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GOE 311 (MVA H.43) AIRFOIL (goe311-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 311 (MVA H.43) AIRFOIL (goe311-il)
Reynolds number: 200,000
Max Cl/Cd: 82.42 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe311-il-200000.txt
Download as CSV file: xf-goe311-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 311 (MVA H.43) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2755   0.09856   0.09540  -0.0297   1.0000   0.0428
  -8.000  -0.2816   0.09724   0.09417  -0.0316   1.0000   0.0435
  -7.750  -0.3010   0.09697   0.09401  -0.0288   1.0000   0.0437
  -7.500  -0.2911   0.09398   0.09105  -0.0361   0.9946   0.0440
  -7.250  -0.2598   0.08863   0.08565  -0.0469   0.9869   0.0442
  -7.000  -0.2368   0.08153   0.07855  -0.0530   0.9825   0.0447
  -6.750  -0.2197   0.07774   0.07477  -0.0502   0.9773   0.0464
  -6.500  -0.1911   0.07393   0.07093  -0.0548   0.9707   0.0489
  -6.250  -0.1647   0.06982   0.06678  -0.0610   0.9589   0.0512
  -6.000  -0.1252   0.06526   0.06202  -0.0743   0.9435   0.0552
  -5.750  -0.0999   0.06112   0.05773  -0.0789   0.9289   0.0556
  -5.500  -0.0936   0.05620   0.05282  -0.0782   0.9147   0.0568
  -5.250  -0.0813   0.05411   0.05071  -0.0762   0.9001   0.0584
  -5.000  -0.0640   0.05205   0.04858  -0.0759   0.8851   0.0627
  -4.750  -0.0372   0.04779   0.04410  -0.0800   0.8702   0.0700
  -4.500  -0.0198   0.04608   0.04232  -0.0788   0.8546   0.0743
  -4.250   0.0071   0.04253   0.03852  -0.0812   0.8387   0.0827
  -4.000   0.0410   0.03176   0.02706  -0.0861   0.8260   0.0649
  -3.750   0.0538   0.03830   0.03394  -0.0814   0.8037   0.1003
  -3.500   0.0845   0.03402   0.02923  -0.0834   0.7876   0.1020
  -3.250   0.1178   0.02451   0.01870  -0.0862   0.7751   0.0866
  -3.000   0.1454   0.02100   0.01448  -0.0863   0.7591   0.0903
  -2.750   0.1725   0.01872   0.01157  -0.0861   0.7429   0.0914
  -2.500   0.1998   0.01734   0.00972  -0.0858   0.7274   0.0919
  -2.250   0.2271   0.01630   0.00835  -0.0856   0.7132   0.0929
  -2.000   0.2545   0.01570   0.00758  -0.0854   0.7008   0.0945
  -1.750   0.2820   0.01546   0.00721  -0.0852   0.6899   0.0971
  -1.500   0.3101   0.01513   0.00674  -0.0851   0.6787   0.1004
  -1.250   0.3381   0.01471   0.00615  -0.0849   0.6694   0.1037
  -1.000   0.3659   0.01438   0.00573  -0.0847   0.6617   0.1077
  -0.750   0.3940   0.01424   0.00558  -0.0847   0.6535   0.1142
  -0.500   0.4219   0.01410   0.00538  -0.0845   0.6468   0.1246
  -0.250   0.4501   0.01408   0.00535  -0.0845   0.6399   0.1428
   0.000   0.4781   0.01414   0.00532  -0.0845   0.6338   0.1601
   0.250   0.5059   0.01419   0.00535  -0.0845   0.6282   0.1730
   0.500   0.5337   0.01421   0.00538  -0.0845   0.6220   0.1837
   0.750   0.5615   0.01427   0.00534  -0.0845   0.6172   0.1930
   1.000   0.5893   0.01425   0.00538  -0.0846   0.6116   0.1987
   1.250   0.6171   0.01428   0.00537  -0.0846   0.6063   0.2044
   1.500   0.6447   0.01429   0.00533  -0.0845   0.6018   0.2095
   1.750   0.6723   0.01432   0.00544  -0.0845   0.5965   0.2158
   2.000   0.6999   0.01436   0.00551  -0.0845   0.5914   0.2249
   2.250   0.7276   0.01448   0.00559  -0.0845   0.5872   0.2365
   2.500   0.7549   0.01452   0.00576  -0.0846   0.5818   0.2471
   2.750   0.7823   0.01455   0.00585  -0.0845   0.5766   0.2566
   3.000   0.8093   0.01459   0.00590  -0.0843   0.5707   0.2687
   3.250   0.8357   0.01456   0.00596  -0.0841   0.5622   0.2896
   3.500   0.8613   0.01434   0.00600  -0.0837   0.5530   0.3851
