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GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 673 AIRFOIL (goe673-il)
Reynolds number: 50,000
Max Cl/Cd: 37.52 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe673-il-50000-n5.txt
Download as CSV file: xf-goe673-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 673 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  -0.4370   0.09912   0.09235  -0.0453   1.0000   0.0394
  -9.250  -0.4361   0.09540   0.08869  -0.0457   1.0000   0.0391
  -9.000  -0.4381   0.09151   0.08487  -0.0466   1.0000   0.0388
  -8.750  -0.4427   0.08758   0.08103  -0.0476   1.0000   0.0384
  -8.500  -0.4504   0.08371   0.07727  -0.0485   1.0000   0.0381
  -8.250  -0.4614   0.07982   0.07348  -0.0494   1.0000   0.0376
  -8.000  -0.4717   0.07564   0.06937  -0.0506   1.0000   0.0372
  -7.750  -0.4824   0.07174   0.06548  -0.0510   1.0000   0.0367
  -7.500  -0.4921   0.06784   0.06153  -0.0511   1.0000   0.0364
  -7.250  -0.4996   0.06387   0.05746  -0.0510   1.0000   0.0361
  -7.000  -0.5038   0.05987   0.05328  -0.0507   1.0000   0.0359
  -6.750  -0.5041   0.05587   0.04900  -0.0504   1.0000   0.0359
  -6.500  -0.4999   0.05198   0.04477  -0.0501   1.0000   0.0362
  -6.250  -0.4915   0.04825   0.04062  -0.0496   1.0000   0.0365
  -6.000  -0.4793   0.04471   0.03661  -0.0491   1.0000   0.0367
  -5.750  -0.4637   0.04143   0.03283  -0.0486   1.0000   0.0368
  -5.500  -0.4453   0.03848   0.02937  -0.0479   1.0000   0.0371
  -5.250  -0.4247   0.03590   0.02628  -0.0472   1.0000   0.0376
  -5.000  -0.4025   0.03376   0.02365  -0.0464   1.0000   0.0387
  -4.750  -0.3808   0.03172   0.02140  -0.0458   1.0000   0.0415
  -4.500  -0.3587   0.03022   0.01970  -0.0452   1.0000   0.0450
  -4.250  -0.3353   0.02884   0.01800  -0.0443   1.0000   0.0477
  -4.000  -0.3116   0.02767   0.01657  -0.0435   1.0000   0.0511
  -3.750  -0.2879   0.02650   0.01531  -0.0434   1.0000   0.0602
  -3.500  -0.2613   0.02541   0.01407  -0.0437   0.9994   0.0718
  -3.250  -0.2222   0.02339   0.01280  -0.0470   0.9958   0.1912
  -3.000  -0.1908   0.02196   0.01288  -0.0485   0.9911   0.5005
  -2.750  -0.1613   0.02165   0.01293  -0.0482   0.9850   0.6242
  -2.500  -0.1291   0.02154   0.01271  -0.0487   0.9781   0.6967
  -2.250  -0.1004   0.02140   0.01250  -0.0483   0.9704   0.7678
  -2.000  -0.0694   0.02128   0.01232  -0.0480   0.9630   0.8542
  -1.750  -0.0164   0.02118   0.01194  -0.0531   0.9550   1.0000
  -1.500   0.0189   0.02132   0.01166  -0.0557   0.9456   1.0000
  -1.250   0.0582   0.02150   0.01149  -0.0588   0.9379   1.0000
  -1.000   0.0935   0.02168   0.01138  -0.0610   0.9285   1.0000
  -0.750   0.1272   0.02186   0.01130  -0.0628   0.9188   1.0000
  -0.500   0.1658   0.02202   0.01124  -0.0655   0.9109   1.0000
  -0.250   0.1992   0.02219   0.01124  -0.0671   0.9008   1.0000
   0.000   0.2314   0.02237   0.01125  -0.0684   0.8905   1.0000
   0.250   0.2689   0.02250   0.01126  -0.0706   0.8822   1.0000
   0.500   0.3025   0.02263   0.01129  -0.0720   0.8724   1.0000
   0.750   0.3322   0.02279   0.01138  -0.0726   0.8614   1.0000
