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GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 376 AIRFOIL (goe376-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.75 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe376-il-1000000.txt
Download as CSV file: xf-goe376-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 376 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2453   0.08595   0.08449  -0.0225   1.0000   0.0116
  -8.250  -0.2461   0.08274   0.08129  -0.0231   1.0000   0.0124
  -8.000  -0.2480   0.07991   0.07849  -0.0231   1.0000   0.0124
  -7.750  -0.2504   0.07702   0.07563  -0.0233   0.9998   0.0125
  -7.500  -0.2380   0.07238   0.07098  -0.0284   0.9975   0.0125
  -7.250  -0.2257   0.06780   0.06640  -0.0334   0.9932   0.0125
  -6.500  -0.2500   0.07088   0.06938  -0.0409   0.9886   0.0128
  -6.250  -0.2227   0.06722   0.06571  -0.0464   0.9848   0.0130
  -6.000  -0.1994   0.06422   0.06269  -0.0505   0.9766   0.0135
   0.000   0.4690   0.01237   0.00655  -0.0832   0.5756   0.0301
   0.250   0.4921   0.01081   0.00475  -0.0822   0.5533   0.0314
   0.500   0.5166   0.01042   0.00427  -0.0815   0.5282   0.0324
   0.750   0.5415   0.01019   0.00394  -0.0809   0.5060   0.0339
   1.000   0.5668   0.01006   0.00370  -0.0802   0.4864   0.0356
   1.250   0.5927   0.01045   0.00398  -0.0797   0.4692   0.0377
   2.500   0.7173   0.00897   0.00222  -0.0761   0.4071   0.0355
   2.750   0.7425   0.00882   0.00204  -0.0754   0.3978   0.0338
   3.000   0.7679   0.00879   0.00198  -0.0748   0.3894   0.0341
   3.250   0.7935   0.00879   0.00195  -0.0743   0.3804   0.0343
   3.500   0.8192   0.00880   0.00195  -0.0738   0.3714   0.0348
   3.750   0.8446   0.00886   0.00198  -0.0732   0.3613   0.0357
   4.000   0.8702   0.00892   0.00201  -0.0727   0.3502   0.0358
   4.250   0.8957   0.00900   0.00207  -0.0722   0.3382   0.0359
   4.500   0.9207   0.00914   0.00214  -0.0717   0.3213   0.0367
   4.750   0.9450   0.00934   0.00224  -0.0710   0.2988   0.0388
   5.000   1.0178   0.00836   0.00282  -0.0824   0.2545   1.0000
   5.250   1.0407   0.00867   0.00302  -0.0815   0.2353   1.0000
   5.500   1.0640   0.00895   0.00321  -0.0806   0.2203   1.0000
   5.750   1.0876   0.00920   0.00341  -0.0798   0.2075   1.0000
   6.000   1.1108   0.00948   0.00363  -0.0790   0.1930   1.0000
   6.250   1.1335   0.00980   0.00387  -0.0781   0.1765   1.0000
   6.500   1.1559   0.01015   0.00412  -0.0771   0.1572   1.0000
   6.750   1.1758   0.01071   0.00449  -0.0758   0.1256   1.0000
   7.000   1.1922   0.01158   0.00505  -0.0739   0.0798   1.0000
   7.250   1.2027   0.01301   0.00610  -0.0710   0.0176   1.0000
   7.500   1.2243   0.01341   0.00655  -0.0699   0.0153   1.0000
   7.750   1.2452   0.01389   0.00707  -0.0687   0.0136   1.0000
   8.000   1.2649   0.01445   0.00772  -0.0672   0.0123   1.0000
   8.250   1.2859   0.01487   0.00819  -0.0661   0.0119   1.0000
   8.500   1.3060   0.01537   0.00874  -0.0648   0.0113   1.0000
   8.750   1.3254   0.01590   0.00932  -0.0634   0.0106   1.0000
   9.000   1.3439   0.01649   0.00996  -0.0619   0.0100   1.0000
   9.250   1.3606   0.01720   0.01074  -0.0601   0.0096   1.0000
   9.500   1.3670   0.01868   0.01240  -0.0567   0.0088   1.0000
   9.750   1.3835   0.01930   0.01307  -0.0549   0.0087   1.0000
  10.000   1.3985   0.01997   0.01381  -0.0530   0.0085   1.0000
  10.250   1.4119   0.02072   0.01463  -0.0508   0.0082   1.0000
  10.500   1.4215   0.02150   0.01548  -0.0479   0.0080   1.0000
  10.750   1.4299   0.02228   0.01633  -0.0449   0.0077   1.0000
  11.000   1.4352   0.02329   0.01743  -0.0417   0.0075   1.0000
  11.250   1.4420   0.02429   0.01850  -0.0390   0.0073   1.0000
  11.500   1.4477   0.02541   0.01970  -0.0364   0.0071   1.0000
  11.750   1.4506   0.02680   0.02118  -0.0337   0.0070   1.0000
  12.000   1.4587   0.02791   0.02234  -0.0320   0.0067   1.0000
  12.250   1.4591   0.02970   0.02421  -0.0299   0.0065   1.0000
  12.500   1.4518   0.03234   0.02695  -0.0278   0.0063   1.0000
  12.750   1.4435   0.03536   0.03008  -0.0261   0.0062   1.0000
  13.000   1.4266   0.03953   0.03437  -0.0243   0.0061   1.0000
  13.250   1.4271   0.04208   0.03701  -0.0238   0.0060   1.0000
  13.500   1.4317   0.04435   0.03941  -0.0238   0.0059   1.0000
  13.750   1.4336   0.04697   0.04214  -0.0239   0.0058   1.0000
  14.000   1.4310   0.05015   0.04542  -0.0239   0.0058   1.0000
  14.250   1.4269   0.05359   0.04898  -0.0241   0.0057   1.0000
  14.500   1.4245   0.05698   0.05247  -0.0246   0.0056   1.0000
  14.750   1.4188   0.06082   0.05642  -0.0251   0.0056   1.0000
  15.000   1.4131   0.06474   0.06045  -0.0258   0.0056   1.0000
  15.250   1.4080   0.06880   0.06463  -0.0269   0.0054   1.0000
  15.500   1.4001   0.07318   0.06913  -0.0277   0.0055   1.0000
  15.750   1.3929   0.07767   0.07373  -0.0289   0.0054   1.0000
  16.000   1.3856   0.08233   0.07850  -0.0304   0.0054   1.0000
  16.250   1.3781   0.08717   0.08346  -0.0322   0.0053   1.0000
  16.500   1.3681   0.09235   0.08876  -0.0339   0.0052   1.0000
  16.750   1.3586   0.09755   0.09408  -0.0357   0.0053   1.0000
  17.000   1.3478   0.10315   0.09980  -0.0379   0.0052   1.0000
  17.250   1.3380   0.10873   0.10549  -0.0403   0.0052   1.0000
  17.500   1.3290   0.11435   0.11122  -0.0430   0.0050   1.0000
  17.750   1.3151   0.12079   0.11780  -0.0458   0.0051   1.0000
  18.000   1.3036   0.12707   0.12419  -0.0488   0.0051   1.0000
  18.250   1.2931   0.13329   0.13053  -0.0520   0.0051   1.0000
  18.500   1.2825   0.13975   0.13709  -0.0555   0.0050   1.0000
  18.750   1.2677   0.14720   0.14468  -0.0595   0.0050   1.0000
  19.000   1.2533   0.15492   0.15254  -0.0639   0.0051   1.0000
  19.250   1.2446   0.16157   0.15927  -0.0679   0.0050   1.0000
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