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GOE 7K AIRFOIL (goe07k-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 7K AIRFOIL (goe07k-il)
Reynolds number: 200,000
Max Cl/Cd: 70.2 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe07k-il-200000-n5.txt
Download as CSV file: xf-goe07k-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 7K AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2107   0.09126   0.08748  -0.1009   0.9387   0.0170
  -8.750  -0.2042   0.08841   0.08463  -0.1015   0.9360   0.0162
  -8.500  -0.1992   0.08455   0.08078  -0.1040   0.9336   0.0154
  -8.250  -0.1948   0.08006   0.07630  -0.1078   0.9316   0.0148
  -8.000  -0.2099   0.07775   0.07405  -0.1059   0.9237   0.0151
  -7.750  -0.2234   0.06968   0.06595  -0.1120   0.9180   0.0131
  -7.500  -0.2299   0.06645   0.06271  -0.1114   0.9116   0.0130
  -7.250  -0.2323   0.06137   0.05755  -0.1127   0.9060   0.0131
  -7.000  -0.2227   0.05709   0.05316  -0.1148   0.9035   0.0128
  -6.750  -0.2071   0.05390   0.04985  -0.1169   0.9019   0.0141
  -6.500  -0.2271   0.04830   0.04402  -0.1116   0.8918   0.0130
  -6.250  -0.2097   0.04703   0.04267  -0.1121   0.8899   0.0144
  -6.000  -0.2003   0.04053   0.03574  -0.1117   0.8878   0.0140
  -5.750  -0.2104   0.03776   0.03272  -0.1054   0.8791   0.0139
  -5.500  -0.2024   0.03256   0.02696  -0.1026   0.8761   0.0140
  -5.250  -0.1857   0.02907   0.02296  -0.1010   0.8745   0.0144
  -5.000  -0.1646   0.02645   0.01985  -0.0999   0.8734   0.0153
  -4.750  -0.1661   0.02559   0.01871  -0.0941   0.8656   0.0160
  -4.500  -0.1453   0.02383   0.01644  -0.0925   0.8633   0.0175
  -4.250  -0.1218   0.02232   0.01466  -0.0918   0.8618   0.0184
  -4.000  -0.0945   0.02157   0.01377  -0.0918   0.8606   0.0201
  -3.750  -0.0658   0.02077   0.01276  -0.0920   0.8597   0.0228
  -3.250  -0.0375   0.01983   0.01161  -0.0866   0.8505   0.0280
  -2.750   0.0145   0.01900   0.01059  -0.0859   0.8471   0.0388
  -2.500   0.0429   0.01871   0.01019  -0.0861   0.8460   0.0466
  -2.250   0.0707   0.01824   0.00971  -0.0863   0.8451   0.0545
  -2.000   0.0933   0.01805   0.00942  -0.0854   0.8427   0.0615
  -1.000   0.1787   0.01749   0.00870  -0.0808   0.8311   0.0855
  -0.500   0.4032   0.01451   0.00841  -0.1199   0.8447   0.9628
  -0.250   0.4504   0.01482   0.00860  -0.1245   0.8447   1.0000
   0.250   0.4687   0.01550   0.00917  -0.1173   0.8335   1.0000
   0.500   0.4976   0.01545   0.00904  -0.1177   0.8321   1.0000
   0.750   0.5277   0.01538   0.00891  -0.1183   0.8310   1.0000
   1.000   0.5586   0.01532   0.00881  -0.1192   0.8301   1.0000
   1.500   0.5764   0.01616   0.00962  -0.1120   0.8187   1.0000
   1.750   0.6058   0.01612   0.00955  -0.1125   0.8174   1.0000
   2.000   0.6381   0.01597   0.00941  -0.1135   0.8162   1.0000
   2.500   0.6704   0.01622   0.00966  -0.1090   0.8043   1.0000
   2.750   0.7056   0.01587   0.00934  -0.1104   0.8025   1.0000
   3.000   0.7418   0.01556   0.00907  -0.1122   0.8011   1.0000
   3.500   0.7679   0.01614   0.00974  -0.1065   0.7892   1.0000
   3.750   0.8033   0.01582   0.00948  -0.1081   0.7873   1.0000
