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GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 505 AIRFOIL (goe505-il)
Reynolds number: 500,000
Max Cl/Cd: 69.21 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe505-il-500000-n5.txt
Download as CSV file: xf-goe505-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 505 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3659   0.03222   0.02868  -0.1608   0.9146   0.0236
 -11.250  -0.3719   0.03022   0.02645  -0.1580   0.9017   0.0240
 -11.000  -0.3711   0.02834   0.02432  -0.1558   0.8916   0.0242
 -10.500  -0.3556   0.02552   0.02104  -0.1518   0.8762   0.0248
 -10.250  -0.3432   0.02433   0.01961  -0.1501   0.8701   0.0250
 -10.000  -0.3303   0.02339   0.01850  -0.1481   0.8642   0.0252
  -9.750  -0.3148   0.02257   0.01749  -0.1465   0.8592   0.0253
  -9.500  -0.2988   0.02157   0.01630  -0.1450   0.8551   0.0255
  -9.250  -0.2868   0.02027   0.01485  -0.1428   0.8509   0.0260
  -9.000  -0.2698   0.01946   0.01394  -0.1412   0.8468   0.0263
  -8.750  -0.2505   0.01878   0.01316  -0.1400   0.8432   0.0266
  -8.500  -0.2296   0.01815   0.01241  -0.1390   0.8403   0.0269
  -8.250  -0.2087   0.01754   0.01170  -0.1379   0.8374   0.0271
  -8.000  -0.1889   0.01699   0.01106  -0.1365   0.8341   0.0273
  -7.750  -0.1679   0.01646   0.01045  -0.1353   0.8309   0.0276
  -7.500  -0.1456   0.01597   0.00986  -0.1344   0.8273   0.0279
  -7.250  -0.1216   0.01550   0.00927  -0.1337   0.8236   0.0283
  -7.000  -0.1002   0.01507   0.00877  -0.1325   0.8194   0.0285
  -6.750  -0.0787   0.01467   0.00829  -0.1312   0.8145   0.0289
  -6.500  -0.0550   0.01430   0.00783  -0.1304   0.8102   0.0293
  -6.250  -0.0294   0.01395   0.00738  -0.1300   0.8064   0.0297
  -6.000  -0.0082   0.01363   0.00702  -0.1286   0.8018   0.0301
  -5.750   0.0144   0.01331   0.00664  -0.1275   0.7971   0.0304
  -5.500   0.0389   0.01301   0.00626  -0.1268   0.7925   0.0306
  -5.250   0.0626   0.01275   0.00594  -0.1259   0.7875   0.0308
  -5.000   0.0844   0.01249   0.00565  -0.1245   0.7807   0.0311
  -4.750   0.1079   0.01215   0.00522  -0.1236   0.7740   0.0314
  -4.500   0.1295   0.01184   0.00489  -0.1223   0.7681   0.0320
  -4.250   0.1530   0.01159   0.00461  -0.1213   0.7633   0.0325
  -4.000   0.1776   0.01137   0.00435  -0.1206   0.7589   0.0331
  -3.750   0.2016   0.01118   0.00413  -0.1197   0.7542   0.0337
  -3.500   0.2246   0.01100   0.00393  -0.1186   0.7479   0.0344
  -3.250   0.2487   0.01085   0.00373  -0.1177   0.7418   0.0352
  -3.000   0.2717   0.01071   0.00357  -0.1166   0.7351   0.0361
  -2.750   0.2948   0.01059   0.00340  -0.1155   0.7275   0.0373
  -2.500   0.3175   0.01046   0.00325  -0.1143   0.7192   0.0388
  -2.250   0.3392   0.01034   0.00310  -0.1129   0.7090   0.0412
  -2.000   0.3600   0.01022   0.00297  -0.1113   0.6962   0.0452
  -1.750   0.3783   0.01005   0.00285  -0.1093   0.6801   0.0700
  -1.500   0.3947   0.01001   0.00277  -0.1068   0.6591   0.0846
  -1.250   0.4078   0.01006   0.00271  -0.1035   0.6336   0.0957
  -1.000   0.4193   0.01013   0.00269  -0.1000   0.6079   0.1069
  -0.750   0.4274   0.01024   0.00270  -0.0957   0.5832   0.1165
  -0.500   0.4372   0.01034   0.00273  -0.0919   0.5587   0.1291
  -0.250   0.4462   0.01048   0.00281  -0.0880   0.5345   0.1474
   0.000   0.4573   0.01066   0.00293  -0.0845   0.5100   0.1645
   0.250   0.4686   0.01089   0.00306  -0.0811   0.4868   0.1761
   0.500   0.4816   0.01111   0.00320  -0.0781   0.4649   0.1856
   0.750   0.4954   0.01135   0.00334  -0.0753   0.4448   0.1933
   1.000   0.5099   0.01156   0.00349  -0.0727   0.4267   0.2011
   1.250   0.5252   0.01179   0.00363  -0.0703   0.4103   0.2097
   1.500   0.5412   0.01198   0.00378  -0.0680   0.3968   0.2176
   1.750   0.5580   0.01218   0.00392  -0.0659   0.3851   0.2242
   2.000   0.5751   0.01235   0.00408  -0.0639   0.3746   0.2367
