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GOE 265 AIRFOIL (goe265-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 265 AIRFOIL (goe265-il)
Reynolds number: 100,000
Max Cl/Cd: 52.58 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe265-il-100000.txt
Download as CSV file: xf-goe265-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 265 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2498   0.10742   0.10339  -0.0281   1.0000   0.0619
  -7.000  -0.2357   0.09771   0.09372  -0.0202   1.0000   0.0632
  -6.750  -0.2632   0.09893   0.09511  -0.0154   0.9993   0.0632
  -6.500  -0.2317   0.09376   0.08992  -0.0200   0.9920   0.0660
  -6.250  -0.1930   0.08933   0.08544  -0.0294   0.9816   0.0698
  -6.000  -0.1182   0.08814   0.08406  -0.0579   0.9633   0.0732
  -5.750  -0.1045   0.08034   0.07632  -0.0536   0.9588   0.0744
  -5.500  -0.0756   0.07565   0.07162  -0.0561   0.9496   0.0774
  -5.250  -0.0302   0.07201   0.06789  -0.0661   0.9387   0.0837
  -5.000   0.0274   0.06854   0.06423  -0.0816   0.9255   0.0867
  -4.750   0.0430   0.06418   0.05989  -0.0801   0.9124   0.0886
  -4.500   0.0681   0.06112   0.05679  -0.0820   0.8984   0.0924
  -4.250   0.1249   0.04207   0.03776  -0.0854   0.8438   0.1013
  -4.000   0.1357   0.03891   0.03458  -0.0834   0.8313   0.1034
  -3.750   0.1544   0.03635   0.03197  -0.0841   0.8186   0.1074
  -3.500   0.1978   0.03421   0.02954  -0.0926   0.8059   0.1157
  -3.250   0.2089   0.03095   0.02627  -0.0902   0.7969   0.1184
  -3.000   0.2312   0.02880   0.02404  -0.0912   0.7847   0.1237
  -2.750   0.2686   0.02664   0.02162  -0.0963   0.7736   0.1313
  -2.500   0.2869   0.02426   0.01918  -0.0954   0.7649   0.1363
  -2.250   0.3198   0.02253   0.01725  -0.0986   0.7532   0.1468
  -2.000   0.3430   0.02078   0.01541  -0.0988   0.7435   0.1541
  -1.750   0.3730   0.01900   0.01343  -0.1006   0.7339   0.1633
  -1.500   0.4026   0.01775   0.01200  -0.1022   0.7229   0.1766
  -1.250   0.4288   0.01630   0.01040  -0.1026   0.7141   0.1923
  -1.000   0.4552   0.01513   0.00911  -0.1032   0.7033   0.2084
  -0.750   0.4842   0.01445   0.00823  -0.1040   0.6926   0.2355
  -0.500   0.5080   0.01292   0.00663  -0.1038   0.6841   0.2550
   0.250   0.6457   0.02570   0.01769  -0.1151   0.6704   0.1704
   0.500   0.6793   0.02462   0.01605  -0.1153   0.6597   0.1589
   0.750   0.7075   0.02357   0.01481  -0.1149   0.6507   0.1630
   1.000   0.7354   0.02309   0.01417  -0.1146   0.6385   0.1709
   1.250   0.7631   0.02255   0.01347  -0.1143   0.6274   0.1784
   1.500   0.7916   0.02215   0.01279  -0.1137   0.6184   0.1872
   1.750   0.8182   0.02185   0.01249  -0.1133   0.6061   0.1968
   2.000   0.8454   0.02168   0.01218  -0.1128   0.5950   0.2056
   2.250   0.8728   0.02142   0.01179  -0.1122   0.5858   0.2157
   2.500   0.8992   0.02132   0.01171  -0.1117   0.5739   0.2277
   2.750   0.9260   0.02129   0.01163  -0.1111   0.5630   0.2380
   3.000   0.9534   0.02118   0.01141  -0.1105   0.5547   0.2542
   3.250   0.9789   0.02128   0.01161  -0.1100   0.5432   0.2740
   3.500   1.0053   0.02135   0.01172  -0.1095   0.5338   0.3010
   3.750   1.0314   0.02031   0.01173  -0.1089   0.5250   1.0000
   4.000   1.0576   0.02083   0.01203  -0.1083   0.5154   1.0000
