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GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL (goe320-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL (goe320-il)
Reynolds number: 100,000
Max Cl/Cd: 52.27 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe320-il-100000.txt
Download as CSV file: xf-goe320-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 320 (HANSA-BRANDENBURG II.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2066   0.13165   0.12685  -0.0375   1.0000   0.0624
 -10.500  -0.2309   0.13329   0.12863  -0.0330   1.0000   0.0625
 -10.250  -0.2563   0.13491   0.13036  -0.0285   1.0000   0.0625
  -9.750  -0.2302   0.12701   0.12250  -0.0320   0.9942   0.0635
  -9.500  -0.2085   0.12262   0.11811  -0.0351   0.9899   0.0646
  -9.250  -0.1886   0.11883   0.11431  -0.0391   0.9853   0.0660
  -9.000  -0.1698   0.11526   0.11073  -0.0437   0.9808   0.0676
  -8.750  -0.1546   0.11230   0.10776  -0.0488   0.9744   0.0697
  -8.500  -0.1508   0.11148   0.10694  -0.0580   0.9657   0.0709
  -8.250  -0.1306   0.10666   0.10214  -0.0610   0.9609   0.0717
  -8.000  -0.1007   0.10150   0.09695  -0.0626   0.9588   0.0731
  -7.750  -0.0758   0.09764   0.09309  -0.0670   0.9556   0.0749
  -7.500  -0.0672   0.09537   0.09084  -0.0689   0.9467   0.0765
  -7.250  -0.0511   0.09254   0.08800  -0.0739   0.9410   0.0787
  -7.000  -0.0545   0.09183   0.08730  -0.0782   0.9290   0.0802
  -6.750  -0.0478   0.09086   0.08623  -0.0896   0.9186   0.0811
  -6.500  -0.0312   0.08594   0.08139  -0.0850   0.9143   0.0819
  -6.250  -0.0095   0.08231   0.07778  -0.0851   0.9095   0.0836
  -6.000   0.0155   0.07897   0.07440  -0.0887   0.9051   0.0861
  -5.750   0.0149   0.07777   0.07322  -0.0884   0.8947   0.0879
  -5.500   0.0454   0.07628   0.07141  -0.1028   0.8874   0.0926
  -5.250   0.0449   0.07338   0.06864  -0.0982   0.8786   0.0933
  -5.000   0.0618   0.07022   0.06554  -0.0969   0.8732   0.0954
  -4.750   0.0881   0.06732   0.06259  -0.0993   0.8690   0.0993
  -4.500   0.1059   0.06899   0.06378  -0.1062   0.8574   0.1053
  -4.250   0.1235   0.06357   0.05857  -0.1052   0.8530   0.1066
  -4.000   0.1494   0.06018   0.05521  -0.1056   0.8493   0.1095
  -3.750   0.1534   0.05922   0.05425  -0.1037   0.8384   0.1124
  -3.500   0.1949   0.05670   0.05138  -0.1095   0.8327   0.1207
  -3.250   0.2074   0.05438   0.04914  -0.1079   0.8245   0.1232
  -3.000   0.2292   0.05259   0.04729  -0.1081   0.8172   0.1294
  -2.750   0.2636   0.05001   0.04451  -0.1108   0.8129   0.1378
  -2.500   0.2773   0.04890   0.04340  -0.1097   0.8045   0.1442
  -2.250   0.3037   0.04692   0.04129  -0.1106   0.7976   0.1551
  -2.000   0.3382   0.04459   0.03880  -0.1121   0.7932   0.1706
  -1.750   0.3545   0.04389   0.03800  -0.1114   0.7830   0.1855
  -1.500   0.3834   0.04168   0.03573  -0.1117   0.7770   0.2043
  -1.250   0.4150   0.03945   0.03345  -0.1120   0.7729   0.2292
  -0.750   0.4567   0.03635   0.03039  -0.1100   0.7558   0.3053
  -0.500   0.4743   0.03499   0.02908  -0.1085   0.7448   0.3404
  -0.250   0.5056   0.03278   0.02681  -0.1081   0.7381   0.3765
   0.000   0.5345   0.03153   0.02540  -0.1080   0.7272   0.3911
