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GOE 484 AIRFOIL (goe484-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 484 AIRFOIL (goe484-il)
Reynolds number: 50,000
Max Cl/Cd: 44.38 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe484-il-50000-n5.txt
Download as CSV file: xf-goe484-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 484 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3581   0.10399   0.09710  -0.0260   1.0000   0.1082
  -7.250  -0.3703   0.10332   0.09655  -0.0246   1.0000   0.1106
  -7.000  -0.3809   0.10287   0.09622  -0.0259   1.0000   0.1121
  -6.750  -0.3865   0.10218   0.09561  -0.0298   1.0000   0.1128
  -6.500  -0.3796   0.09691   0.09040  -0.0245   1.0000   0.1144
  -6.250  -0.3759   0.09386   0.08737  -0.0224   1.0000   0.1164
  -6.000  -0.3737   0.09136   0.08490  -0.0217   1.0000   0.1190
  -5.750  -0.3712   0.08899   0.08256  -0.0222   1.0000   0.1220
  -5.500  -0.3641   0.08717   0.08074  -0.0281   1.0000   0.1266
  -5.250  -0.3532   0.08412   0.07769  -0.0324   1.0000   0.1281
  -5.000  -0.3515   0.08074   0.07437  -0.0275   1.0000   0.1308
  -4.750  -0.3431   0.07812   0.07176  -0.0273   1.0000   0.1363
  -4.500  -0.3187   0.07505   0.06858  -0.0365   1.0000   0.1433
  -4.250  -0.3116   0.07189   0.06545  -0.0344   1.0000   0.1453
  -4.000  -0.2979   0.06897   0.06252  -0.0352   1.0000   0.1481
  -3.500  -0.1802   0.05490   0.04748  -0.0625   0.9918   0.0818
  -3.250  -0.1372   0.05097   0.04328  -0.0692   0.9870   0.0815
  -3.000  -0.0970   0.04745   0.03951  -0.0746   0.9821   0.0802
  -2.750  -0.0538   0.04397   0.03569  -0.0803   0.9776   0.0776
  -2.500  -0.0105   0.04065   0.03194  -0.0855   0.9727   0.0753
  -2.250   0.0341   0.03760   0.02837  -0.0905   0.9684   0.0737
  -2.000   0.0750   0.03514   0.02542  -0.0941   0.9634   0.0730
  -1.750   0.1139   0.03350   0.02339  -0.0970   0.9580   0.0749
  -1.500   0.1505   0.03212   0.02164  -0.0993   0.9519   0.0779
  -1.250   0.1890   0.03074   0.01986  -0.1016   0.9465   0.0794
  -1.000   0.2236   0.02961   0.01836  -0.1030   0.9398   0.0805
  -0.750   0.2608   0.02866   0.01707  -0.1048   0.9339   0.0821
  -0.500   0.2937   0.02798   0.01618  -0.1058   0.9263   0.0844
  -0.250   0.3317   0.02747   0.01555  -0.1077   0.9204   0.0884
   0.000   0.3627   0.02713   0.01508  -0.1083   0.9117   0.0955
   0.250   0.4016   0.02681   0.01475  -0.1105   0.9058   0.1100
   0.500   0.4312   0.02654   0.01454  -0.1109   0.8962   0.1306
   0.750   0.4723   0.02594   0.01416  -0.1136   0.8909   0.2044
   1.000   0.4961   0.02405   0.01430  -0.1132   0.8812   1.0000
   1.250   0.5349   0.02425   0.01416  -0.1150   0.8750   1.0000
   1.500   0.5607   0.02459   0.01432  -0.1148   0.8638   1.0000
   1.750   0.5911   0.02488   0.01448  -0.1153   0.8548   1.0000
   2.000   0.6245   0.02510   0.01462  -0.1163   0.8468   1.0000
   2.250   0.6509   0.02548   0.01494  -0.1161   0.8365   1.0000
