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GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il)
Reynolds number: 100,000
Max Cl/Cd: 53.83 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe133-il-100000.txt
Download as CSV file: xf-goe133-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 133 (MVA H.11) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3641   0.09184   0.08710  -0.0206   1.0000   0.0706
  -7.250  -0.3625   0.08913   0.08446  -0.0223   1.0000   0.0727
  -7.000  -0.3604   0.08663   0.08203  -0.0272   1.0000   0.0751
  -6.750  -0.3557   0.08492   0.08028  -0.0376   1.0000   0.0765
  -6.500  -0.3512   0.08030   0.07571  -0.0380   1.0000   0.0773
  -6.250  -0.3471   0.07632   0.07183  -0.0325   1.0000   0.0789
  -6.000  -0.3413   0.07347   0.06902  -0.0306   1.0000   0.0812
  -5.750  -0.3345   0.07065   0.06622  -0.0310   1.0000   0.0843
  -5.500  -0.3121   0.06896   0.06414  -0.0420   1.0000   0.0910
  -5.250  -0.3083   0.06386   0.05921  -0.0397   1.0000   0.0924
  -5.000  -0.3042   0.06099   0.05648  -0.0361   1.0000   0.0953
  -4.750  -0.2774   0.05918   0.05421  -0.0428   1.0000   0.1063
  -4.500  -0.2742   0.05490   0.05020  -0.0395   1.0000   0.1086
  -4.250  -0.2630   0.05239   0.04771  -0.0384   1.0000   0.1138
  -4.000  -0.2411   0.04927   0.04436  -0.0413   1.0000   0.1234
  -3.750  -0.2236   0.04726   0.04225  -0.0415   1.0000   0.1339
  -3.500  -0.2078   0.04414   0.03912  -0.0417   1.0000   0.1410
  -3.250  -0.1888   0.04183   0.03670  -0.0424   1.0000   0.1559
  -3.000  -0.1699   0.03984   0.03464  -0.0428   1.0000   0.1751
  -2.750  -0.1372   0.03715   0.03183  -0.0458   0.9968   0.2023
  -2.250  -0.0087   0.02840   0.02130  -0.0588   0.9852   0.1244
  -2.000   0.0434   0.02552   0.01782  -0.0628   0.9777   0.1137
  -1.750   0.0972   0.02341   0.01518  -0.0672   0.9709   0.1139
  -1.500   0.1452   0.02202   0.01340  -0.0706   0.9600   0.1185
  -1.250   0.1926   0.02070   0.01195  -0.0742   0.9491   0.1266
  -1.000   0.2447   0.01959   0.01070  -0.0783   0.9403   0.1338
  -0.750   0.2916   0.01855   0.00973  -0.0816   0.9282   0.1470
  -0.500   0.3337   0.01756   0.00886  -0.0837   0.9143   0.1603
  -0.250   0.3729   0.01665   0.00809  -0.0852   0.8993   0.1881
   0.000   0.4098   0.01373   0.00729  -0.0854   0.8852   1.0000
   0.250   0.4453   0.01352   0.00675  -0.0857   0.8674   1.0000
   0.500   0.4739   0.01343   0.00647  -0.0850   0.8443   1.0000
   0.750   0.5035   0.01328   0.00612  -0.0842   0.8235   1.0000
   1.000   0.5296   0.01325   0.00591  -0.0829   0.7983   1.0000
   1.250   0.5557   0.01324   0.00571  -0.0816   0.7742   1.0000
   1.500   0.5814   0.01330   0.00555  -0.0802   0.7499   1.0000
   1.750   0.6066   0.01346   0.00554  -0.0791   0.7255   1.0000
   2.000   0.6326   0.01366   0.00556  -0.0782   0.7052   1.0000
   2.250   0.6587   0.01391   0.00568  -0.0775   0.6869   1.0000
   2.500   0.6846   0.01419   0.00586  -0.0768   0.6686   1.0000
   2.750   0.7107   0.01446   0.00605  -0.0762   0.6515   1.0000
   3.000   0.7367   0.01474   0.00625  -0.0756   0.6351   1.0000
   3.250   0.7628   0.01503   0.00647  -0.0750   0.6193   1.0000
