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GOE 380 AIRFOIL (goe380-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 380 AIRFOIL (goe380-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.75 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe380-il-1000000.txt
Download as CSV file: xf-goe380-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 380 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2993   0.09449   0.09300  -0.0222   1.0000   0.0063
  -7.750  -0.3022   0.09255   0.09109  -0.0211   1.0000   0.0063
  -7.500  -0.3019   0.09017   0.08873  -0.0217   0.9992   0.0063
  -7.250  -0.2798   0.08577   0.08433  -0.0282   0.9956   0.0063
  -7.000  -0.2622   0.08014   0.07870  -0.0340   0.9913   0.0065
  -6.750  -0.2404   0.07628   0.07483  -0.0387   0.9871   0.0066
  -6.500  -0.2143   0.07260   0.07113  -0.0445   0.9835   0.0069
  -6.250  -0.1912   0.06884   0.06736  -0.0497   0.9767   0.0070
  -6.000  -0.1606   0.06474   0.06323  -0.0566   0.9717   0.0073
  -5.750  -0.1282   0.06062   0.05908  -0.0635   0.9654   0.0076
  -5.500  -0.0921   0.05639   0.05478  -0.0709   0.9561   0.0078
  -5.250  -0.0599   0.05245   0.05076  -0.0766   0.9415   0.0084
  -5.000  -0.0328   0.04904   0.04723  -0.0801   0.9186   0.0089
  -4.750  -0.0040   0.04594   0.04395  -0.0830   0.8932   0.0095
  -4.500   0.0180   0.04317   0.04101  -0.0841   0.8677   0.0096
  -4.250   0.0407   0.04025   0.03792  -0.0849   0.8466   0.0096
  -4.000   0.0635   0.03731   0.03480  -0.0855   0.8285   0.0097
  -3.750   0.0868   0.03427   0.03159  -0.0859   0.8117   0.0097
  -1.750   0.2709   0.01153   0.00638  -0.0789   0.6502   0.0125
  -1.500   0.2949   0.00954   0.00386  -0.0775   0.6266   0.0115
  -1.250   0.3198   0.00901   0.00312  -0.0766   0.6033   0.0123
  -1.000   0.3452   0.00870   0.00266  -0.0760   0.5841   0.0136
  -0.750   0.3709   0.00852   0.00235  -0.0754   0.5687   0.0144
  -0.500   0.3958   0.00811   0.00179  -0.0746   0.5565   0.0161
  -0.250   0.4215   0.00792   0.00152  -0.0740   0.5458   0.0189
   0.000   0.4476   0.00783   0.00135  -0.0735   0.5358   0.0215
   0.250   0.4736   0.00768   0.00125  -0.0730   0.5264   0.0484
   0.500   0.5002   0.00773   0.00129  -0.0727   0.5166   0.0642
   0.750   0.5266   0.00780   0.00130  -0.0724   0.5054   0.0706
   1.000   0.5534   0.00784   0.00133  -0.0721   0.4946   0.0777
   1.250   0.5801   0.00791   0.00137  -0.0719   0.4837   0.0842
   1.500   0.6068   0.00797   0.00141  -0.0716   0.4738   0.0914
   1.750   0.6332   0.00803   0.00141  -0.0713   0.4622   0.0955
   2.000   0.6592   0.00803   0.00139  -0.0709   0.4476   0.1021
   2.250   0.6854   0.00810   0.00140  -0.0706   0.4315   0.1067
   2.500   0.7112   0.00817   0.00141  -0.0702   0.4138   0.1121
   2.750   0.7370   0.00826   0.00145  -0.0698   0.3966   0.1171
   3.000   0.7625   0.00838   0.00151  -0.0694   0.3805   0.1241
   3.500   0.8635   0.00714   0.00197  -0.0806   0.3474   1.0000
   3.750   0.8875   0.00732   0.00207  -0.0799   0.3379   1.0000
   4.000   0.9120   0.00744   0.00218  -0.0792   0.3305   1.0000
   4.250   0.9359   0.00761   0.00230  -0.0785   0.3230   1.0000
   4.500   0.9604   0.00774   0.00244  -0.0778   0.3161   1.0000
   4.750   0.9843   0.00792   0.00258  -0.0771   0.3088   1.0000
   5.000   1.0088   0.00804   0.00271  -0.0764   0.3025   1.0000
