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GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il)
Reynolds number: 100,000
Max Cl/Cd: 54.88 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe199-il-100000-n5.txt
Download as CSV file: xf-goe199-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 199 (L.F.G. 5406) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3089   0.09301   0.08850  -0.0250   1.0000   0.0340
  -7.000  -0.3083   0.09068   0.08624  -0.0250   1.0000   0.0346
  -6.750  -0.3100   0.08863   0.08427  -0.0245   1.0000   0.0353
  -6.500  -0.3138   0.08683   0.08254  -0.0236   1.0000   0.0359
  -6.250  -0.2937   0.08315   0.07882  -0.0288   0.9949   0.0375
  -6.000  -0.2407   0.07937   0.07481  -0.0462   0.9860   0.0401
  -5.750  -0.2251   0.07407   0.06955  -0.0472   0.9804   0.0411
  -5.500  -0.2019   0.06997   0.06544  -0.0495   0.9753   0.0434
  -5.250  -0.1683   0.06596   0.06133  -0.0557   0.9677   0.0463
  -5.000  -0.1043   0.06202   0.05696  -0.0703   0.9610   0.0503
  -4.750  -0.0911   0.05757   0.05262  -0.0697   0.9529   0.0521
  -4.500  -0.0375   0.05533   0.04994  -0.0785   0.9468   0.0606
  -4.250  -0.0161   0.05087   0.04551  -0.0801   0.9388   0.0619
  -4.000   0.0107   0.04761   0.04223  -0.0822   0.9333   0.0649
  -3.750   0.0564   0.04572   0.03982  -0.0874   0.9249   0.0727
  -3.500   0.0775   0.04206   0.03629  -0.0883   0.9187   0.0762
  -3.250   0.1153   0.04019   0.03402  -0.0913   0.9103   0.0859
  -3.000   0.1415   0.03732   0.03115  -0.0925   0.9036   0.0894
  -2.750   0.1757   0.03566   0.02912  -0.0944   0.8951   0.1003
  -2.500   0.2032   0.03331   0.02674  -0.0953   0.8880   0.1049
  -2.250   0.2312   0.03169   0.02497  -0.0961   0.8790   0.1205
  -2.000   0.2608   0.03026   0.02336  -0.0971   0.8718   0.1476
  -1.750   0.3069   0.02711   0.01920  -0.0968   0.8631   0.0618
  -1.500   0.3360   0.02552   0.01745  -0.0969   0.8552   0.0575
  -1.250   0.3651   0.02416   0.01582  -0.0968   0.8450   0.0548
  -1.000   0.3934   0.02311   0.01451  -0.0964   0.8334   0.0553
  -0.750   0.4211   0.02216   0.01330  -0.0957   0.8196   0.0559
  -0.500   0.4484   0.02120   0.01206  -0.0947   0.8035   0.0545
  -0.250   0.4754   0.02036   0.01097  -0.0938   0.7867   0.0534
   0.000   0.5023   0.01964   0.01003  -0.0929   0.7703   0.0526
   0.250   0.5292   0.01902   0.00925  -0.0921   0.7542   0.0522
   0.500   0.5560   0.01847   0.00859  -0.0915   0.7382   0.0522
   0.750   0.5827   0.01799   0.00803  -0.0908   0.7219   0.0525
   1.000   0.6092   0.01760   0.00761  -0.0903   0.7047   0.0548
   1.250   0.6352   0.01728   0.00722  -0.0896   0.6866   0.0574
   1.500   0.6614   0.01700   0.00687  -0.0889   0.6659   0.0585
   1.750   0.6881   0.01681   0.00655  -0.0884   0.6436   0.0594
   2.000   0.7147   0.01671   0.00630  -0.0878   0.6194   0.0606
   2.250   0.7410   0.01664   0.00607  -0.0873   0.5935   0.0627
   2.500   0.7672   0.01668   0.00593  -0.0867   0.5670   0.0661
