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GOE 441 AIRFOIL (goe441-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 441 AIRFOIL (goe441-il)
Reynolds number: 1,000,000
Max Cl/Cd: 132.37 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe441-il-1000000.txt
Download as CSV file: xf-goe441-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 441 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.0241   0.10697   0.10444  -0.0892   0.8126   0.0298
 -11.000  -0.0120   0.10499   0.10243  -0.0897   0.8020   0.0300
 -10.750  -0.2961   0.02546   0.02190  -0.1737   0.8006   0.0291
 -10.500  -0.2662   0.02302   0.01919  -0.1793   0.7918   0.0293
 -10.250  -0.2369   0.02150   0.01747  -0.1823   0.7832   0.0295
 -10.000  -0.2080   0.02044   0.01621  -0.1844   0.7752   0.0296
  -9.750  -0.1795   0.01811   0.01364  -0.1877   0.7684   0.0300
  -9.500  -0.1507   0.01703   0.01244  -0.1891   0.7614   0.0303
  -9.250  -0.1214   0.01635   0.01167  -0.1902   0.7552   0.0306
  -9.000  -0.0919   0.01580   0.01107  -0.1910   0.7482   0.0310
  -8.750  -0.0627   0.01533   0.01049  -0.1917   0.7407   0.0313
  -8.500  -0.0329   0.01480   0.00988  -0.1925   0.7339   0.0317
  -8.250  -0.0033   0.01429   0.00927  -0.1932   0.7254   0.0320
  -8.000   0.0264   0.01383   0.00870  -0.1938   0.7174   0.0323
  -7.750   0.0563   0.01339   0.00817  -0.1945   0.7092   0.0326
  -7.500   0.0858   0.01301   0.00768  -0.1950   0.7001   0.0330
  -7.250   0.1158   0.01265   0.00724  -0.1955   0.6896   0.0333
  -7.000   0.1453   0.01238   0.00686  -0.1958   0.6763   0.0336
  -6.750   0.1746   0.01198   0.00632  -0.1963   0.6560   0.0339
  -6.500   0.2023   0.01166   0.00578  -0.1966   0.6105   0.0346
  -6.250   0.2279   0.01174   0.00555  -0.1963   0.5534   0.0351
  -6.000   0.2563   0.01167   0.00535  -0.1964   0.5337   0.0357
  -5.750   0.2851   0.01158   0.00515  -0.1967   0.5218   0.0363
  -5.500   0.3148   0.01144   0.00495  -0.1970   0.5145   0.0370
  -5.250   0.3441   0.01134   0.00477  -0.1973   0.5077   0.0377
  -5.000   0.3732   0.01127   0.00461  -0.1975   0.5006   0.0383
  -4.750   0.4038   0.01098   0.00431  -0.1981   0.4967   0.0396
  -4.500   0.4336   0.01086   0.00415  -0.1984   0.4923   0.0407
  -4.250   0.4631   0.01079   0.00403  -0.1987   0.4879   0.0419
  -4.000   0.4921   0.01077   0.00394  -0.1988   0.4829   0.0430
  -3.750   0.5224   0.01059   0.00376  -0.1993   0.4798   0.0452
  -3.500   0.5523   0.01049   0.00365  -0.1996   0.4770   0.0475
  -3.250   0.5823   0.01038   0.00353  -0.2000   0.4736   0.0508
  -3.000   0.6118   0.01032   0.00344  -0.2002   0.4699   0.0552
  -2.750   0.6409   0.01028   0.00339  -0.2004   0.4659   0.0625
  -2.500   0.6698   0.01028   0.00341  -0.2006   0.4620   0.0728
  -2.250   0.6994   0.01025   0.00343  -0.2009   0.4601   0.0824
  -2.000   0.7288   0.01025   0.00345  -0.2010   0.4577   0.0890
  -1.750   0.7577   0.01030   0.00348  -0.2011   0.4548   0.0939
  -1.500   0.7867   0.01030   0.00348  -0.2013   0.4516   0.0987
  -1.250   0.8152   0.01036   0.00351  -0.2014   0.4482   0.1030
  -1.000   0.8430   0.01049   0.00359  -0.2013   0.4443   0.1060
  -0.750   0.8723   0.01045   0.00357  -0.2015   0.4423   0.1109
  -0.500   0.9016   0.01044   0.00357  -0.2018   0.4402   0.1150
  -0.250   0.9305   0.01046   0.00358  -0.2019   0.4377   0.1184
   0.000   0.9593   0.01046   0.00359  -0.2021   0.4349   0.1244
   0.250   0.9878   0.01050   0.00362  -0.2022   0.4321   0.1306
   0.500   1.0158   0.01056   0.00368  -0.2022   0.4290   0.1388
   0.750   1.0435   0.01064   0.00380  -0.2022   0.4252   0.1636
   1.000   1.0727   0.01061   0.00387  -0.2025   0.4235   0.2003
   1.250   1.1015   0.01061   0.00393  -0.2027   0.4214   0.2233
