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GOE 309 (MVA H.41) AIRFOIL (goe309-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 309 (MVA H.41) AIRFOIL (goe309-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.8 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe309-il-1000000.txt
Download as CSV file: xf-goe309-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 309 (MVA H.41) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3637   0.08521   0.08381  -0.0199   0.9923   0.0118
  -7.500  -0.3521   0.08092   0.07950  -0.0255   0.9679   0.0128
  -7.000  -0.4213   0.01822   0.01477  -0.0520   0.9141   0.0111
  -6.750  -0.3955   0.01839   0.01492  -0.0514   0.8943   0.0116
  -6.500  -0.3718   0.01754   0.01386  -0.0507   0.8710   0.0121
  -6.250  -0.2907   0.05889   0.05688  -0.0423   0.8375   0.0139
  -6.000  -0.2790   0.05385   0.05167  -0.0445   0.8183   0.0133
  -5.750  -0.2992   0.01349   0.00875  -0.0490   0.8132   0.0145
  -5.500  -0.2717   0.01347   0.00869  -0.0489   0.7986   0.0153
  -5.250  -0.2436   0.01367   0.00887  -0.0489   0.7859   0.0160
  -5.000  -0.2156   0.01373   0.00887  -0.0489   0.7744   0.0170
  -4.750  -0.1877   0.01366   0.00871  -0.0488   0.7638   0.0181
  -4.500  -0.1596   0.01375   0.00870  -0.0488   0.7537   0.0187
  -4.250  -0.1338   0.01228   0.00700  -0.0485   0.7447   0.0204
  -4.000  -0.1058   0.01228   0.00697  -0.0486   0.7361   0.0214
  -3.750  -0.0778   0.01219   0.00681  -0.0486   0.7272   0.0227
  -3.500  -0.0496   0.01207   0.00662  -0.0486   0.7186   0.0241
  -3.250  -0.0215   0.01202   0.00648  -0.0486   0.7102   0.0250
  -3.000   0.0058   0.01100   0.00526  -0.0484   0.7022   0.0262
  -2.750   0.0329   0.01029   0.00447  -0.0483   0.6944   0.0281
  -2.500   0.0610   0.01003   0.00416  -0.0483   0.6857   0.0295
  -2.250   0.0889   0.00974   0.00380  -0.0483   0.6771   0.0307
  -2.000   0.1168   0.00949   0.00348  -0.0482   0.6681   0.0319
  -1.750   0.1448   0.00924   0.00318  -0.0482   0.6593   0.0329
  -1.500   0.1726   0.00898   0.00285  -0.0482   0.6501   0.0334
  -1.250   0.2005   0.00877   0.00257  -0.0481   0.6398   0.0339
  -1.000   0.2285   0.00859   0.00234  -0.0481   0.6281   0.0344
  -0.750   0.2561   0.00836   0.00202  -0.0480   0.6148   0.0354
  -0.500   0.2837   0.00813   0.00170  -0.0479   0.6002   0.0380
  -0.250   0.3116   0.00804   0.00155  -0.0479   0.5849   0.0403
   0.000   0.3396   0.00800   0.00145  -0.0479   0.5701   0.0423
   0.250   0.3675   0.00798   0.00136  -0.0479   0.5546   0.0447
   0.750   0.4231   0.00795   0.00135  -0.0480   0.5206   0.0988
   1.000   0.4511   0.00799   0.00136  -0.0481   0.5046   0.1107
   1.250   0.4790   0.00803   0.00137  -0.0482   0.4914   0.1206
   1.500   0.5070   0.00807   0.00138  -0.0483   0.4798   0.1293
   1.750   0.5350   0.00807   0.00140  -0.0484   0.4696   0.1449
   2.000   0.5624   0.00792   0.00150  -0.0486   0.4603   0.2658
   2.250   0.5779   0.00637   0.00161  -0.0464   0.4522   0.9000