   4.000   0.8097   0.01615   0.00986  -0.1038   0.7776   1.0000
   4.250   0.8505   0.01544   0.00922  -0.1060   0.7730   1.0000
   4.500   0.8619   0.01558   0.00942  -0.1027   0.7626   1.0000
   4.750   0.8961   0.01507   0.00900  -0.1036   0.7542   1.0000
   5.000   0.9174   0.01501   0.00902  -0.1022   0.7441   1.0000
   5.250   0.9354   0.01504   0.00914  -0.1002   0.7321   1.0000
   5.500   0.9671   0.01459   0.00875  -0.1005   0.7130   1.0000
   5.750   0.9821   0.01464   0.00883  -0.0977   0.6876   1.0000
   6.000   1.0073   0.01435   0.00812  -0.0964   0.5839   1.0000
   6.250   0.9916   0.01562   0.00861  -0.0877   0.4744   1.0000
   6.500   0.9780   0.01704   0.00956  -0.0801   0.3926   1.0000
   6.750   0.9655   0.01863   0.01066  -0.0732   0.2992   1.0000
   7.000   0.9588   0.02021   0.01177  -0.0678   0.2186   1.0000
   7.250   0.9584   0.02163   0.01281  -0.0636   0.1454   1.0000
   7.500   0.9590   0.02312   0.01390  -0.0596   0.0806   1.0000
   7.750   0.9680   0.02415   0.01484  -0.0569   0.0539   1.0000
   8.000   0.9775   0.02520   0.01577  -0.0544   0.0326   1.0000
   8.250   0.9878   0.02625   0.01684  -0.0519   0.0252   1.0000
   8.500   0.9995   0.02719   0.01788  -0.0497   0.0212   1.0000
   8.750   1.0082   0.02837   0.01914  -0.0471   0.0190   1.0000
   9.000   1.0182   0.02948   0.02036  -0.0448   0.0170   1.0000
   9.250   1.0293   0.03052   0.02149  -0.0427   0.0153   1.0000
   9.500   1.0381   0.03178   0.02281  -0.0403   0.0144   1.0000
   9.750   1.0454   0.03324   0.02437  -0.0378   0.0137   1.0000
  10.000   1.0558   0.03453   0.02579  -0.0357   0.0129   1.0000
  10.250   1.0681   0.03562   0.02697  -0.0340   0.0117   1.0000
  10.500   1.0792   0.03697   0.02838  -0.0321   0.0112   1.0000
  10.750   1.0908   0.03845   0.02991  -0.0304   0.0105   1.0000
  11.000   1.1068   0.03991   0.03156  -0.0289   0.0101   1.0000
  11.250   1.1239   0.04147   0.03335  -0.0276   0.0097   1.0000
  11.500   1.1420   0.04332   0.03542  -0.0264   0.0093   1.0000
  11.750   1.1545   0.04501   0.03729  -0.0249   0.0089   1.0000
  12.000   1.1630   0.04667   0.03906  -0.0232   0.0084   1.0000
  12.250   1.1722   0.04873   0.04129  -0.0216   0.0082   1.0000
  12.500   1.1762   0.05139   0.04430  -0.0193   0.0080   1.0000
  12.750   1.1740   0.05460   0.04795  -0.0164   0.0077   1.0000
  13.000   1.1692   0.05781   0.05149  -0.0137   0.0076   1.0000
  13.250   1.1587   0.06157   0.05561  -0.0108   0.0075   1.0000
  13.500   1.1454   0.06551   0.05987  -0.0082   0.0074   1.0000
  13.750   1.1305   0.06962   0.06426  -0.0060   0.0074   1.0000
  14.000   1.1144   0.07391   0.06881  -0.0043   0.0074   1.0000
  14.250   1.0947   0.07890   0.07406  -0.0031   0.0074   1.0000
  14.500   1.0757   0.08403   0.07941  -0.0027   0.0074   1.0000
  14.750   1.0549   0.08976   0.08536  -0.0031   0.0074   1.0000
  15.000   1.0374   0.09541   0.09118  -0.0043   0.0075   1.0000
  15.250   1.0166   0.10223   0.09819  -0.0066   0.0075   1.0000
  15.500   0.9938   0.11027   0.10641  -0.0102   0.0076   1.0000
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