   5.250   1.0326   0.00823   0.00287  -0.0757   0.2944   1.0000
   5.500   1.0563   0.00842   0.00302  -0.0750   0.2828   1.0000
   5.750   1.0802   0.00859   0.00318  -0.0743   0.2713   1.0000
   6.000   1.1033   0.00884   0.00337  -0.0735   0.2546   1.0000
   6.250   1.1263   0.00909   0.00356  -0.0727   0.2366   1.0000
   6.500   1.1470   0.00954   0.00384  -0.0715   0.2033   1.0000
   6.750   1.1664   0.01010   0.00422  -0.0701   0.1719   1.0000
   7.000   1.1859   0.01065   0.00464  -0.0688   0.1453   1.0000
   7.250   1.1988   0.01178   0.00537  -0.0664   0.0811   1.0000
   7.500   1.2072   0.01334   0.00657  -0.0632   0.0147   1.0000
   7.750   1.2278   0.01379   0.00709  -0.0620   0.0120   1.0000
   8.000   1.2479   0.01428   0.00763  -0.0607   0.0104   1.0000
   8.250   1.2662   0.01492   0.00837  -0.0591   0.0089   1.0000
   8.500   1.2798   0.01597   0.00959  -0.0567   0.0079   1.0000
   8.750   1.2995   0.01642   0.01009  -0.0555   0.0076   1.0000
   9.000   1.3180   0.01695   0.01068  -0.0540   0.0069   1.0000
   9.250   1.3354   0.01753   0.01131  -0.0525   0.0062   1.0000
   9.500   1.3505   0.01826   0.01210  -0.0505   0.0058   1.0000
   9.750   1.3633   0.01909   0.01301  -0.0483   0.0055   1.0000
  10.000   1.3704   0.02017   0.01421  -0.0452   0.0052   1.0000
  10.250   1.3631   0.02173   0.01591  -0.0396   0.0050   1.0000
  10.500   1.3534   0.02357   0.01790  -0.0343   0.0048   1.0000
  10.750   1.3553   0.02489   0.01933  -0.0312   0.0047   1.0000
  11.000   1.3716   0.02536   0.01986  -0.0299   0.0043   1.0000
  11.250   1.3690   0.02717   0.02178  -0.0268   0.0043   1.0000
  11.500   1.3703   0.02886   0.02357  -0.0245   0.0042   1.0000
  11.750   1.3715   0.03071   0.02552  -0.0226   0.0040   1.0000
  12.000   1.3676   0.03319   0.02812  -0.0207   0.0040   1.0000
  12.250   1.3672   0.03551   0.03054  -0.0194   0.0038   1.0000
  12.500   1.3628   0.03842   0.03357  -0.0180   0.0038   1.0000
  12.750   1.3682   0.04034   0.03557  -0.0178   0.0036   1.0000
  13.000   1.3625   0.04366   0.03902  -0.0168   0.0036   1.0000
  13.250   1.3580   0.04695   0.04244  -0.0160   0.0035   1.0000
  13.500   1.3570   0.04991   0.04552  -0.0160   0.0035   1.0000
  13.750   1.3598   0.05256   0.04824  -0.0172   0.0033   1.0000
  14.000   1.3558   0.05610   0.05189  -0.0176   0.0032   1.0000
  14.250   1.3559   0.05938   0.05524  -0.0191   0.0030   1.0000
  14.500   1.3452   0.06381   0.05983  -0.0189   0.0031   1.0000
  14.750   1.3367   0.06822   0.06438  -0.0194   0.0031   1.0000
  15.000   1.3319   0.07237   0.06862  -0.0209   0.0030   1.0000
  15.250   1.3229   0.07712   0.07351  -0.0221   0.0030   1.0000
  15.500   1.3145   0.08198   0.07849  -0.0238   0.0030   1.0000
  15.750   1.3053   0.08718   0.08380  -0.0257   0.0030   1.0000
  16.000   1.2975   0.09227   0.08899  -0.0280   0.0029   1.0000
  16.250   1.2822   0.09880   0.09570  -0.0302   0.0030   1.0000
  16.500   1.2739   0.10433   0.10132  -0.0331   0.0029   1.0000
  16.750   1.2478   0.11362   0.11091  -0.0365   0.0031   1.0000
  17.000   1.2435   0.11875   0.11609  -0.0397   0.0030   1.0000
  17.250   1.2222   0.12778   0.12533  -0.0442   0.0031   1.0000
  17.500   1.1784   0.14295   0.14085  -0.0522   0.0034   1.0000
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