   2.500   0.6874   0.02561   0.01505  -0.1175   0.8301   1.0000
   2.750   0.7110   0.02606   0.01552  -0.1169   0.8189   1.0000
   3.000   0.7447   0.02625   0.01575  -0.1178   0.8117   1.0000
   3.250   0.7715   0.02660   0.01616  -0.1177   0.8015   1.0000
   3.500   0.7981   0.02691   0.01657  -0.1173   0.7904   1.0000
   3.750   0.8313   0.02681   0.01657  -0.1175   0.7784   1.0000
   4.000   0.8644   0.02656   0.01645  -0.1175   0.7650   1.0000
   4.250   0.8952   0.02635   0.01642  -0.1170   0.7505   1.0000
   4.500   0.9250   0.02560   0.01581  -0.1154   0.7265   1.0000
   4.750   0.9558   0.02432   0.01460  -0.1130   0.6896   1.0000
   5.000   0.9867   0.02350   0.01384  -0.1111   0.6501   1.0000
   5.250   1.0147   0.02304   0.01323  -0.1089   0.5936   1.0000
   5.500   1.0337   0.02329   0.01328  -0.1060   0.5280   1.0000
   5.750   1.0451   0.02399   0.01362  -0.1022   0.4109   1.0000
   6.000   1.0431   0.02629   0.01450  -0.0973   0.2361   1.0000
   6.250   1.0467   0.02870   0.01615  -0.0943   0.1375   1.0000
   6.500   1.0561   0.03052   0.01767  -0.0918   0.1148   1.0000
   6.750   1.0663   0.03213   0.01921  -0.0894   0.1033   1.0000
   7.000   1.0790   0.03351   0.02069  -0.0872   0.0962   1.0000
   7.250   1.0914   0.03499   0.02225  -0.0851   0.0916   1.0000
   7.500   1.1051   0.03660   0.02391  -0.0831   0.0881   1.0000
   7.750   1.1253   0.03797   0.02553  -0.0817   0.0844   1.0000
   8.000   1.1482   0.03949   0.02715  -0.0808   0.0788   1.0000
   8.250   1.1839   0.04144   0.02910  -0.0817   0.0740   1.0000
   8.500   1.2227   0.04347   0.03141  -0.0826   0.0702   1.0000
   8.750   1.2513   0.04564   0.03379  -0.0827   0.0653   1.0000
   9.000   1.2882   0.04917   0.03730  -0.0843   0.0617   1.0000
   9.250   1.3059   0.05169   0.04039  -0.0826   0.0597   1.0000
   9.500   1.3191   0.05439   0.04358  -0.0807   0.0567   1.0000
   9.750   1.3308   0.05738   0.04697  -0.0788   0.0543   1.0000
  10.000   1.3401   0.06077   0.05078  -0.0768   0.0531   1.0000
  10.250   1.3474   0.06412   0.05441  -0.0749   0.0515   1.0000
  10.500   1.3528   0.06779   0.05826  -0.0732   0.0498   1.0000
  10.750   1.3505   0.07214   0.06285  -0.0710   0.0486   1.0000
  11.000   1.3362   0.07519   0.06633  -0.0671   0.0481   1.0000
  11.250   1.3191   0.07847   0.06996  -0.0635   0.0477   1.0000
  11.500   1.3006   0.08214   0.07395  -0.0606   0.0475   1.0000
  11.750   1.2809   0.08626   0.07835  -0.0587   0.0474   1.0000
  12.000   1.2603   0.09086   0.08319  -0.0578   0.0474   1.0000
  12.250   1.2388   0.09598   0.08854  -0.0579   0.0475   1.0000
  12.500   1.2170   0.10166   0.09442  -0.0590   0.0476   1.0000
  12.750   1.1950   0.10798   0.10092  -0.0613   0.0478   1.0000
  13.000   1.1740   0.11492   0.10800  -0.0647   0.0481   1.0000
  13.250   1.1546   0.12242   0.11560  -0.0688   0.0483   1.0000
  13.500   1.1377   0.13033   0.12359  -0.0735   0.0486   1.0000
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