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GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 264 AIRFOIL (goe264-il)
Reynolds number: 500,000
Max Cl/Cd: 104.32 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe264-il-500000-n5.txt
Download as CSV file: xf-goe264-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 264 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3226   0.09784   0.09568  -0.0226   1.0000   0.0076
  -8.250  -0.3184   0.09454   0.09240  -0.0240   1.0000   0.0078
  -8.000  -0.3137   0.09106   0.08895  -0.0259   0.9962   0.0079
  -7.750  -0.3003   0.08622   0.08411  -0.0312   0.9845   0.0084
  -7.500  -0.2850   0.07975   0.07764  -0.0390   0.9731   0.0091
  -7.250  -0.2663   0.07615   0.07402  -0.0439   0.9618   0.0094
  -7.000  -0.2481   0.07283   0.07067  -0.0481   0.9504   0.0097
  -6.750  -0.2299   0.06935   0.06716  -0.0524   0.9385   0.0102
  -6.500  -0.2096   0.06527   0.06303  -0.0575   0.9269   0.0107
  -6.250  -0.1850   0.05911   0.05679  -0.0654   0.9154   0.0120
  -6.000  -0.1569   0.05343   0.05101  -0.0729   0.9037   0.0133
  -5.750  -0.1317   0.05136   0.04885  -0.0756   0.8911   0.0140
  -5.500  -0.1033   0.04807   0.04543  -0.0798   0.8779   0.0152
  -5.250  -0.0616   0.03961   0.03669  -0.0903   0.8659   0.0187
  -5.000  -0.0359   0.03892   0.03590  -0.0910   0.8512   0.0194
  -4.750  -0.0067   0.03694   0.03376  -0.0932   0.8362   0.0209
  -4.500   0.0395   0.02851   0.02484  -0.1017   0.8238   0.0257
  -4.250   0.0665   0.02791   0.02411  -0.1022   0.8073   0.0264
  -4.000   0.0941   0.02727   0.02333  -0.1027   0.7894   0.0275
  -3.750   0.1419   0.01671   0.01166  -0.1098   0.7767   0.0327
  -3.500   0.1729   0.01444   0.00886  -0.1112   0.7553   0.0334
  -3.250   0.2018   0.01350   0.00760  -0.1116   0.7279   0.0340
  -3.000   0.2301   0.01294   0.00675  -0.1118   0.6935   0.0345
  -2.750   0.2585   0.01253   0.00607  -0.1120   0.6641   0.0349
  -2.500   0.2867   0.01235   0.00570  -0.1121   0.6422   0.0357
  -2.250   0.3153   0.01202   0.00518  -0.1123   0.6245   0.0364
  -2.000   0.3441   0.01163   0.00460  -0.1125   0.6102   0.0370
  -1.750   0.3728   0.01132   0.00415  -0.1127   0.5976   0.0377
  -1.500   0.4014   0.01108   0.00377  -0.1129   0.5849   0.0388
  -1.250   0.4300   0.01088   0.00347  -0.1130   0.5727   0.0399
  -1.000   0.4586   0.01073   0.00323  -0.1132   0.5611   0.0409
  -0.750   0.4870   0.01063   0.00305  -0.1133   0.5488   0.0416
  -0.500   0.5154   0.01057   0.00291  -0.1134   0.5359   0.0421
  -0.250   0.5442   0.01032   0.00259  -0.1136   0.5233   0.0436
   0.000   0.5727   0.01022   0.00244  -0.1138   0.5101   0.0452
   0.250   0.6010   0.01020   0.00236  -0.1139   0.4962   0.0468
   0.750   0.6575   0.01023   0.00229  -0.1141   0.4694   0.0516
   1.000   0.6857   0.01027   0.00228  -0.1142   0.4569   0.0536
   1.250   0.7138   0.01031   0.00226  -0.1143   0.4430   0.0556
   1.500   0.7419   0.01036   0.00226  -0.1145   0.4292   0.0602
   1.750   0.7699   0.01044   0.00231  -0.1145   0.4162   0.0652
   2.000   0.7979   0.01051   0.00238  -0.1147   0.4062   0.0760
   2.250   0.8260   0.01055   0.00249  -0.1148   0.3973   0.1094
   2.500   0.8539   0.01063   0.00262  -0.1149   0.3894   0.1319
   2.750   0.8818   0.01073   0.00273  -0.1150   0.3814   0.1472
   3.000   0.9096   0.01082   0.00285  -0.1150   0.3740   0.1662
   3.250   0.9373   0.01092   0.00300  -0.1151   0.3662   0.1895
   3.500   0.9654   0.01093   0.00318  -0.1154   0.3591   0.2726
   4.000   1.0136   0.00996   0.00350  -0.1141   0.3446   1.0000
   4.250   1.0410   0.01014   0.00366  -0.1141   0.3379   1.0000
   4.500   1.0684   0.01032   0.00384  -0.1141   0.3326   1.0000
   4.750   1.0957   0.01051   0.00403  -0.1140   0.3254   1.0000
