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GOE 449 AIRFOIL (goe449-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 449 AIRFOIL (goe449-il)
Reynolds number: 100,000
Max Cl/Cd: 34.69 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe449-il-100000.txt
Download as CSV file: xf-goe449-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 449 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2144   0.11736   0.11256  -0.0654   0.9557   0.1394
  -9.250  -0.2154   0.11490   0.11011  -0.0666   0.9495   0.1438
  -9.000  -0.2827   0.11331   0.10864  -0.0751   0.9405   0.1479
  -8.750  -0.2100   0.10762   0.10286  -0.0729   0.9401   0.1512
  -8.500  -0.1993   0.10567   0.10091  -0.0716   0.9339   0.1550
  -8.250  -0.2050   0.10320   0.09847  -0.0734   0.9273   0.1610
  -8.000  -0.2783   0.10196   0.09735  -0.0756   0.9156   0.1639
  -7.750  -0.2351   0.09725   0.09261  -0.0752   0.9128   0.1670
  -7.500  -0.2018   0.09435   0.08967  -0.0761   0.9093   0.1715
  -7.250  -0.2125   0.09210   0.08744  -0.0763   0.9020   0.1764
  -7.000  -0.3302   0.09030   0.08553  -0.0769   0.8836   0.1816
  -6.750  -0.2948   0.08623   0.08161  -0.0750   0.8800   0.1835
  -6.500  -0.2623   0.08388   0.07928  -0.0742   0.8758   0.1870
  -6.250  -0.3747   0.06297   0.05707  -0.0785   0.8615   0.1189
  -6.000  -0.3420   0.06132   0.05560  -0.0798   0.8566   0.1215
  -5.750  -0.3370   0.05584   0.04957  -0.0792   0.8504   0.1139
  -5.500  -0.3342   0.05280   0.04618  -0.0768   0.8417   0.1126
  -5.250  -0.3100   0.04873   0.04152  -0.0776   0.8377   0.1112
  -5.000  -0.3043   0.04693   0.03938  -0.0747   0.8288   0.1113
  -4.750  -0.2805   0.04494   0.03697  -0.0744   0.8226   0.1135
  -4.500  -0.2440   0.04291   0.03428  -0.0757   0.8191   0.1175
  -4.250  -0.2406   0.04209   0.03331  -0.0722   0.8084   0.1195
  -4.000  -0.2073   0.04092   0.03210  -0.0732   0.8038   0.1236
  -3.750  -0.1665   0.03984   0.03064  -0.0750   0.8009   0.1315
  -3.500  -0.1670   0.03968   0.03042  -0.0710   0.7893   0.1343
  -3.250  -0.1296   0.03879   0.02950  -0.0723   0.7853   0.1425
  -3.000  -0.1146   0.03858   0.02911  -0.0704   0.7770   0.1496
  -2.750  -0.0911   0.03824   0.02882  -0.0699   0.7704   0.1583
  -2.500  -0.0535   0.03745   0.02801  -0.0713   0.7671   0.1707
  -2.250  -0.0473   0.03790   0.02838  -0.0683   0.7575   0.1785
  -2.000  -0.0186   0.03745   0.02800  -0.0684   0.7521   0.1913
  -1.750   0.0209   0.03672   0.02731  -0.0699   0.7492   0.2087
  -1.500   0.0190   0.03765   0.02816  -0.0660   0.7391   0.2172
  -1.250   0.0480   0.03726   0.02788  -0.0661   0.7343   0.2369
  -1.000   0.0861   0.03646   0.02731  -0.0673   0.7316   0.2677
  -0.750   0.0805   0.03743   0.02839  -0.0630   0.7212   0.2842
  -0.500   0.1053   0.03687   0.02825  -0.0625   0.7169   0.3482
  -0.250   0.2756   0.03536   0.02884  -0.0868   0.7182   1.0000
   0.000   0.3107   0.03506   0.02829  -0.0875   0.7150   1.0000
   0.250   0.3516   0.03462   0.02764  -0.0890   0.7131   1.0000
   0.500   0.3119   0.03684   0.02983  -0.0802   0.6993   1.0000
   0.750   0.3497   0.03654   0.02934  -0.0813   0.6968   1.0000
   1.000   0.3901   0.03615   0.02878  -0.0826   0.6949   1.0000
   1.250   0.3530   0.03869   0.03129  -0.0747   0.6813   1.0000
   1.500   0.3922   0.03836   0.03081  -0.0758   0.6791   1.0000
   1.750   0.3644   0.04084   0.03326  -0.0695   0.6666   1.0000
   2.000   0.3978   0.04076   0.03306  -0.0699   0.6635   1.0000
   2.250   0.4385   0.04034   0.03252  -0.0711   0.6615   1.0000
   2.500   0.4093   0.04320   0.03536  -0.0652   0.6487   1.0000
   2.750   0.4463   0.04293   0.03499  -0.0659   0.6459   1.0000
   3.000   0.4887   0.04237   0.03433  -0.0672   0.6441   1.0000
   3.250   0.4590   0.04552   0.03747  -0.0617   0.6308   1.0000
   3.500   0.4990   0.04505   0.03692  -0.0626   0.6284   1.0000