   1.000   0.3633   0.02293   0.01147  -0.0735   0.8510   1.0000
   1.250   0.3994   0.02296   0.01147  -0.0750   0.8427   1.0000
   1.500   0.4282   0.02310   0.01161  -0.0754   0.8313   1.0000
   1.750   0.4563   0.02326   0.01178  -0.0755   0.8197   1.0000
   2.000   0.4852   0.02340   0.01196  -0.0758   0.8084   1.0000
   2.250   0.5163   0.02346   0.01207  -0.0763   0.7981   1.0000
   2.500   0.5485   0.02347   0.01214  -0.0769   0.7881   1.0000
   2.750   0.5753   0.02364   0.01241  -0.0767   0.7755   1.0000
   3.000   0.6026   0.02378   0.01265  -0.0765   0.7630   1.0000
   3.250   0.6305   0.02391   0.01288  -0.0764   0.7507   1.0000
   3.500   0.6590   0.02401   0.01314  -0.0763   0.7383   1.0000
   3.750   0.6880   0.02408   0.01335  -0.0762   0.7259   1.0000
   4.000   0.7170   0.02414   0.01357  -0.0761   0.7132   1.0000
   4.250   0.7456   0.02422   0.01386  -0.0758   0.6999   1.0000
   4.500   0.7733   0.02434   0.01418  -0.0754   0.6858   1.0000
   4.750   0.8004   0.02451   0.01456  -0.0749   0.6711   1.0000
   5.000   0.8270   0.02472   0.01500  -0.0743   0.6559   1.0000
   5.250   0.8534   0.02497   0.01556  -0.0737   0.6404   1.0000
   5.500   0.8797   0.02526   0.01615  -0.0731   0.6249   1.0000
   5.750   0.9059   0.02560   0.01684  -0.0724   0.6093   1.0000
   6.000   0.9216   0.02473   0.01591  -0.0676   0.5509   1.0000
   6.250   0.9253   0.02466   0.01540  -0.0616   0.4558   1.0000
   6.500   0.9238   0.02589   0.01583  -0.0562   0.3131   1.0000
   6.750   0.9068   0.02970   0.01775  -0.0511   0.0938   1.0000
   7.000   0.9091   0.03234   0.02009  -0.0480   0.0668   1.0000
   7.250   0.9145   0.03430   0.02225  -0.0452   0.0565   1.0000
   7.500   0.9200   0.03619   0.02430  -0.0425   0.0497   1.0000
   7.750   0.9250   0.03815   0.02641  -0.0400   0.0454   1.0000
   8.000   0.9279   0.04038   0.02875  -0.0375   0.0430   1.0000
   8.250   0.9368   0.04230   0.03086  -0.0353   0.0406   1.0000
   8.500   0.9503   0.04406   0.03284  -0.0335   0.0373   1.0000
   8.750   0.9684   0.04594   0.03479  -0.0320   0.0341   1.0000
   9.000   1.0148   0.04827   0.03726  -0.0324   0.0322   1.0000
   9.250   1.0562   0.05133   0.04074  -0.0332   0.0308   1.0000
   9.500   1.0779   0.05437   0.04420  -0.0324   0.0292   1.0000
   9.750   1.0902   0.05738   0.04758  -0.0308   0.0279   1.0000
  10.000   1.0969   0.06048   0.05101  -0.0288   0.0271   1.0000
  10.250   1.0989   0.06376   0.05465  -0.0265   0.0268   1.0000
  10.500   1.0957   0.06715   0.05838  -0.0241   0.0268   1.0000
  10.750   1.0882   0.07066   0.06235  -0.0218   0.0268   1.0000
  11.000   1.0773   0.07435   0.06635  -0.0199   0.0269   1.0000
  11.250   1.0636   0.07832   0.07060  -0.0186   0.0270   1.0000
  11.500   1.0480   0.08262   0.07517  -0.0181   0.0272   1.0000
  11.750   1.0305   0.08736   0.08015  -0.0184   0.0274   1.0000
  12.000   1.0118   0.09261   0.08563  -0.0196   0.0276   1.0000
  12.250   0.9921   0.09846   0.09167  -0.0219   0.0278   1.0000
  12.500   0.9722   0.10497   0.09823  -0.0251   0.0281   1.0000
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