   1.500   1.1300   0.01062   0.00399  -0.2028   0.4189   0.2449
   1.750   1.1583   0.01063   0.00408  -0.2030   0.4161   0.2804
   2.000   1.1866   0.01061   0.00422  -0.2032   0.4131   0.3657
   2.250   1.2135   0.01073   0.00439  -0.2031   0.4095   0.4134
   2.500   1.2407   0.01082   0.00454  -0.2030   0.4067   0.4439
   2.750   1.2687   0.01087   0.00464  -0.2031   0.4047   0.4650
   3.000   1.2964   0.01094   0.00474  -0.2030   0.4022   0.4828
   3.250   1.3235   0.01104   0.00486  -0.2029   0.3995   0.4993
   3.500   1.3501   0.01116   0.00499  -0.2027   0.3967   0.5168
   3.750   1.3759   0.01131   0.00515  -0.2024   0.3935   0.5367
   4.000   1.4013   0.01148   0.00536  -0.2020   0.3901   0.5621
   4.250   1.4286   0.01153   0.00550  -0.2020   0.3886   0.5947
   4.500   1.4558   0.01156   0.00568  -0.2020   0.3865   0.6519
   4.750   1.4824   0.01156   0.00589  -0.2019   0.3841   0.7541
   5.000   1.5024   0.01135   0.00602  -0.2003   0.3815   1.0000
   5.250   1.5271   0.01155   0.00619  -0.1998   0.3785   1.0000
   5.500   1.5505   0.01180   0.00640  -0.1991   0.3750   1.0000
   5.750   1.5748   0.01201   0.00660  -0.1985   0.3725   1.0000
   6.000   1.6000   0.01215   0.00676  -0.1981   0.3706   1.0000
   6.250   1.6237   0.01231   0.00693  -0.1974   0.3682   1.0000
   6.500   1.6463   0.01250   0.00713  -0.1966   0.3656   1.0000
   6.750   1.6682   0.01274   0.00736  -0.1956   0.3628   1.0000
   7.000   1.6890   0.01303   0.00763  -0.1945   0.3596   1.0000
   7.250   1.7095   0.01335   0.00794  -0.1933   0.3564   1.0000
   7.500   1.7333   0.01352   0.00814  -0.1927   0.3539   1.0000
   7.750   1.7557   0.01374   0.00838  -0.1919   0.3500   1.0000
   8.000   1.7760   0.01406   0.00868  -0.1908   0.3454   1.0000
   8.250   1.7941   0.01449   0.00908  -0.1894   0.3403   1.0000
   8.500   1.8170   0.01471   0.00933  -0.1887   0.3368   1.0000
   8.750   1.8375   0.01504   0.00966  -0.1877   0.3323   1.0000
   9.000   1.8553   0.01550   0.01010  -0.1863   0.3271   1.0000
   9.250   1.8748   0.01589   0.01050  -0.1852   0.3222   1.0000
   9.500   1.8944   0.01628   0.01091  -0.1842   0.3174   1.0000
   9.750   1.9112   0.01682   0.01143  -0.1827   0.3118   1.0000
  10.000   1.9287   0.01733   0.01195  -0.1814   0.3069   1.0000
  10.250   1.9466   0.01783   0.01246  -0.1802   0.3012   1.0000
  10.500   1.9602   0.01859   0.01318  -0.1784   0.2941   1.0000
  10.750   1.9775   0.01914   0.01376  -0.1772   0.2888   1.0000
  11.000   1.9913   0.01991   0.01452  -0.1756   0.2817   1.0000
  11.250   2.0043   0.02075   0.01534  -0.1739   0.2744   1.0000
  11.500   2.0149   0.02175   0.01632  -0.1720   0.2655   1.0000
  11.750   2.0265   0.02272   0.01729  -0.1702   0.2576   1.0000
  12.000   2.0330   0.02405   0.01858  -0.1680   0.2483   1.0000
  12.250   2.0427   0.02520   0.01972  -0.1662   0.2395   1.0000
  12.500   2.0480   0.02669   0.02119  -0.1640   0.2304   1.0000
  12.750   2.0489   0.02855   0.02301  -0.1616   0.2193   1.0000
  13.000   2.0493   0.03052   0.02495  -0.1592   0.2074   1.0000
  13.250   2.0451   0.03295   0.02733  -0.1566   0.1937   1.0000
  13.500   2.0355   0.03597   0.03028  -0.1538   0.1782   1.0000
  13.750   2.0182   0.03982   0.03405  -0.1507   0.1579   1.0000
  14.000   1.9911   0.04487   0.03902  -0.1475   0.1371   1.0000
  14.250   1.9625   0.05036   0.04447  -0.1448   0.1200   1.0000
  14.500   1.9359   0.05598   0.05008  -0.1426   0.1072   1.0000
  14.750   1.9076   0.06209   0.05623  -0.1410   0.0955   1.0000
  15.000   1.8728   0.06938   0.06353  -0.1397   0.0787   1.0000
  15.250   1.8375   0.07706   0.07124  -0.1390   0.0637   1.0000
  15.500   1.8027   0.08487   0.07910  -0.1387   0.0527   1.0000
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