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GOE 328 AIRFOIL (goe328-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 328 AIRFOIL (goe328-il)
Reynolds number: 500,000
Max Cl/Cd: 101.59 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe328-il-500000.txt
Download as CSV file: xf-goe328-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 328 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3633   0.09359   0.09136  -0.0176   1.0000   0.0237
  -7.750  -0.3609   0.09048   0.08829  -0.0224   1.0000   0.0248
  -7.500  -0.3545   0.08661   0.08445  -0.0298   1.0000   0.0250
  -7.250  -0.3434   0.08255   0.08039  -0.0353   1.0000   0.0251
  -6.750  -0.3161   0.07307   0.07091  -0.0429   0.9936   0.0255
  -6.500  -0.2939   0.06961   0.06743  -0.0455   0.9853   0.0258
  -6.250  -0.2692   0.06612   0.06391  -0.0496   0.9744   0.0262
  -6.000  -0.2441   0.06268   0.06043  -0.0540   0.9606   0.0268
  -5.750  -0.2213   0.05927   0.05694  -0.0579   0.9437   0.0277
  -5.500  -0.1994   0.05579   0.05334  -0.0614   0.9265   0.0288
  -5.250  -0.1581   0.05107   0.04830  -0.0694   0.9103   0.0307
  -5.000  -0.1329   0.04772   0.04474  -0.0716   0.8961   0.0308
  -4.750  -0.1146   0.04220   0.03905  -0.0738   0.8827   0.0313
  -4.500  -0.0954   0.03994   0.03672  -0.0742   0.8693   0.0317
  -4.250  -0.0736   0.03801   0.03470  -0.0747   0.8562   0.0323
  -4.000  -0.0494   0.03596   0.03251  -0.0755   0.8443   0.0330
  -3.750  -0.0232   0.03378   0.03016  -0.0765   0.8334   0.0341
  -3.500   0.0057   0.03144   0.02762  -0.0775   0.8224   0.0360
  -3.250   0.0416   0.03029   0.02600  -0.0777   0.8121   0.0381
  -3.000   0.0664   0.02554   0.02097  -0.0792   0.8025   0.0391
  -2.750   0.0923   0.02401   0.01937  -0.0797   0.7919   0.0398
  -2.500   0.1188   0.02284   0.01810  -0.0800   0.7822   0.0409
  -2.250   0.1464   0.02170   0.01680  -0.0803   0.7722   0.0426
  -2.000   0.1760   0.02067   0.01554  -0.0804   0.7621   0.0458
  -1.750   0.2066   0.01900   0.01340  -0.0805   0.7529   0.0487
  -1.500   0.2337   0.01756   0.01192  -0.0809   0.7420   0.0502
  -1.250   0.2616   0.01674   0.01100  -0.0811   0.7300   0.0522
  -1.000   0.2902   0.01618   0.01028  -0.0811   0.7177   0.0563
  -0.750   0.3196   0.01727   0.01114  -0.0805   0.7051   0.0594
  -0.250   0.3759   0.01410   0.00776  -0.0814   0.6838   0.0696
   0.000   0.4074   0.01218   0.00544  -0.0806   0.6741   0.0458
   0.250   0.4360   0.01125   0.00437  -0.0805   0.6635   0.0431
   0.500   0.4645   0.01071   0.00376  -0.0805   0.6518   0.0426
   0.750   0.4929   0.01035   0.00336  -0.0804   0.6402   0.0430
   1.000   0.5212   0.01009   0.00305  -0.0804   0.6282   0.0437
   1.250   0.5494   0.00989   0.00281  -0.0804   0.6152   0.0446
   1.500   0.5777   0.00979   0.00267  -0.0805   0.6010   0.0463
   1.750   0.6059   0.00971   0.00255  -0.0805   0.5851   0.0475
   2.000   0.6343   0.00952   0.00231  -0.0806   0.5672   0.0496
   2.250   0.6625   0.00948   0.00221  -0.0806   0.5467   0.0538
   2.500   0.6904   0.00953   0.00217  -0.0806   0.5246   0.0593
   2.750   0.7110   0.00757   0.00229  -0.0795   0.5039   1.0000
   3.000   0.7385   0.00780   0.00234  -0.0794   0.4833   1.0000
   3.250   0.7660   0.00802   0.00244  -0.0794   0.4659   1.0000
   3.500   0.7934   0.00825   0.00256  -0.0794   0.4510   1.0000
   4.000   0.8484   0.00867   0.00285  -0.0793   0.4263   1.0000
   4.250   0.8759   0.00887   0.00302  -0.0793   0.4160   1.0000
   4.500   0.9031   0.00912   0.00320  -0.0793   0.4060   1.0000