   0.250   0.5850   0.03011   0.02339  -0.1101   0.7192   0.3224
   0.500   0.6395   0.02940   0.02134  -0.1095   0.7078   0.1282
   0.750   0.6766   0.02773   0.01920  -0.1086   0.6995   0.1174
   1.000   0.7033   0.02668   0.01799  -0.1072   0.6848   0.1180
   1.250   0.7319   0.02547   0.01661  -0.1060   0.6703   0.1182
   1.500   0.7613   0.02424   0.01522  -0.1048   0.6552   0.1186
   1.750   0.7896   0.02300   0.01392  -0.1036   0.6383   0.1220
   2.000   0.8162   0.02211   0.01299  -0.1024   0.6183   0.1298
   2.250   0.8423   0.02127   0.01205  -0.1009   0.5962   0.1363
   2.500   0.8679   0.02062   0.01127  -0.0995   0.5738   0.1502
   2.750   0.8920   0.02016   0.01077  -0.0984   0.5478   0.1715
   3.000   0.9185   0.01807   0.01026  -0.0974   0.5258   1.0000
   3.250   0.9439   0.01827   0.00991  -0.0963   0.5057   1.0000
   3.500   0.9682   0.01859   0.00989  -0.0954   0.4873   1.0000
   3.750   0.9925   0.01899   0.00998  -0.0946   0.4710   1.0000
   4.000   1.0166   0.01945   0.01020  -0.0939   0.4560   1.0000
   4.250   1.0404   0.01998   0.01053  -0.0932   0.4419   1.0000
   4.500   1.0645   0.02055   0.01090  -0.0925   0.4291   1.0000
   4.750   1.0893   0.02116   0.01127  -0.0920   0.4173   1.0000
   5.000   1.1133   0.02178   0.01173  -0.0914   0.4053   1.0000
   5.250   1.1367   0.02246   0.01231  -0.0908   0.3937   1.0000
   5.500   1.1622   0.02319   0.01281  -0.0905   0.3832   1.0000
   5.750   1.1846   0.02389   0.01347  -0.0898   0.3718   1.0000
   6.000   1.2080   0.02470   0.01419  -0.0892   0.3613   1.0000
   6.250   1.2328   0.02549   0.01480  -0.0889   0.3510   1.0000
   6.500   1.2537   0.02637   0.01571  -0.0880   0.3407   1.0000
   6.750   1.2804   0.02725   0.01636  -0.0880   0.3320   1.0000
   7.000   1.2993   0.02818   0.01741  -0.0869   0.3231   1.0000
   7.250   1.3242   0.02902   0.01812  -0.0866   0.3157   1.0000
   7.500   1.3457   0.03005   0.01917  -0.0859   0.3090   1.0000
   7.750   1.3654   0.03094   0.02013  -0.0850   0.3025   1.0000
   8.000   1.3915   0.03180   0.02086  -0.0850   0.2975   1.0000
   8.250   1.4139   0.03295   0.02206  -0.0846   0.2930   1.0000
   8.500   1.4306   0.03406   0.02335  -0.0833   0.2886   1.0000
   8.750   1.4505   0.03510   0.02447  -0.0825   0.2848   1.0000
   9.000   1.4737   0.03610   0.02547  -0.0822   0.2815   1.0000
   9.250   1.5012   0.03723   0.02652  -0.0826   0.2787   1.0000
   9.500   1.5166   0.03870   0.02817  -0.0814   0.2762   1.0000
   9.750   1.5280   0.04022   0.02995  -0.0797   0.2736   1.0000
  10.000   1.5407   0.04177   0.03170  -0.0782   0.2712   1.0000
  10.250   1.5546   0.04323   0.03331  -0.0769   0.2687   1.0000
  10.500   1.5701   0.04459   0.03477  -0.0758   0.2664   1.0000
  10.750   1.5886   0.04588   0.03611  -0.0751   0.2643   1.0000
  11.000   1.6101   0.04731   0.03758  -0.0749   0.2625   1.0000
  11.250   1.6257   0.04934   0.03970  -0.0742   0.2611   1.0000
  11.500   1.6149   0.05202   0.04273  -0.0704   0.2599   1.0000
  11.750   1.5953   0.05514   0.04618  -0.0660   0.2589   1.0000
  12.000   1.5587   0.05915   0.05050  -0.0605   0.2581   1.0000
  12.250   1.4807   0.06693   0.05870  -0.0549   0.2576   1.0000
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