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GOE 451 AIRFOIL (modified line 6) (goe451-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 451 AIRFOIL (modified line 6) (goe451-il)
Reynolds number: 100,000
Max Cl/Cd: 29.16 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe451-il-100000.txt
Download as CSV file: xf-goe451-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 451 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4165   0.09864   0.09371  -0.0220   1.0000   0.0354
  -7.500  -0.4156   0.09623   0.09138  -0.0221   1.0000   0.0372
  -7.250  -0.4140   0.09399   0.08921  -0.0225   1.0000   0.0388
  -7.000  -0.4088   0.09162   0.08690  -0.0244   1.0000   0.0401
  -6.750  -0.4006   0.08974   0.08508  -0.0277   1.0000   0.0412
  -6.500  -0.3877   0.08803   0.08340  -0.0329   1.0000   0.0418
  -6.250  -0.3703   0.08595   0.08133  -0.0385   1.0000   0.0422
  -6.000  -0.3517   0.08313   0.07849  -0.0432   1.0000   0.0424
  -5.750  -0.3322   0.08005   0.07536  -0.0472   1.0000   0.0425
  -5.500  -0.3327   0.07377   0.06922  -0.0446   1.0000   0.0432
  -5.250  -0.3291   0.06923   0.06465  -0.0425   1.0000   0.0442
  -5.000  -0.3183   0.06554   0.06099  -0.0428   1.0000   0.0455
  -4.750  -0.3025   0.06201   0.05746  -0.0445   1.0000   0.0471
  -4.500  -0.2826   0.05856   0.05399  -0.0473   1.0000   0.0491
  -4.250  -0.2580   0.05510   0.05047  -0.0509   1.0000   0.0517
  -3.750  -0.1914   0.04732   0.04241  -0.0612   0.9989   0.0580
  -3.500  -0.1728   0.04414   0.03921  -0.0620   0.9989   0.0621
  -3.250  -0.1338   0.04073   0.03550  -0.0672   0.9985   0.0711
  -3.000  -0.1119   0.03808   0.03277  -0.0681   0.9987   0.0807
  -2.750  -0.0735   0.03446   0.02896  -0.0728   0.9956   0.0997
  -2.500  -0.0389   0.03191   0.02627  -0.0763   0.9923   0.1393
  -2.000   0.0685   0.02451   0.01762  -0.0871   0.9803   0.1214
  -1.750   0.1201   0.02058   0.01286  -0.0905   0.9722   0.0923
  -1.500   0.1722   0.01750   0.00913  -0.0945   0.9587   0.1030
  -1.250   0.2228   0.01520   0.00626  -0.0978   0.9360   0.0948
  -1.000   0.2646   0.01372   0.00464  -0.1001   0.9034   0.0940
  -0.750   0.3140   0.01269   0.00313  -0.1035   0.8118   0.0985
  -0.500   0.3417   0.01281   0.00243  -0.1027   0.6606   0.1128
  -0.250   0.3542   0.01510   0.00291  -0.1009   0.0572   0.2799
   0.000   0.3737   0.01440   0.00391  -0.0994   0.0377   1.0000
   0.250   0.3941   0.01542   0.00493  -0.0986   0.0311   1.0000
   0.500   0.4206   0.01516   0.00457  -0.0988   0.0264   1.0000
   0.750   0.4352   0.01698   0.00618  -0.0973   0.0231   1.0000
   1.000   0.4649   0.01620   0.00547  -0.0981   0.0210   1.0000
   1.250   0.4867   0.01669   0.00588  -0.0977   0.0191   1.0000
   1.500   0.5064   0.01754   0.00659  -0.0970   0.0176   1.0000
   1.750   0.5257   0.01946   0.00799  -0.0964   0.0165   1.0000
   2.000   0.5510   0.02151   0.00960  -0.0969   0.0159   1.0000
   2.250   0.5729   0.02067   0.00903  -0.0964   0.0154   1.0000
   2.500   0.5961   0.02076   0.00920  -0.0961   0.0144   1.0000
   2.750   0.6201   0.02163   0.01018  -0.0960   0.0132   1.0000
   3.000   0.6449   0.02314   0.01155  -0.0962   0.0117   1.0000
   3.250   0.6720   0.02588   0.01404  -0.0970   0.0110   1.0000
   3.750   0.7229   0.03129   0.01930  -0.0977   0.0105   1.0000
   4.000   0.7435   0.02902   0.01750  -0.0962   0.0102   1.0000
   4.250   0.7666   0.02930   0.01800  -0.0954   0.0096   1.0000
   4.500   0.7902   0.03061   0.01948  -0.0950   0.0089   1.0000
   4.750   0.8135   0.03250   0.02156  -0.0946   0.0083   1.0000
   5.000   0.8364   0.03459   0.02404  -0.0942   0.0081   1.0000
   5.250   0.8582   0.03715   0.02685  -0.0937   0.0079   1.0000
   5.500   0.8792   0.04058   0.03051  -0.0934   0.0077   1.0000
   5.750   0.8994   0.04559   0.03569  -0.0935   0.0075   1.0000
   6.000   0.9207   0.05426   0.04424  -0.0945   0.0074   1.0000
   8.250   1.0546   0.06865   0.06193  -0.0844   0.0070   1.0000
   8.500   1.0670   0.06974   0.06338  -0.0826   0.0069   1.0000
   8.750   1.0780   0.07178   0.06574  -0.0810   0.0067   1.0000
   9.000   1.0864   0.07457   0.06881  -0.0795   0.0064   1.0000
   9.250   1.0922   0.07780   0.07230  -0.0782   0.0062   1.0000
   9.500   1.0954   0.08128   0.07602  -0.0768   0.0061   1.0000
   9.750   1.0962   0.08489   0.07986  -0.0755   0.0059   1.0000
  10.000   1.0941   0.08859   0.08377  -0.0742   0.0058   1.0000
  10.250   1.0893   0.09231   0.08767  -0.0730   0.0058   1.0000
  10.500   1.0814   0.09604   0.09155  -0.0719   0.0058   1.0000
  10.750   1.0689   0.09949   0.09514  -0.0705   0.0058   1.0000
  11.000   1.0550   0.10324   0.09898  -0.0699   0.0059   1.0000
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