   3.750   0.5432   0.04429   0.03608  -0.0639   0.6268   1.0000
   4.000   0.5144   0.04760   0.03939  -0.0588   0.6129   1.0000
   4.250   0.5579   0.04679   0.03852  -0.0598   0.6108   1.0000
   4.500   0.5361   0.04991   0.04164  -0.0557   0.5978   1.0000
   4.750   0.5764   0.04923   0.04091  -0.0564   0.5951   1.0000
   5.000   0.6225   0.04809   0.03971  -0.0575   0.5933   1.0000
   5.250   0.5992   0.05147   0.04310  -0.0535   0.5793   1.0000
   5.500   0.6438   0.05033   0.04192  -0.0543   0.5772   1.0000
   5.750   0.6926   0.04879   0.04035  -0.0554   0.5759   1.0000
   6.000   0.6667   0.05257   0.04415  -0.0515   0.5610   1.0000
   6.250   0.6525   0.05568   0.04728  -0.0486   0.5481   1.0000
   6.500   0.6906   0.05486   0.04644  -0.0488   0.5448   1.0000
   6.750   0.6842   0.05749   0.04908  -0.0466   0.5332   1.0000
   7.000   0.7156   0.05712   0.04871  -0.0464   0.5286   1.0000
   7.250   0.7573   0.05585   0.04744  -0.0467   0.5263   1.0000
   7.500   0.7403   0.05951   0.05113  -0.0441   0.5123   1.0000
   7.750   0.7818   0.05807   0.04970  -0.0442   0.5096   1.0000
   8.000   0.7676   0.06166   0.05331  -0.0420   0.4960   1.0000
   8.250   0.8038   0.06068   0.05235  -0.0419   0.4927   1.0000
   8.500   0.8161   0.06192   0.05361  -0.0408   0.4849   1.0000
   8.750   0.8815   0.05787   0.04959  -0.0416   0.4873   1.0000
   9.000   0.9388   0.05441   0.04616  -0.0421   0.4881   1.0000
   9.250   0.9993   0.05088   0.04266  -0.0432   0.4885   1.0000
   9.500   1.0713   0.04665   0.03847  -0.0453   0.4884   1.0000
   9.750   1.1941   0.03936   0.03116  -0.0525   0.4882   1.0000
  10.000   1.1431   0.04381   0.03569  -0.0450   0.4737   1.0000
  10.250   1.2809   0.03692   0.02872  -0.0550   0.4719   1.0000
  10.500   1.1176   0.04885   0.04082  -0.0384   0.4502   1.0000
  10.750   1.1385   0.04875   0.04076  -0.0374   0.4421   1.0000
  11.000   1.2407   0.04271   0.03471  -0.0421   0.4407   1.0000
  11.250   1.1843   0.04838   0.04048  -0.0358   0.4267   1.0000
  11.500   1.2905   0.04215   0.03421  -0.0408   0.4235   1.0000
  11.750   1.2492   0.04649   0.03865  -0.0354   0.4118   1.0000
  12.000   1.3399   0.04178   0.03387  -0.0396   0.4059   1.0000
  12.250   1.2970   0.04611   0.03833  -0.0341   0.3950   1.0000
  12.500   1.3969   0.04108   0.03313  -0.0393   0.3871   1.0000
  12.750   1.3406   0.04601   0.03827  -0.0325   0.3768   1.0000
  13.000   1.3791   0.04488   0.03709  -0.0329   0.3675   1.0000
  13.250   1.3940   0.04537   0.03759  -0.0317   0.3574   1.0000
  13.500   1.3833   0.04776   0.04007  -0.0290   0.3479   1.0000
  13.750   1.4390   0.04567   0.03781  -0.0306   0.3374   1.0000
  14.000   1.4063   0.04950   0.04184  -0.0265   0.3282   1.0000
  14.250   1.4286   0.04967   0.04196  -0.0259   0.3180   1.0000
  14.500   1.4592   0.04925   0.04141  -0.0258   0.3068   1.0000
  14.750   1.4293   0.05323   0.04559  -0.0225   0.2985   1.0000
  15.000   1.4619   0.05266   0.04488  -0.0225   0.2877   1.0000
  15.250   1.4408   0.05616   0.04855  -0.0200   0.2795   1.0000
  15.500   1.4591   0.05680   0.04913  -0.0194   0.2703   1.0000
  15.750   1.4506   0.05956   0.05199  -0.0177   0.2626   1.0000
  16.000   1.4672   0.06044   0.05285  -0.0172   0.2546   1.0000
  16.250   1.4473   0.06439   0.05697  -0.0155   0.2483   1.0000
  16.500   1.4861   0.06346   0.05590  -0.0157   0.2403   1.0000
  16.750   1.4453   0.06943   0.06217  -0.0138   0.2357   1.0000
  17.000   1.4786   0.06870   0.06135  -0.0137   0.2282   1.0000
  17.250   1.4630   0.07271   0.06552  -0.0128   0.2233   1.0000
  17.500   1.4150   0.08031   0.07342  -0.0121   0.2194   1.0000
  17.750   1.4880   0.07507   0.06787  -0.0119   0.2101   1.0000
  18.000   1.4292   0.08394   0.07712  -0.0115   0.2078   1.0000
  18.250   0.9282   0.17666   0.17010  -0.0455   0.1934   1.0000
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