   2.500   0.6111   0.01267   0.00439  -0.0602   0.3593   0.2615
   2.750   0.6288   0.01283   0.00457  -0.0584   0.3525   0.2812
   3.000   0.6468   0.01297   0.00475  -0.0566   0.3451   0.3054
   3.250   0.6642   0.01316   0.00495  -0.0547   0.3396   0.3278
   3.500   0.6832   0.01329   0.00513  -0.0532   0.3349   0.3503
   3.750   0.7021   0.01343   0.00531  -0.0516   0.3302   0.3768
   4.000   0.7195   0.01356   0.00551  -0.0498   0.3255   0.4129
   4.250   0.7187   0.01296   0.00574  -0.0443   0.3222   0.7463
   4.750   0.9473   0.01379   0.00696  -0.0830   0.3051   1.0000
   5.000   0.9645   0.01398   0.00715  -0.0811   0.3025   1.0000
   5.250   0.9815   0.01420   0.00736  -0.0792   0.2998   1.0000
   5.500   0.9987   0.01443   0.00758  -0.0774   0.2971   1.0000
   5.750   1.0154   0.01469   0.00784  -0.0755   0.2943   1.0000
   6.000   1.0315   0.01499   0.00812  -0.0736   0.2915   1.0000
   6.250   1.0480   0.01530   0.00841  -0.0718   0.2890   1.0000
   6.500   1.0669   0.01554   0.00867  -0.0704   0.2870   1.0000
   6.750   1.0852   0.01580   0.00894  -0.0690   0.2830   1.0000
   7.000   1.1014   0.01616   0.00927  -0.0672   0.2767   1.0000
   7.250   1.1181   0.01653   0.00961  -0.0656   0.2724   1.0000
   7.500   1.1368   0.01682   0.00992  -0.0643   0.2681   1.0000
   7.750   1.1538   0.01720   0.01029  -0.0628   0.2621   1.0000
   8.000   1.1702   0.01762   0.01069  -0.0612   0.2571   1.0000
   8.250   1.1880   0.01800   0.01107  -0.0599   0.2496   1.0000
   8.500   1.2034   0.01849   0.01152  -0.0583   0.2415   1.0000
   8.750   1.2179   0.01906   0.01202  -0.0567   0.2281   1.0000
   9.000   1.2326   0.01964   0.01256  -0.0551   0.2165   1.0000
   9.250   1.2445   0.02038   0.01322  -0.0532   0.2001   1.0000
   9.500   1.2523   0.02140   0.01409  -0.0508   0.1776   1.0000
   9.750   1.2616   0.02237   0.01496  -0.0487   0.1628   1.0000
  10.000   1.2679   0.02354   0.01602  -0.0464   0.1449   1.0000
  10.250   1.2742   0.02476   0.01712  -0.0441   0.1234   1.0000
  10.500   1.2425   0.02859   0.02046  -0.0380   0.0370   1.0000
  10.750   1.2452   0.03022   0.02206  -0.0357   0.0180   1.0000
  11.000   1.2552   0.03134   0.02323  -0.0342   0.0160   1.0000
  11.250   1.2658   0.03244   0.02438  -0.0328   0.0149   1.0000
  11.500   1.2763   0.03358   0.02558  -0.0315   0.0142   1.0000
  11.750   1.2850   0.03489   0.02696  -0.0302   0.0133   1.0000
  12.000   1.2927   0.03632   0.02846  -0.0288   0.0127   1.0000
  12.250   1.2991   0.03788   0.03010  -0.0274   0.0121   1.0000
  12.500   1.3067   0.03937   0.03167  -0.0263   0.0119   1.0000
  12.750   1.3134   0.04100   0.03337  -0.0251   0.0114   1.0000
  13.000   1.3191   0.04277   0.03522  -0.0240   0.0111   1.0000
  13.250   1.3234   0.04472   0.03726  -0.0230   0.0108   1.0000
  13.500   1.3269   0.04682   0.03943  -0.0221   0.0104   1.0000
  13.750   1.3288   0.04913   0.04183  -0.0212   0.0102   1.0000
  14.000   1.3284   0.05177   0.04456  -0.0204   0.0099   1.0000
  14.250   1.3260   0.05474   0.04762  -0.0198   0.0096   1.0000
  14.500   1.3201   0.05822   0.05122  -0.0193   0.0095   1.0000
  14.750   1.3168   0.06150   0.05460  -0.0190   0.0093   1.0000
  15.000   1.3148   0.06473   0.05793  -0.0189   0.0091   1.0000
  15.250   1.3092   0.06849   0.06182  -0.0190   0.0089   1.0000
  15.500   1.3006   0.07279   0.06623  -0.0193   0.0089   1.0000
  15.750   1.2920   0.07715   0.07072  -0.0198   0.0087   1.0000
  16.000   1.2814   0.08191   0.07559  -0.0205   0.0087   1.0000
  16.250   1.2699   0.08690   0.08071  -0.0214   0.0086   1.0000
  16.500   1.2595   0.09180   0.08572  -0.0224   0.0086   1.0000
  16.750   1.2477   0.09695   0.09099  -0.0235   0.0084   1.0000
  17.000   1.2359   0.10217   0.09632  -0.0247   0.0082   1.0000
  17.250   1.2240   0.10745   0.10170  -0.0260   0.0082   1.0000
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