   2.750   0.7932   0.01681   0.00589  -0.0862   0.5415   0.0727
   3.250   0.8447   0.01556   0.00601  -0.0854   0.4916   1.0000
   3.500   0.8699   0.01592   0.00617  -0.0849   0.4650   1.0000
   3.750   0.8948   0.01632   0.00636  -0.0844   0.4373   1.0000
   4.000   0.9193   0.01675   0.00659  -0.0838   0.4091   1.0000
   4.250   0.9437   0.01721   0.00689  -0.0833   0.3828   1.0000
   4.500   0.9678   0.01770   0.00721  -0.0828   0.3607   1.0000
   4.750   0.9920   0.01820   0.00758  -0.0823   0.3427   1.0000
   5.000   1.0161   0.01871   0.00799  -0.0818   0.3283   1.0000
   5.250   1.0402   0.01924   0.00845  -0.0813   0.3166   1.0000
   5.500   1.0644   0.01975   0.00893  -0.0808   0.3065   1.0000
   5.750   1.0887   0.02027   0.00944  -0.0804   0.2984   1.0000
   6.000   1.1129   0.02081   0.01000  -0.0799   0.2914   1.0000
   6.250   1.1370   0.02138   0.01055  -0.0794   0.2857   1.0000
   6.500   1.1615   0.02191   0.01116  -0.0790   0.2801   1.0000
   6.750   1.1856   0.02249   0.01177  -0.0786   0.2755   1.0000
   7.000   1.2098   0.02311   0.01243  -0.0782   0.2715   1.0000
   7.250   1.2344   0.02368   0.01314  -0.0778   0.2673   1.0000
   7.500   1.2586   0.02427   0.01384  -0.0774   0.2632   1.0000
   7.750   1.2819   0.02490   0.01452  -0.0769   0.2581   1.0000
   8.000   1.3043   0.02542   0.01523  -0.0763   0.2505   1.0000
   8.250   1.3254   0.02599   0.01581  -0.0755   0.2425   1.0000
   8.500   1.3464   0.02647   0.01655  -0.0746   0.2338   1.0000
   8.750   1.3656   0.02698   0.01722  -0.0736   0.2236   1.0000
   9.000   1.3831   0.02750   0.01785  -0.0723   0.2114   1.0000
   9.250   1.3998   0.02802   0.01854  -0.0709   0.1962   1.0000
   9.500   1.4158   0.02857   0.01928  -0.0694   0.1732   1.0000
   9.750   1.4260   0.02966   0.02019  -0.0674   0.0970   1.0000
  10.000   1.4208   0.03250   0.02256  -0.0638   0.0603   1.0000
  10.250   1.4202   0.03474   0.02481  -0.0605   0.0471   1.0000
  10.500   1.4194   0.03672   0.02690  -0.0572   0.0415   1.0000
  10.750   1.4148   0.03908   0.02938  -0.0540   0.0383   1.0000
  11.000   1.4118   0.04142   0.03193  -0.0514   0.0361   1.0000
  11.250   1.4076   0.04402   0.03475  -0.0492   0.0341   1.0000
  11.500   1.4009   0.04703   0.03796  -0.0476   0.0324   1.0000
  11.750   1.3914   0.05057   0.04169  -0.0464   0.0310   1.0000
  12.000   1.3787   0.05474   0.04603  -0.0458   0.0301   1.0000
  12.250   1.3638   0.05950   0.05097  -0.0458   0.0293   1.0000
  12.500   1.3504   0.06441   0.05605  -0.0463   0.0288   1.0000
  12.750   1.3398   0.06925   0.06109  -0.0472   0.0283   1.0000
  13.000   1.3287   0.07435   0.06638  -0.0483   0.0278   1.0000
  13.250   1.3182   0.07948   0.07168  -0.0495   0.0273   1.0000
  13.500   1.3095   0.08437   0.07672  -0.0506   0.0268   1.0000
  13.750   1.3030   0.08888   0.08139  -0.0515   0.0261   1.0000
  14.000   1.2985   0.09303   0.08567  -0.0522   0.0253   1.0000
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