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GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il)
Reynolds number: 100,000
Max Cl/Cd: 58.42 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe133-il-100000-n5.txt
Download as CSV file: xf-goe133-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3587   0.10869   0.10377  -0.0245   1.0000   0.0413
  -8.500  -0.3576   0.10617   0.10131  -0.0267   1.0000   0.0415
  -8.250  -0.3570   0.10352   0.09873  -0.0282   1.0000   0.0416
  -8.000  -0.3555   0.10066   0.09595  -0.0299   1.0000   0.0416
  -7.750  -0.3518   0.09754   0.09288  -0.0321   1.0000   0.0417
  -7.500  -0.3481   0.09436   0.08975  -0.0339   1.0000   0.0417
  -7.250  -0.3439   0.09108   0.08652  -0.0356   1.0000   0.0417
  -7.000  -0.3394   0.08775   0.08322  -0.0369   1.0000   0.0418
  -6.750  -0.3345   0.08437   0.07984  -0.0378   1.0000   0.0418
  -6.500  -0.3292   0.08095   0.07644  -0.0386   1.0000   0.0417
  -6.000  -0.3265   0.07215   0.06772  -0.0346   1.0000   0.0319
  -5.750  -0.3217   0.06922   0.06482  -0.0341   1.0000   0.0312
  -5.500  -0.3054   0.06504   0.06059  -0.0379   0.9984   0.0313
  -5.250  -0.2639   0.05865   0.05399  -0.0477   0.9916   0.0317
  -5.000  -0.2260   0.05314   0.04830  -0.0548   0.9857   0.0314
  -4.750  -0.1883   0.04776   0.04266  -0.0611   0.9790   0.0310
  -4.500  -0.1480   0.04212   0.03665  -0.0671   0.9728   0.0311
  -4.250  -0.1067   0.03677   0.03083  -0.0724   0.9669   0.0335
  -4.000  -0.0713   0.03422   0.02806  -0.0754   0.9602   0.0357
  -3.750  -0.0311   0.03007   0.02336  -0.0788   0.9542   0.0374
  -3.500   0.0102   0.02619   0.01865  -0.0818   0.9489   0.0425
  -3.250   0.0442   0.02452   0.01677  -0.0834   0.9406   0.0455
  -3.000   0.0811   0.02291   0.01466  -0.0850   0.9333   0.0523
  -2.750   0.1151   0.02120   0.01264  -0.0862   0.9245   0.0568
  -2.500   0.1474   0.02032   0.01158  -0.0869   0.9142   0.0633
  -2.250   0.1822   0.01927   0.01015  -0.0877   0.9050   0.0681
  -2.000   0.2131   0.01831   0.00921  -0.0882   0.8933   0.0732
  -1.750   0.2436   0.01753   0.00831  -0.0883   0.8802   0.0767
  -1.500   0.2739   0.01688   0.00753  -0.0884   0.8665   0.0808
  -1.250   0.3035   0.01630   0.00699  -0.0884   0.8519   0.0871
  -1.000   0.3329   0.01580   0.00644  -0.0883   0.8364   0.0926
  -0.750   0.3621   0.01535   0.00591  -0.0880   0.8199   0.0981
  -0.500   0.3904   0.01501   0.00553  -0.0877   0.8014   0.1072
  -0.250   0.4187   0.01473   0.00519  -0.0873   0.7826   0.1244
   0.000   0.4473   0.01439   0.00487  -0.0871   0.7634   0.1584
   0.250   0.4737   0.01213   0.00468  -0.0862   0.7451   1.0000
   0.500   0.5014   0.01225   0.00451  -0.0857   0.7249   1.0000
   0.750   0.5287   0.01239   0.00441  -0.0852   0.7044   1.0000
   1.000   0.5555   0.01255   0.00433  -0.0846   0.6828   1.0000
   1.250   0.5818   0.01274   0.00430  -0.0840   0.6590   1.0000
   1.500   0.6080   0.01294   0.00429  -0.0834   0.6356   1.0000
   1.750   0.6338   0.01316   0.00430  -0.0827   0.6117   1.0000
   2.000   0.6597   0.01339   0.00435  -0.0821   0.5895   1.0000
   2.250   0.6856   0.01364   0.00443  -0.0816   0.5700   1.0000
   2.500   0.7118   0.01389   0.00457  -0.0812   0.5543   1.0000
   2.750   0.7382   0.01415   0.00473  -0.0808   0.5407   1.0000