   3.500   0.7888   0.01533   0.00671  -0.0744   0.6036   1.0000
   3.750   0.8147   0.01565   0.00699  -0.0738   0.5877   1.0000
   4.000   0.8404   0.01597   0.00725  -0.0732   0.5714   1.0000
   4.250   0.8660   0.01632   0.00753  -0.0725   0.5546   1.0000
   4.500   0.8910   0.01669   0.00791  -0.0718   0.5357   1.0000
   4.750   0.9158   0.01709   0.00828  -0.0711   0.5158   1.0000
   5.000   0.9407   0.01751   0.00863  -0.0703   0.4957   1.0000
   5.250   0.9647   0.01794   0.00906  -0.0694   0.4725   1.0000
   5.500   0.9889   0.01837   0.00942  -0.0685   0.4498   1.0000
   5.750   1.0122   0.01881   0.00987  -0.0676   0.4255   1.0000
   6.000   1.0363   0.01928   0.01026  -0.0668   0.4053   1.0000
   6.250   1.0599   0.01975   0.01076  -0.0660   0.3856   1.0000
   6.500   1.0834   0.02018   0.01124  -0.0653   0.3672   1.0000
   6.750   1.1069   0.02061   0.01170  -0.0645   0.3507   1.0000
   7.000   1.1305   0.02109   0.01223  -0.0638   0.3360   1.0000
   7.250   1.1536   0.02156   0.01277  -0.0630   0.3212   1.0000
   7.500   1.1758   0.02198   0.01323  -0.0621   0.3050   1.0000
   7.750   1.1976   0.02249   0.01378  -0.0612   0.2892   1.0000
   8.000   1.2183   0.02307   0.01442  -0.0601   0.2712   1.0000
   8.250   1.2375   0.02374   0.01520  -0.0589   0.2500   1.0000
   8.500   1.2539   0.02464   0.01611  -0.0573   0.2231   1.0000
   8.750   1.2670   0.02587   0.01725  -0.0553   0.1903   1.0000
   9.000   1.2801   0.02729   0.01860  -0.0533   0.1623   1.0000
   9.250   1.2944   0.02861   0.01985  -0.0515   0.1433   1.0000
   9.500   1.3091   0.02978   0.02110  -0.0498   0.1276   1.0000
   9.750   1.3226   0.03102   0.02238  -0.0480   0.1149   1.0000
  10.000   1.3347   0.03252   0.02385  -0.0462   0.1044   1.0000
  10.250   1.3465   0.03446   0.02562  -0.0445   0.0948   1.0000
  10.500   1.3579   0.03644   0.02777  -0.0426   0.0862   1.0000
  10.750   1.3719   0.03926   0.03068  -0.0411   0.0786   1.0000
  11.000   1.3921   0.04306   0.03431  -0.0409   0.0700   1.0000
  11.250   1.3959   0.04516   0.03691  -0.0380   0.0663   1.0000
  11.500   1.4038   0.04782   0.03981  -0.0361   0.0622   1.0000
  11.750   1.4201   0.05229   0.04423  -0.0359   0.0576   1.0000
  12.000   1.4116   0.05449   0.04689  -0.0323   0.0561   1.0000
  12.250   1.4016   0.05730   0.05007  -0.0290   0.0548   1.0000
  12.500   1.3902   0.06060   0.05371  -0.0264   0.0539   1.0000
  12.750   1.3761   0.06427   0.05769  -0.0244   0.0533   1.0000
  13.000   1.3592   0.06839   0.06210  -0.0233   0.0529   1.0000
  13.250   1.3395   0.07307   0.06707  -0.0231   0.0528   1.0000
  13.500   1.3168   0.07847   0.07276  -0.0240   0.0528   1.0000
  13.750   1.2913   0.08477   0.07931  -0.0263   0.0532   1.0000
  14.000   1.2632   0.09206   0.08685  -0.0298   0.0537   1.0000
  14.250   1.2335   0.10041   0.09540  -0.0346   0.0545   1.0000
  14.500   1.2030   0.10976   0.10492  -0.0404   0.0554   1.0000
  14.750   1.1728   0.11995   0.11523  -0.0468   0.0565   1.0000
  15.000   1.1453   0.13066   0.12600  -0.0533   0.0574   1.0000
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