   3.750   0.8943   0.01337   0.00593  -0.0844   0.5430   1.0000
   4.000   0.9203   0.01354   0.00610  -0.0840   0.5345   1.0000
   4.250   0.9471   0.01378   0.00625  -0.0838   0.5288   1.0000
   4.500   0.9735   0.01401   0.00653  -0.0836   0.5229   1.0000
   4.750   1.0000   0.01422   0.00675  -0.0834   0.5166   1.0000
   5.000   1.0266   0.01449   0.00697  -0.0833   0.5109   1.0000
   5.250   1.0525   0.01467   0.00724  -0.0830   0.5036   1.0000
   5.500   1.0792   0.01491   0.00745  -0.0828   0.4976   1.0000
   5.750   1.1046   0.01509   0.00776  -0.0825   0.4902   1.0000
   6.000   1.1310   0.01528   0.00796  -0.0822   0.4836   1.0000
   6.250   1.1564   0.01547   0.00828  -0.0819   0.4760   1.0000
   6.500   1.1822   0.01560   0.00844  -0.0816   0.4682   1.0000
   6.750   1.2066   0.01565   0.00862  -0.0810   0.4569   1.0000
   7.000   1.2306   0.01561   0.00865  -0.0803   0.4427   1.0000
   7.250   1.2542   0.01557   0.00870  -0.0796   0.4258   1.0000
   7.500   1.2776   0.01564   0.00882  -0.0788   0.4085   1.0000
   7.750   1.3006   0.01578   0.00905  -0.0781   0.3867   1.0000
   8.000   1.3202   0.01612   0.00926  -0.0769   0.3520   1.0000
   8.250   1.3376   0.01676   0.00976  -0.0754   0.3137   1.0000
   8.500   1.3523   0.01767   0.01048  -0.0737   0.2741   1.0000
   8.750   1.3612   0.01901   0.01149  -0.0713   0.2226   1.0000
   9.000   1.3672   0.02056   0.01271  -0.0686   0.1700   1.0000
   9.250   1.3597   0.02296   0.01450  -0.0644   0.0901   1.0000
   9.500   1.3580   0.02466   0.01611  -0.0605   0.0670   1.0000
   9.750   1.3563   0.02650   0.01778  -0.0572   0.0395   1.0000
  10.000   1.3582   0.02824   0.01952  -0.0545   0.0336   1.0000
  10.250   1.3615   0.02999   0.02143  -0.0524   0.0311   1.0000
  10.500   1.3615   0.03213   0.02369  -0.0503   0.0290   1.0000
  10.750   1.3583   0.03474   0.02643  -0.0486   0.0273   1.0000
  11.000   1.3547   0.03758   0.02942  -0.0473   0.0264   1.0000
  11.250   1.3536   0.04034   0.03234  -0.0463   0.0258   1.0000
  11.500   1.3511   0.04334   0.03549  -0.0455   0.0253   1.0000
  11.750   1.3479   0.04650   0.03877  -0.0449   0.0249   1.0000
  12.000   1.3445   0.04972   0.04212  -0.0443   0.0244   1.0000
  12.250   1.3414   0.05292   0.04543  -0.0437   0.0241   1.0000
  12.500   1.3390   0.05605   0.04865  -0.0430   0.0237   1.0000
  12.750   1.3379   0.05900   0.05170  -0.0423   0.0234   1.0000
  13.000   1.3383   0.06174   0.05452  -0.0414   0.0230   1.0000
  13.250   1.3400   0.06435   0.05721  -0.0405   0.0225   1.0000
  13.500   1.3426   0.06683   0.05974  -0.0395   0.0218   1.0000
  13.750   1.3475   0.06890   0.06181  -0.0380   0.0210   1.0000
  14.000   1.3609   0.06994   0.06284  -0.0349   0.0204   1.0000
  14.250   1.3773   0.07130   0.06430  -0.0322   0.0202   1.0000
  14.500   1.3889   0.07357   0.06675  -0.0306   0.0201   1.0000
  14.750   1.3949   0.07639   0.06975  -0.0296   0.0201   1.0000
  15.000   1.3967   0.07956   0.07311  -0.0292   0.0202   1.0000
  15.250   1.3951   0.08307   0.07683  -0.0292   0.0204   1.0000
  15.500   1.3904   0.08694   0.08095  -0.0297   0.0206   1.0000
  15.750   1.3823   0.09134   0.08561  -0.0307   0.0209   1.0000
  16.000   1.3704   0.09655   0.09112  -0.0321   0.0213   1.0000
  16.250   1.3530   0.10297   0.09790  -0.0342   0.0220   1.0000
  16.500   1.3317   0.11033   0.10559  -0.0373   0.0226   1.0000
  16.750   1.3110   0.11786   0.11341  -0.0407   0.0232   1.0000
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