   3.000   0.7645   0.01442   0.00492  -0.0804   0.5281   1.0000
   3.250   0.7908   0.01470   0.00514  -0.0801   0.5161   1.0000
   3.500   0.8169   0.01499   0.00537  -0.0797   0.5040   1.0000
   3.750   0.8429   0.01527   0.00563  -0.0793   0.4912   1.0000
   4.000   0.8688   0.01556   0.00593  -0.0789   0.4783   1.0000
   4.250   0.8945   0.01586   0.00622  -0.0785   0.4650   1.0000
   4.500   0.9200   0.01617   0.00653  -0.0781   0.4513   1.0000
   4.750   0.9453   0.01649   0.00685  -0.0776   0.4373   1.0000
   5.000   0.9704   0.01681   0.00722  -0.0771   0.4228   1.0000
   5.250   0.9952   0.01714   0.00758  -0.0766   0.4069   1.0000
   5.500   1.0196   0.01749   0.00795  -0.0760   0.3883   1.0000
   5.750   1.0432   0.01787   0.00833  -0.0753   0.3675   1.0000
   6.000   1.0668   0.01826   0.00875  -0.0746   0.3447   1.0000
   6.250   1.0899   0.01871   0.00917  -0.0739   0.3240   1.0000
   6.500   1.1128   0.01920   0.00966  -0.0732   0.3046   1.0000
   6.750   1.1353   0.01974   0.01021  -0.0724   0.2871   1.0000
   7.000   1.1572   0.02034   0.01079  -0.0716   0.2705   1.0000
   7.250   1.1788   0.02096   0.01142  -0.0708   0.2558   1.0000
   7.500   1.2004   0.02159   0.01210  -0.0700   0.2434   1.0000
   7.750   1.2216   0.02226   0.01285  -0.0691   0.2318   1.0000
   8.000   1.2421   0.02296   0.01361  -0.0682   0.2199   1.0000
   8.250   1.2619   0.02369   0.01440  -0.0672   0.2064   1.0000
   8.500   1.2811   0.02444   0.01525  -0.0661   0.1928   1.0000
   8.750   1.2999   0.02521   0.01613  -0.0650   0.1775   1.0000
   9.000   1.3183   0.02600   0.01712  -0.0638   0.1608   1.0000
   9.250   1.3358   0.02686   0.01812  -0.0625   0.1406   1.0000
   9.500   1.3509   0.02790   0.01919  -0.0610   0.1198   1.0000
   9.750   1.3630   0.02914   0.02039  -0.0592   0.1048   1.0000
  10.000   1.3721   0.03057   0.02179  -0.0571   0.0953   1.0000
  10.250   1.3769   0.03224   0.02343  -0.0546   0.0877   1.0000
  10.500   1.3818   0.03379   0.02510  -0.0521   0.0804   1.0000
  10.750   1.3801   0.03584   0.02718  -0.0493   0.0741   1.0000
  11.000   1.3864   0.03741   0.02898  -0.0474   0.0676   1.0000
  11.250   1.3873   0.03943   0.03114  -0.0454   0.0624   1.0000
  11.500   1.3875   0.04162   0.03349  -0.0436   0.0579   1.0000
  11.750   1.3897   0.04376   0.03585  -0.0423   0.0524   1.0000
  12.000   1.3850   0.04666   0.03883  -0.0413   0.0486   1.0000
  12.250   1.3845   0.04939   0.04180  -0.0406   0.0438   1.0000
  12.500   1.3798   0.05272   0.04528  -0.0404   0.0402   1.0000
  12.750   1.3724   0.05658   0.04925  -0.0406   0.0373   1.0000
  13.000   1.3663   0.06051   0.05339  -0.0411   0.0341   1.0000
  13.250   1.3579   0.06493   0.05795  -0.0421   0.0320   1.0000
  13.500   1.3469   0.06987   0.06299  -0.0435   0.0308   1.0000
  13.750   1.3378   0.07463   0.06791  -0.0446   0.0293   1.0000
  14.000   1.3287   0.07949   0.07297  -0.0458   0.0278   1.0000
  14.250   1.3191   0.08458   0.07823  -0.0474   0.0266   1.0000
  14.500   1.3090   0.08989   0.08368  -0.0492   0.0256   1.0000
  14.750   1.2984   0.09543   0.08935  -0.0514   0.0247   1.0000
  15.000   1.2875   0.10118   0.09524  -0.0538   0.0240   1.0000
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