   4.250   1.0847   0.02114   0.01211  -0.1078   0.5078   1.0000
   4.500   1.1094   0.02168   0.01267  -0.1073   0.4978   1.0000
   4.750   1.1365   0.02194   0.01273  -0.1068   0.4903   1.0000
   5.000   1.1606   0.02242   0.01327  -0.1062   0.4800   1.0000
   5.250   1.1865   0.02279   0.01358  -0.1057   0.4723   1.0000
   5.500   1.2112   0.02325   0.01406  -0.1051   0.4637   1.0000
   5.750   1.2369   0.02367   0.01444  -0.1047   0.4566   1.0000
   6.000   1.2612   0.02415   0.01498  -0.1041   0.4482   1.0000
   6.250   1.2871   0.02455   0.01535  -0.1036   0.4417   1.0000
   6.500   1.3103   0.02518   0.01611  -0.1030   0.4338   1.0000
   6.750   1.3377   0.02546   0.01626  -0.1027   0.4281   1.0000
   7.000   1.3588   0.02616   0.01721  -0.1019   0.4192   1.0000
   7.250   1.3860   0.02636   0.01729  -0.1015   0.4129   1.0000
   7.500   1.4065   0.02712   0.01829  -0.1006   0.4044   1.0000
   7.750   1.4333   0.02736   0.01846  -0.1002   0.3979   1.0000
   8.000   1.4533   0.02812   0.01947  -0.0992   0.3893   1.0000
   8.250   1.4803   0.02831   0.01956  -0.0988   0.3823   1.0000
   8.500   1.4991   0.02909   0.02060  -0.0977   0.3731   1.0000
   8.750   1.5262   0.02932   0.02075  -0.0973   0.3658   1.0000
   9.000   1.5437   0.03009   0.02180  -0.0960   0.3559   1.0000
   9.250   1.5659   0.03061   0.02238  -0.0951   0.3466   1.0000
   9.500   1.5897   0.03092   0.02268  -0.0943   0.3365   1.0000
   9.750   1.6060   0.03167   0.02366  -0.0928   0.3244   1.0000
  10.000   1.6238   0.03232   0.02441  -0.0914   0.3117   1.0000
  10.250   1.6415   0.03296   0.02511  -0.0899   0.2983   1.0000
  10.500   1.6584   0.03364   0.02581  -0.0884   0.2849   1.0000
  10.750   1.6749   0.03426   0.02643  -0.0868   0.2720   1.0000
  11.000   1.6895   0.03477   0.02693  -0.0851   0.2593   1.0000
  11.250   1.6954   0.03566   0.02803  -0.0825   0.2471   1.0000
  11.500   1.7017   0.03664   0.02915  -0.0800   0.2364   1.0000
  11.750   1.7105   0.03748   0.03001  -0.0778   0.2271   1.0000
  12.000   1.7123   0.03859   0.03128  -0.0749   0.2184   1.0000
  12.250   1.7114   0.03992   0.03273  -0.0720   0.2107   1.0000
  12.500   1.7111   0.04126   0.03415  -0.0694   0.2032   1.0000
  12.750   1.7071   0.04318   0.03623  -0.0672   0.1961   1.0000
  13.000   1.7039   0.04505   0.03815  -0.0654   0.1887   1.0000
  13.250   1.6957   0.04772   0.04102  -0.0640   0.1815   1.0000
  13.500   1.6908   0.05016   0.04347  -0.0630   0.1741   1.0000
  13.750   1.6808   0.05363   0.04718  -0.0625   0.1676   1.0000
  14.000   1.6747   0.05665   0.05021  -0.0621   0.1609   1.0000
  14.250   1.6623   0.06078   0.05457  -0.0622   0.1545   1.0000
  14.500   1.6525   0.06448   0.05828  -0.0623   0.1473   1.0000
  14.750   1.6359   0.06954   0.06356  -0.0631   0.1410   1.0000
  15.000   1.6226   0.07393   0.06788  -0.0636   0.1329   1.0000
  15.250   1.6020   0.08005   0.07426  -0.0653   0.1264   1.0000
  15.500   1.5844   0.08561   0.07980  -0.0667   0.1179   1.0000
  15.750   1.5625   0.09241   0.08678  -0.0690   0.1103   1.0000
  16.000   1.5409   0.09932   0.09376  -0.0713   0.1016   1.0000
  16.250   1.5206   0.10615   0.10056  -0.0739   0.0927   1.0000
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