   5.000   1.1225   0.01076   0.00423  -0.1140   0.3119   1.0000
   5.250   1.1490   0.01103   0.00445  -0.1139   0.2965   1.0000
   5.500   1.1753   0.01133   0.00469  -0.1138   0.2806   1.0000
   5.750   1.2011   0.01168   0.00497  -0.1136   0.2607   1.0000
   6.000   1.2261   0.01215   0.00530  -0.1133   0.2300   1.0000
   6.250   1.2435   0.01378   0.00628  -0.1123   0.1176   1.0000
   6.500   1.2631   0.01503   0.00720  -0.1114   0.0540   1.0000
   6.750   1.2849   0.01589   0.00793  -0.1106   0.0266   1.0000
   7.000   1.3083   0.01647   0.00852  -0.1101   0.0173   1.0000
   7.250   1.3316   0.01703   0.00910  -0.1095   0.0142   1.0000
   7.500   1.3538   0.01773   0.00986  -0.1087   0.0114   1.0000
   7.750   1.3765   0.01828   0.01048  -0.1080   0.0106   1.0000
   8.000   1.3984   0.01891   0.01119  -0.1072   0.0098   1.0000
   8.250   1.4193   0.01958   0.01196  -0.1063   0.0089   1.0000
   8.500   1.4385   0.02040   0.01283  -0.1052   0.0081   1.0000
   8.750   1.4558   0.02136   0.01389  -0.1037   0.0074   1.0000
   9.000   1.4738   0.02217   0.01479  -0.1024   0.0070   1.0000
   9.250   1.4900   0.02308   0.01580  -0.1008   0.0067   1.0000
   9.500   1.5044   0.02406   0.01687  -0.0990   0.0063   1.0000
   9.750   1.5170   0.02507   0.01797  -0.0969   0.0060   1.0000
  10.000   1.5270   0.02614   0.01913  -0.0945   0.0058   1.0000
  10.250   1.5319   0.02732   0.02042  -0.0913   0.0056   1.0000
  10.500   1.5345   0.02876   0.02195  -0.0881   0.0054   1.0000
  10.750   1.5327   0.03068   0.02398  -0.0848   0.0052   1.0000
  11.000   1.5315   0.03275   0.02617  -0.0820   0.0051   1.0000
  11.250   1.5352   0.03458   0.02813  -0.0801   0.0049   1.0000
  11.500   1.5382   0.03660   0.03028  -0.0784   0.0048   1.0000
  11.750   1.5398   0.03890   0.03271  -0.0770   0.0046   1.0000
  12.000   1.5403   0.04146   0.03540  -0.0758   0.0044   1.0000
  12.250   1.5394   0.04432   0.03838  -0.0749   0.0043   1.0000
  12.500   1.5376   0.04741   0.04161  -0.0742   0.0042   1.0000
  12.750   1.5354   0.05070   0.04502  -0.0738   0.0041   1.0000
  13.000   1.5332   0.05411   0.04856  -0.0736   0.0040   1.0000
  13.250   1.5300   0.05772   0.05230  -0.0736   0.0040   1.0000
  13.500   1.5268   0.06141   0.05610  -0.0737   0.0039   1.0000
  13.750   1.5229   0.06524   0.06008  -0.0740   0.0038   1.0000
  14.000   1.5182   0.06921   0.06417  -0.0744   0.0038   1.0000
  14.250   1.5130   0.07333   0.06841  -0.0749   0.0037   1.0000
  14.500   1.5078   0.07756   0.07276  -0.0756   0.0037   1.0000
  14.750   1.5020   0.08196   0.07727  -0.0764   0.0036   1.0000
  15.000   1.4953   0.08653   0.08196  -0.0773   0.0036   1.0000
  15.250   1.4882   0.09127   0.08682  -0.0784   0.0035   1.0000
  15.500   1.4802   0.09623   0.09191  -0.0796   0.0035   1.0000
  15.750   1.4711   0.10141   0.09723  -0.0809   0.0034   1.0000
  16.000   1.4604   0.10694   0.10291  -0.0825   0.0034   1.0000
  16.250   1.4489   0.11281   0.10893  -0.0844   0.0034   1.0000
  16.500   1.4396   0.11855   0.11484  -0.0866   0.0033   1.0000
  16.750   1.4297   0.12452   0.12097  -0.0890   0.0033   1.0000
  17.000   1.4191   0.13078   0.12738  -0.0918   0.0033   1.0000
  17.250   1.4078   0.13738   0.13416  -0.0950   0.0033   1.0000
  17.500   1.3967   0.14416   0.14110  -0.0985   0.0033   1.0000
  17.750   1.3846   0.15144   0.14854  -0.1025   0.0033   1.0000
  18.000   1.3722   0.15901   0.15627  -0.1069   0.0033   1.0000
  18.250   1.3595   0.16698   0.16439  -0.1116   0.0033   1.0000
  18.500   1.3461   0.17556   0.17313  -0.1170   0.0033   1.0000
  18.750   1.3325   0.18469   0.18240  -0.1229   0.0033   1.0000
  19.000   1.3182   0.19474   0.19260  -0.1294   0.0033   1.0000
  19.250   1.3018   0.20653   0.20453  -0.1370   0.0033   1.0000
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