   4.750   0.9305   0.00931   0.00337  -0.0793   0.3944   1.0000
   5.000   0.9576   0.00952   0.00355  -0.0792   0.3797   1.0000
   5.250   0.9847   0.00973   0.00372  -0.0792   0.3660   1.0000
   5.500   1.0116   0.00996   0.00391  -0.0791   0.3502   1.0000
   5.750   1.0382   0.01022   0.00410  -0.0791   0.3323   1.0000
   6.000   1.0647   0.01049   0.00432  -0.0790   0.3164   1.0000
   6.250   1.0911   0.01076   0.00456  -0.0788   0.2990   1.0000
   6.500   1.1172   0.01106   0.00481  -0.0787   0.2829   1.0000
   6.750   1.1428   0.01142   0.00510  -0.0785   0.2635   1.0000
   7.000   1.1676   0.01187   0.00545  -0.0782   0.2393   1.0000
   7.250   1.1909   0.01250   0.00591  -0.0778   0.2019   1.0000
   7.500   1.2009   0.01491   0.00742  -0.0759   0.0580   1.0000
   7.750   1.2208   0.01597   0.00838  -0.0748   0.0383   1.0000
   8.000   1.2430   0.01664   0.00906  -0.0741   0.0322   1.0000
   8.250   1.2644   0.01739   0.00987  -0.0732   0.0285   1.0000
   8.500   1.2859   0.01806   0.01058  -0.0724   0.0261   1.0000
   8.750   1.3025   0.01922   0.01180  -0.0710   0.0240   1.0000
   9.000   1.3227   0.01991   0.01257  -0.0700   0.0229   1.0000
   9.250   1.3419   0.02065   0.01337  -0.0689   0.0216   1.0000
   9.500   1.3595   0.02147   0.01424  -0.0676   0.0204   1.0000
   9.750   1.3726   0.02260   0.01543  -0.0658   0.0195   1.0000
  10.000   1.3761   0.02439   0.01732  -0.0626   0.0188   1.0000
  10.250   1.3874   0.02531   0.01833  -0.0604   0.0184   1.0000
  10.500   1.3951   0.02643   0.01954  -0.0578   0.0179   1.0000
  10.750   1.4016   0.02774   0.02096  -0.0554   0.0175   1.0000
  11.000   1.4080   0.02919   0.02250  -0.0533   0.0170   1.0000
  11.250   1.4147   0.03070   0.02409  -0.0515   0.0165   1.0000
  11.500   1.4212   0.03231   0.02577  -0.0500   0.0161   1.0000
  11.750   1.4270   0.03405   0.02757  -0.0486   0.0156   1.0000
  12.000   1.4298   0.03619   0.02976  -0.0471   0.0152   1.0000
  12.250   1.4276   0.03903   0.03268  -0.0450   0.0148   1.0000
  12.500   1.4322   0.04123   0.03500  -0.0436   0.0146   1.0000
  12.750   1.4379   0.04326   0.03716  -0.0427   0.0143   1.0000
  13.000   1.4427   0.04547   0.03950  -0.0417   0.0141   1.0000
  13.250   1.4466   0.04783   0.04200  -0.0407   0.0139   1.0000
  13.500   1.4494   0.05035   0.04466  -0.0398   0.0137   1.0000
  13.750   1.4513   0.05304   0.04749  -0.0390   0.0134   1.0000
  14.000   1.4519   0.05592   0.05052  -0.0383   0.0133   1.0000
  14.250   1.4511   0.05899   0.05375  -0.0378   0.0131   1.0000
  14.500   1.4489   0.06232   0.05723  -0.0375   0.0129   1.0000
  14.750   1.4450   0.06590   0.06097  -0.0374   0.0128   1.0000
  15.000   1.4398   0.06970   0.06492  -0.0376   0.0127   1.0000
  15.250   1.4338   0.07367   0.06904  -0.0381   0.0125   1.0000
  15.500   1.4284   0.07767   0.07317  -0.0389   0.0124   1.0000
  15.750   1.4221   0.08189   0.07751  -0.0399   0.0122   1.0000
  16.000   1.4139   0.08659   0.08234  -0.0414   0.0121   1.0000
  16.250   1.4049   0.09159   0.08747  -0.0432   0.0120   1.0000
  16.500   1.3949   0.09690   0.09292  -0.0452   0.0119   1.0000
  16.750   1.3838   0.10254   0.09871  -0.0476   0.0118   1.0000
  17.000   1.3706   0.10878   0.10511  -0.0505   0.0118   1.0000
  17.250   1.3568   0.11538   0.11186  -0.0537   0.0117   1.0000
  17.500   1.3406   0.12274   0.11939  -0.0577   0.0117   1.0000
  17.750   1.3206   0.13130   0.12816  -0.0626   0.0118   1.0000
  18.000   1.2931   0.14226   0.13939  -0.0695   0.0119   1.0000
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