.08991  -0.1437   0.2696   1.0000
  14.500   1.6860   0.09775   0.08975  -0.1431   0.2684   1.0000
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