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GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 177 AIRFOIL (goe177-il)
Reynolds number: 1,000,000
Max Cl/Cd: 89.56 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe177-il-1000000-n5.txt
Download as CSV file: xf-goe177-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 177 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3103   0.09385   0.09236  -0.0207   0.9871   0.0031
  -7.500  -0.2920   0.08650   0.08496  -0.0259   0.9392   0.0032
  -7.250  -0.2883   0.08344   0.08178  -0.0269   0.8883   0.0032
  -7.000  -0.2815   0.08026   0.07833  -0.0291   0.8184   0.0033
  -6.750  -0.2685   0.07643   0.07433  -0.0333   0.7786   0.0033
  -6.500  -0.2522   0.07204   0.06983  -0.0386   0.7517   0.0036
  -6.250  -0.2328   0.06727   0.06496  -0.0447   0.7300   0.0037
  -6.000  -0.2109   0.06264   0.06023  -0.0508   0.7118   0.0037
  -5.500  -0.1234   0.01712   0.01317  -0.0932   0.7039   0.0029
  -5.250  -0.0957   0.01458   0.01009  -0.0940   0.6867   0.0030
  -5.000  -0.0679   0.01319   0.00834  -0.0943   0.6706   0.0032
  -4.500  -0.0118   0.01138   0.00595  -0.0945   0.6376   0.0036
  -4.250   0.0164   0.01084   0.00519  -0.0945   0.6218   0.0039
  -4.000   0.0445   0.01043   0.00460  -0.0946   0.6073   0.0040
  -3.750   0.0728   0.00978   0.00372  -0.0946   0.5900   0.0045
  -3.500   0.1007   0.00954   0.00333  -0.0946   0.5668   0.0049
  -3.250   0.1287   0.00940   0.00308  -0.0946   0.5470   0.0056
  -3.000   0.1568   0.00921   0.00275  -0.0946   0.5284   0.0063
  -2.750   0.1853   0.00894   0.00233  -0.0946   0.5167   0.0071
  -2.500   0.2136   0.00873   0.00203  -0.0947   0.5042   0.0088
  -2.250   0.2418   0.00863   0.00184  -0.0947   0.4910   0.0106
  -2.000   0.2701   0.00851   0.00163  -0.0947   0.4780   0.0169
  -1.500   0.3264   0.00829   0.00144  -0.0948   0.4531   0.0562
  -1.250   0.3542   0.00839   0.00143  -0.0948   0.4287   0.0656
  -1.000   0.3819   0.00850   0.00142  -0.0948   0.4041   0.0708
  -0.750   0.4098   0.00856   0.00140  -0.0948   0.3858   0.0747
  -0.500   0.4375   0.00866   0.00137  -0.0948   0.3649   0.0764
  -0.250   0.4652   0.00876   0.00135  -0.0947   0.3442   0.0776
   0.000   0.4929   0.00887   0.00135  -0.0947   0.3255   0.0789
   0.250   0.5205   0.00899   0.00137  -0.0947   0.3082   0.0805
   0.500   0.5481   0.00911   0.00139  -0.0947   0.2907   0.0812
   0.750   0.5755   0.00923   0.00141  -0.0947   0.2697   0.0839
   1.000   0.6027   0.00941   0.00147  -0.0946   0.2445   0.0880
   1.250   0.6283   0.00989   0.00166  -0.0944   0.1821   0.0920
   1.750   0.6809   0.01057   0.00208  -0.0942   0.1011   0.1195
   2.000   0.7085   0.01058   0.00220  -0.0943   0.0946   0.1789
   2.250   0.7351   0.01079   0.00241  -0.0942   0.0609   0.2457
   2.500   0.7625   0.01083   0.00257  -0.0943   0.0573   0.3113
   2.750   0.7899   0.01087   0.00272  -0.0943   0.0533   0.3676
   3.250   0.8383   0.00986   0.00308  -0.0931   0.0491   1.0000
   3.500   0.8655   0.01002   0.00323  -0.0931   0.0479   1.0000