   2.500   0.6005   0.00637   0.00170  -0.0449   0.4443   0.9583
   2.750   0.6360   0.00650   0.00179  -0.0465   0.4354   0.9861
   3.000   0.6775   0.00664   0.00190  -0.0496   0.4263   0.9942
   3.250   0.7193   0.00677   0.00199  -0.0529   0.4176   0.9969
   3.500   0.7568   0.00693   0.00208  -0.0552   0.4076   0.9991
   4.000   0.8122   0.00718   0.00224  -0.0555   0.3820   1.0000
   4.250   0.8364   0.00735   0.00233  -0.0549   0.3645   1.0000
   4.500   0.8601   0.00758   0.00244  -0.0543   0.3368   1.0000
   4.750   0.8834   0.00789   0.00260  -0.0536   0.3043   1.0000
   5.000   0.9053   0.00836   0.00284  -0.0527   0.2593   1.0000
   5.250   0.9260   0.00900   0.00319  -0.0518   0.2090   1.0000
   5.500   0.9474   0.00957   0.00353  -0.0509   0.1704   1.0000
   5.750   0.9681   0.01022   0.00391  -0.0499   0.1261   1.0000
   6.000   0.9814   0.01182   0.00498  -0.0479   0.0188   1.0000
   6.250   1.0055   0.01215   0.00533  -0.0474   0.0153   1.0000
   6.500   1.0298   0.01247   0.00570  -0.0469   0.0139   1.0000
   6.750   1.0539   0.01283   0.00612  -0.0464   0.0130   1.0000
   7.000   1.0775   0.01325   0.00658  -0.0458   0.0121   1.0000
   7.250   1.1004   0.01373   0.00711  -0.0452   0.0113   1.0000
   7.500   1.1220   0.01437   0.00782  -0.0443   0.0105   1.0000
   7.750   1.1400   0.01538   0.00896  -0.0430   0.0096   1.0000
   8.000   1.1631   0.01578   0.00940  -0.0424   0.0092   1.0000
   8.250   1.1840   0.01640   0.01007  -0.0415   0.0088   1.0000
   8.500   1.2035   0.01711   0.01084  -0.0405   0.0084   1.0000
   8.750   1.2219   0.01788   0.01167  -0.0393   0.0081   1.0000
   9.000   1.2391   0.01868   0.01254  -0.0380   0.0078   1.0000
   9.250   1.2550   0.01954   0.01346  -0.0365   0.0075   1.0000
   9.500   1.2686   0.02050   0.01447  -0.0348   0.0072   1.0000
   9.750   1.2766   0.02169   0.01572  -0.0322   0.0069   1.0000
  10.000   1.2741   0.02333   0.01743  -0.0283   0.0067   1.0000
  10.250   1.2672   0.02564   0.01981  -0.0244   0.0066   1.0000
  10.500   1.2699   0.02751   0.02176  -0.0220   0.0064   1.0000
  10.750   1.2840   0.02835   0.02269  -0.0211   0.0062   1.0000
  11.000   1.2939   0.02966   0.02408  -0.0200   0.0060   1.0000
  11.250   1.3003   0.03141   0.02591  -0.0186   0.0059   1.0000
  11.500   1.3064   0.03329   0.02787  -0.0172   0.0058   1.0000
  11.750   1.3130   0.03519   0.02986  -0.0159   0.0057   1.0000
  12.000   1.3200   0.03713   0.03187  -0.0147   0.0056   1.0000
  12.250   1.3273   0.03911   0.03393  -0.0134   0.0056   1.0000
  12.500   1.3345   0.04116   0.03608  -0.0122   0.0055   1.0000
  12.750   1.3407   0.04334   0.03836  -0.0110   0.0054   1.0000
  13.000   1.3455   0.04566   0.04079  -0.0101   0.0053   1.0000
  13.250   1.3490   0.04820   0.04346  -0.0092   0.0053   1.0000
  13.500   1.3503   0.05100   0.04640  -0.0083   0.0052   1.0000
  13.750   1.3494   0.05412   0.04966  -0.0077   0.0052   1.0000
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