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GOE 744 AIRFOIL (goe744-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 744 AIRFOIL (goe744-il)
Reynolds number: 100,000
Max Cl/Cd: 35.54 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe744-il-100000-n5.txt
Download as CSV file: xf-goe744-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 744 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2017   0.11634   0.11040   0.0043   0.5741   0.0607
  -9.000  -0.2021   0.11416   0.10827   0.0012   0.5715   0.0610
  -8.750  -0.1959   0.11117   0.10532  -0.0007   0.5686   0.0613
  -8.500  -0.1785   0.10750   0.10165  -0.0004   0.5654   0.0620
  -8.250  -0.1676   0.10468   0.09881  -0.0011   0.5627   0.0628
  -8.000  -0.1589   0.10201   0.09613  -0.0021   0.5603   0.0638
  -7.750  -0.1521   0.09944   0.09353  -0.0034   0.5582   0.0650
  -7.500  -0.1474   0.09692   0.09099  -0.0049   0.5562   0.0663
  -7.250  -0.1489   0.09461   0.08872  -0.0080   0.5540   0.0676
  -7.000  -0.1582   0.09273   0.08691  -0.0116   0.5515   0.0681
  -6.750  -0.1535   0.08990   0.08412  -0.0139   0.5487   0.0685
  -6.500  -0.1354   0.08674   0.08098  -0.0127   0.5455   0.0694
  -6.250  -0.1228   0.08427   0.07850  -0.0129   0.5429   0.0711
  -6.000  -0.1144   0.08189   0.07609  -0.0144   0.5405   0.0733
  -5.750  -0.1140   0.07987   0.07388  -0.0223   0.5389   0.0764
  -5.500  -0.0997   0.07655   0.07057  -0.0206   0.5367   0.0771
  -5.250  -0.0847   0.07396   0.06798  -0.0202   0.5341   0.0781
  -5.000  -0.0689   0.07161   0.06567  -0.0213   0.5306   0.0797
  -4.750  -0.0530   0.06927   0.06330  -0.0230   0.5275   0.0821
  -4.500  -0.0347   0.06668   0.06045  -0.0282   0.5250   0.0859
  -4.250  -0.0191   0.06395   0.05775  -0.0275   0.5222   0.0867
  -4.000  -0.0022   0.06166   0.05542  -0.0272   0.5197   0.0880
  -3.750   0.0161   0.05951   0.05314  -0.0274   0.5175   0.0900
  -3.250   0.0609   0.05002   0.04295  -0.0311   0.5129   0.0615
  -3.000   0.0824   0.04826   0.04117  -0.0313   0.5092   0.0601
  -2.750   0.1045   0.04343   0.03582  -0.0315   0.5065   0.0546
  -2.500   0.1262   0.04176   0.03405  -0.0311   0.5034   0.0541
  -2.250   0.1484   0.03973   0.03178  -0.0304   0.5008   0.0534
  -2.000   0.1710   0.03751   0.02922  -0.0296   0.4986   0.0528
  -1.750   0.1943   0.03538   0.02669  -0.0286   0.4967   0.0524
  -1.500   0.2186   0.03384   0.02486  -0.0283   0.4931   0.0524
  -1.250   0.2436   0.03259   0.02328  -0.0280   0.4890   0.0536
  -1.000   0.2694   0.03137   0.02158  -0.0274   0.4856   0.0546
  -0.750   0.2955   0.03045   0.02049  -0.0269   0.4826   0.0552
  -0.500   0.3223   0.02958   0.01942  -0.0264   0.4802   0.0558
  -0.250   0.3497   0.02879   0.01842  -0.0258   0.4781   0.0565
   0.000   0.3762   0.02848   0.01805  -0.0259   0.4744   0.0574
   0.250   0.4021   0.02838   0.01792  -0.0261   0.4695   0.0587
   0.500   0.4291   0.02807   0.01744  -0.0258   0.4659   0.0610
   0.750   0.4561   0.02761   0.01700  -0.0256   0.4632   0.0632
   1.000   0.4842   0.02714   0.01645  -0.0252   0.4609   0.0652
   1.250   0.5128   0.02665   0.01582  -0.0247   0.4590   0.0674
   1.500   0.5345   0.02725   0.01662  -0.0251   0.4530   0.0695
   1.750   0.5602   0.02735   0.01677  -0.0252   0.4488   0.0740
   2.000   0.5902   0.02715   0.01656  -0.0254   0.4458   0.0795
   2.250   0.6211   0.02685   0.01618  -0.0255   0.4434   0.0865
   2.500   0.6512   0.02645   0.01575  -0.0253   0.4415   0.1014
   2.750   0.6692   0.02744   0.01708  -0.0256   0.4351   0.1333
   3.000   0.6905   0.02768   0.01757  -0.0251   0.4309   0.2263
   3.250   0.7134   0.02743   0.01756  -0.0243   0.4281   0.3247
   3.750   0.8837   0.02669   0.01784  -0.0463   0.4195   1.0000
   4.000   0.9019   0.02751   0.01865  -0.0457   0.4147   1.0000
   4.250   0.9240   0.02773   0.01877  -0.0448   0.4116   1.0000
   4.500   0.9486   0.02763   0.01853  -0.0439   0.4092   1.0000
   4.750   0.9745   0.02742   0.01815  -0.0429   0.4073   1.0000
   5.000   0.9756   0.02987   0.02082  -0.0423   0.3997   1.0000
   5.250   0.9926   0.03045   0.02135  -0.0412   0.3961   1.0000
   5.500   1.0158   0.03043   0.02123  -0.0402   0.3937   1.0000
   5.750   1.0424   0.03013   0.02081  -0.0393   0.3917   1.0000
   6.250   1.0225   0.03540   0.02629  -0.0360   0.3789   1.0000
   6.500   1.0500   0.03492   0.02571  -0.0349   0.3770   1.0000
   6.750   1.0809   0.03425   0.02493  -0.0340   0.3756   1.0000
   7.250   0.9762   0.04598   0.03686  -0.0284   0.3570   1.0000
   7.500   1.0259   0.04325   0.03401  -0.0274   0.3583   1.0000
  11.500   0.8950   0.10511   0.09626  -0.0267   0.2669   1.0000
  11.750   0.9127   0.10562   0.09676  -0.0261   0.2658   1.0000
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