   3.750   0.8927   0.01020   0.00339  -0.0930   0.0459   1.0000
   4.000   0.9195   0.01043   0.00359  -0.0929   0.0420   1.0000
   4.250   0.9465   0.01061   0.00376  -0.0929   0.0387   1.0000
   4.500   0.9724   0.01097   0.00397  -0.0927   0.0198   1.0000
   4.750   0.9991   0.01118   0.00420  -0.0926   0.0126   1.0000
   5.000   1.0255   0.01145   0.00453  -0.0924   0.0102   1.0000
   5.250   1.0515   0.01178   0.00491  -0.0921   0.0077   1.0000
   5.500   1.0776   0.01205   0.00521  -0.0919   0.0065   1.0000
   5.750   1.1032   0.01242   0.00561  -0.0916   0.0052   1.0000
   6.000   1.1288   0.01274   0.00598  -0.0914   0.0046   1.0000
   6.250   1.1541   0.01311   0.00639  -0.0911   0.0041   1.0000
   6.500   1.1790   0.01353   0.00683  -0.0907   0.0036   1.0000
   6.750   1.2028   0.01408   0.00743  -0.0902   0.0032   1.0000
   7.000   1.2271   0.01452   0.00792  -0.0897   0.0028   1.0000
   7.250   1.2504   0.01507   0.00854  -0.0892   0.0026   1.0000
   7.500   1.2735   0.01564   0.00919  -0.0885   0.0024   1.0000
   7.750   1.2961   0.01622   0.00982  -0.0879   0.0022   1.0000
   8.000   1.3163   0.01706   0.01074  -0.0869   0.0020   1.0000
   8.250   1.3345   0.01808   0.01187  -0.0856   0.0019   1.0000
   8.500   1.3520   0.01910   0.01302  -0.0842   0.0018   1.0000
   8.750   1.3663   0.02037   0.01441  -0.0823   0.0017   1.0000
   9.000   1.3771   0.02188   0.01604  -0.0799   0.0016   1.0000
   9.250   1.3850   0.02354   0.01781  -0.0771   0.0015   1.0000
   9.500   1.3927   0.02510   0.01948  -0.0744   0.0015   1.0000
   9.750   1.3996   0.02640   0.02087  -0.0716   0.0014   1.0000
  10.000   1.4062   0.02765   0.02221  -0.0689   0.0013   1.0000
  10.250   1.4129   0.02895   0.02361  -0.0665   0.0012   1.0000
  10.500   1.4179   0.03050   0.02525  -0.0642   0.0012   1.0000
  10.750   1.4213   0.03234   0.02719  -0.0620   0.0011   1.0000
  11.000   1.4243   0.03431   0.02928  -0.0601   0.0011   1.0000
  11.250   1.4272   0.03641   0.03153  -0.0586   0.0011   1.0000
  11.500   1.4291   0.03873   0.03398  -0.0574   0.0011   1.0000
  11.750   1.4289   0.04144   0.03683  -0.0563   0.0010   1.0000
  12.000   1.4253   0.04475   0.04029  -0.0551   0.0010   1.0000
  12.250   1.4178   0.04877   0.04450  -0.0536   0.0010   1.0000
  12.500   1.4150   0.05227   0.04818  -0.0528   0.0009   1.0000
  12.750   1.4086   0.05632   0.05241  -0.0522   0.0009   1.0000
  13.000   1.3992   0.06090   0.05719  -0.0520   0.0009   1.0000
  13.250   1.3875   0.06590   0.06240  -0.0524   0.0008   1.0000
  13.500   1.3749   0.07110   0.06777  -0.0534   0.0008   1.0000
  13.750   1.3591   0.07702   0.07388  -0.0547   0.0008   1.0000
  14.000   1.3435   0.08307   0.08011  -0.0566   0.0008   1.0000
  14.250   1.3274   0.08950   0.08670  -0.0590   0.0008   1.0000
  14.500   1.3121   0.09607   0.09342  -0.0618   0.0008   1.0000
  14.750   1.2954   0.10316   0.10066  -0.0651   0.0008   1.0000
  15.000   1.2798   0.11039   0.10802  -0.0686   0.0008   1.0000
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