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GOE 382 AIRFOIL (goe382-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 382 AIRFOIL (goe382-il)
Reynolds number: 50,000
Max Cl/Cd: 14 at α=0°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe382-il-50000-n5.txt
Download as CSV file: xf-goe382-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 382 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.0386   0.10575   0.09865  -0.1010   0.8896   0.0864
 -10.250  -0.0324   0.10240   0.09530  -0.1025   0.8795   0.0858
 -10.000  -0.0272   0.09877   0.09165  -0.1043   0.8704   0.0852
  -9.750  -0.0262   0.09521   0.08809  -0.1057   0.8603   0.0843
  -9.250  -0.0648   0.08191   0.07472  -0.1145   0.8405   0.0794
  -9.000  -0.0710   0.07735   0.07011  -0.1170   0.8318   0.0787
  -8.750  -0.0918   0.07342   0.06613  -0.1179   0.8204   0.0779
  -8.500  -0.1154   0.06938   0.06195  -0.1179   0.8117   0.0771
  -8.250  -0.1397   0.06623   0.05863  -0.1164   0.8008   0.0765
  -8.000  -0.1540   0.06253   0.05464  -0.1155   0.7934   0.0760
  -7.750  -0.1671   0.05983   0.05167  -0.1132   0.7843   0.0756
  -7.500  -0.1715   0.05703   0.04853  -0.1114   0.7765   0.0755
  -7.250  -0.1637   0.05393   0.04500  -0.1107   0.7719   0.0756
  -7.000  -0.1686   0.05265   0.04349  -0.1073   0.7615   0.0758
  -6.750  -0.1558   0.05039   0.04085  -0.1064   0.7560   0.0768
  -6.500  -0.1410   0.04827   0.03828  -0.1054   0.7508   0.0780
  -6.250  -0.1382   0.04722   0.03689  -0.1024   0.7414   0.0790
  -6.000  -0.1151   0.04548   0.03486  -0.1021   0.7366   0.0802
  -5.750  -0.0896   0.04400   0.03321  -0.1020   0.7321   0.0815
  -5.500  -0.0830   0.04358   0.03265  -0.0992   0.7226   0.0823
  -5.250  -0.0559   0.04219   0.03101  -0.0991   0.7180   0.0837
  -5.000  -0.0225   0.04066   0.02916  -0.0996   0.7147   0.0855
  -4.750  -0.0187   0.04075   0.02910  -0.0964   0.7044   0.0866
  -4.500   0.0087   0.03981   0.02819  -0.0963   0.6996   0.0892
  -4.250   0.0427   0.03868   0.02690  -0.0968   0.6962   0.0933
  -4.000   0.0474   0.03897   0.02722  -0.0938   0.6865   0.0955
  -3.750   0.0727   0.03837   0.02660  -0.0932   0.6811   0.0994
  -3.500   0.1056   0.03746   0.02562  -0.0936   0.6776   0.1044
  -3.250   0.1128   0.03785   0.02602  -0.0910   0.6689   0.1082
  -3.000   0.1343   0.03760   0.02578  -0.0901   0.6626   0.1161
  -2.750   0.1672   0.03687   0.02502  -0.0905   0.6588   0.1327
  -2.500   0.1822   0.03694   0.02511  -0.0889   0.6519   0.1520
  -2.250   0.1932   0.03705   0.02534  -0.0869   0.6439   0.1784
  -2.000   0.2212   0.03610   0.02482  -0.0870   0.6399   0.2502
  -1.750   0.2514   0.03484   0.02420  -0.0871   0.6370   0.3874
  -1.500   0.2393   0.03612   0.02598  -0.0823   0.6252   0.4527
  -1.250   0.2592   0.03559   0.02605  -0.0796   0.6209   0.6205
  -1.000   0.2897   0.03507   0.02574  -0.0778   0.6180   0.7335
  -0.750   0.2822   0.03678   0.02762  -0.0733   0.6066   0.7894
  -0.500   0.3286   0.03684   0.02760  -0.0752   0.6022   0.8797
  -0.250   0.4095   0.03656   0.02698  -0.0832   0.5995   0.9580
   0.000   0.5040   0.03600   0.02600  -0.0943   0.5972   1.0000
   0.250   0.4405   0.03868   0.02878  -0.0827   0.5835   1.0000
   0.500   0.4667   0.03853   0.02836  -0.0823   0.5798   1.0000
   0.750   0.4933   0.03848   0.02805  -0.0820   0.5764   1.0000
   1.250   0.4762   0.04134   0.03071  -0.0735   0.5597   1.0000
   1.750   0.4682   0.04510   0.03428  -0.0679   0.5425   1.0000
   2.000   0.5013   0.04481   0.03378  -0.0681   0.5402   1.0000
   2.750   0.5243   0.04940   0.03805  -0.0639   0.5200   1.0000
   3.250   0.5292   0.05388   0.04240  -0.0614   0.5046   1.0000
   3.500   0.5075   0.05837   0.04692  -0.0594   0.4925   1.0000
   3.750   0.5297   0.05903   0.04745  -0.0591   0.4889   1.0000
   4.000   0.5574   0.05920   0.04749  -0.0590   0.4866   1.0000
   4.500   0.5548   0.06491   0.05313  -0.0571   0.4714   1.0000
   4.750   0.5824   0.06509   0.05320  -0.0569   0.4691   1.0000
   5.250   0.5748   0.07164   0.05972  -0.0553   0.4546   1.0000
   5.500   0.5997   0.07214   0.06013  -0.0552   0.4521   1.0000
   5.750   0.6287   0.07222   0.06011  -0.0550   0.4503   1.0000
   6.000   0.5942   0.07865   0.06663  -0.0540   0.4385   1.0000
   6.250   0.6136   0.07979   0.06771  -0.0538   0.4355   1.0000
   6.500   0.6385   0.08035   0.06820  -0.0536   0.4335   1.0000
   6.750   0.6118   0.08617   0.07409  -0.0530   0.4237   1.0000
   7.000   0.6264   0.08777   0.07566  -0.0528   0.4198   1.0000
   7.250   0.6474   0.08877   0.07660  -0.0526   0.4172   1.0000
   7.500   0.6711   0.08952   0.07730  -0.0525   0.4153   1.0000
   7.750   0.6391   0.09614   0.08402  -0.0523   0.4060   1.0000
   8.000   0.6528   0.09787   0.08573  -0.0522   0.4021   1.0000
   8.250   0.6738   0.09888   0.08671  -0.0520   0.3995   1.0000
   8.500   0.6978   0.09961   0.08739  -0.0519   0.3976   1.0000
   8.750   0.6662   0.10637   0.09426  -0.0521   0.3893   1.0000
   9.000   0.6769   0.10849   0.09638  -0.0521   0.3853   1.0000
   9.250   0.6956   0.10975   0.09762  -0.0520   0.3824   1.0000
   9.500   0.7190   0.11056   0.09840  -0.0519   0.3804   1.0000
  10.000   0.7018   0.11909   0.10705  -0.0526   0.3691   1.0000
  10.250   0.7180   0.12063   0.10860  -0.0526   0.3658   1.0000
  10.500   0.7397   0.12162   0.10958  -0.0526   0.3635   1.0000
  10.750   0.7297   0.12606   0.11408  -0.0531   0.3581   1.0000
  11.000   0.7296   0.12931   0.11738  -0.0536   0.3530   1.0000
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