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GOE 499 AIRFOIL (goe499-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 499 AIRFOIL (goe499-il)
Reynolds number: 1,000,000
Max Cl/Cd: 111.87 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe499-il-1000000-n5.txt
Download as CSV file: xf-goe499-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 499 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2707   0.10641   0.10472  -0.0625   0.9806   0.0046
 -10.500  -0.2602   0.10252   0.10083  -0.0656   0.9781   0.0048
  -9.500  -0.3243   0.02033   0.01762  -0.1675   0.9091   0.0059
  -9.250  -0.2979   0.01692   0.01377  -0.1714   0.9033   0.0063
  -9.000  -0.2709   0.01528   0.01182  -0.1730   0.8985   0.0067
  -8.750  -0.2438   0.01400   0.01035  -0.1742   0.8941   0.0079
  -8.500  -0.2165   0.01291   0.00907  -0.1751   0.8894   0.0090
  -8.250  -0.1890   0.01238   0.00846  -0.1755   0.8852   0.0110
  -8.000  -0.1611   0.01323   0.00950  -0.1749   0.8817   0.0127
  -7.750  -0.1335   0.01322   0.00948  -0.1749   0.8778   0.0144
  -7.500  -0.1058   0.01382   0.01015  -0.1745   0.8738   0.0160
  -7.250  -0.0781   0.01398   0.01027  -0.1745   0.8701   0.0175
  -7.000  -0.0504   0.01389   0.01011  -0.1746   0.8663   0.0189
  -6.750  -0.0228   0.01381   0.00995  -0.1747   0.8619   0.0201
  -6.500   0.0046   0.01397   0.01007  -0.1746   0.8571   0.0210
  -6.250   0.0321   0.01399   0.01004  -0.1746   0.8523   0.0215
  -6.000   0.0596   0.01416   0.01017  -0.1745   0.8474   0.0219
  -5.750   0.0871   0.01443   0.01040  -0.1743   0.8431   0.0222
  -5.500   0.1155   0.01223   0.00783  -0.1760   0.8391   0.0236
  -5.250   0.1434   0.01149   0.00697  -0.1765   0.8345   0.0245
  -5.000   0.1713   0.01099   0.00636  -0.1767   0.8301   0.0250
  -4.750   0.1993   0.01050   0.00576  -0.1770   0.8263   0.0252
  -4.500   0.2275   0.01000   0.00514  -0.1773   0.8220   0.0254
  -4.250   0.2556   0.00955   0.00459  -0.1774   0.8175   0.0255
  -4.000   0.2836   0.00915   0.00408  -0.1776   0.8133   0.0255
  -3.750   0.3118   0.00883   0.00370  -0.1778   0.8091   0.0258
  -3.500   0.3399   0.00847   0.00326  -0.1779   0.8049   0.0257
  -3.250   0.3680   0.00815   0.00285  -0.1780   0.8009   0.0255
  -3.000   0.3963   0.00787   0.00251  -0.1781   0.7967   0.0253
  -2.750   0.4244   0.00763   0.00221  -0.1782   0.7916   0.0251
  -2.500   0.4523   0.00745   0.00196  -0.1782   0.7861   0.0250
  -2.250   0.4804   0.00728   0.00175  -0.1783   0.7801   0.0249
  -2.000   0.5084   0.00714   0.00155  -0.1783   0.7744   0.0249
  -1.750   0.5364   0.00702   0.00139  -0.1783   0.7700   0.0249
  -1.500   0.5646   0.00690   0.00125  -0.1784   0.7652   0.0249
  -1.250   0.5925   0.00681   0.00112  -0.1784   0.7599   0.0251
  -1.000   0.6203   0.00674   0.00101  -0.1783   0.7529   0.0255
  -0.750   0.6474   0.00670   0.00091  -0.1782   0.7410   0.0265
  -0.500   0.6745   0.00669   0.00086  -0.1779   0.7272   0.0286
  -0.250   0.7012   0.00671   0.00083  -0.1777   0.7097   0.0313
   0.000   0.7269   0.00681   0.00083  -0.1772   0.6844   0.0330
   0.250   0.7521   0.00695   0.00086  -0.1766   0.6543   0.0360
   0.500   0.7763   0.00718   0.00094  -0.1759   0.6139   0.0442
   0.750   0.8002   0.00737   0.00107  -0.1752   0.5693   0.1006
   1.000   0.8249   0.00757   0.00120  -0.1747   0.5365   0.1253
   1.250   0.8502   0.00771   0.00135  -0.1743   0.5122   0.1676
   1.500   0.8742   0.00800   0.00153  -0.1736   0.4749   0.1955
   1.750   0.8981   0.00828   0.00174  -0.1730   0.4388   0.2345
   2.000   0.9239   0.00839   0.00190  -0.1727   0.4206   0.2816
   2.250   0.9492   0.00851   0.00207  -0.1723   0.3988   0.3437
   2.500   0.9733   0.00870   0.00232  -0.1718   0.3615   0.4518
   2.750   0.9879   0.00989   0.00292  -0.1697   0.2233   0.4976
   3.000   1.0050   0.01095   0.00353  -0.1680   0.1077   0.5351
   3.250   1.0247   0.01174   0.00405  -0.1666   0.0196   0.5781
   3.500   1.0499   0.01187   0.00432  -0.1662   0.0157   0.6471
   4.000   1.0968   0.01180   0.00489  -0.1645   0.0107   1.0000
   4.250   1.1215   0.01208   0.00517  -0.1639   0.0097   1.0000
   4.500   1.1459   0.01238   0.00549  -0.1633   0.0087   1.0000
   4.750   1.1696   0.01275   0.00585  -0.1625   0.0076   1.0000
   5.000   1.1928   0.01316   0.00630  -0.1617   0.0067   1.0000
   5.250   1.2163   0.01352   0.00669  -0.1609   0.0063   1.0000
   5.500   1.2393   0.01392   0.00711  -0.1601   0.0058   1.0000
   5.750   1.2619   0.01433   0.00755  -0.1591   0.0054   1.0000
   6.000   1.2842   0.01476   0.00799  -0.1582   0.0051   1.0000
   6.250   1.3051   0.01532   0.00859  -0.1570   0.0047   1.0000
   6.500   1.3234   0.01610   0.00944  -0.1553   0.0044   1.0000
   6.750   1.3441   0.01660   0.00999  -0.1541   0.0042   1.0000
   7.000   1.3640   0.01715   0.01059  -0.1527   0.0039   1.0000
   7.250   1.3831   0.01774   0.01122  -0.1513   0.0037   1.0000
   7.500   1.4006   0.01843   0.01197  -0.1495   0.0035   1.0000
   7.750   1.4169   0.01912   0.01272  -0.1476   0.0033   1.0000
   8.000   1.4322   0.01977   0.01341  -0.1454   0.0032   1.0000
   8.250   1.4463   0.02048   0.01420  -0.1431   0.0031   1.0000
   8.500   1.4600   0.02123   0.01500  -0.1408   0.0030   1.0000
   8.750   1.4724   0.02209   0.01592  -0.1384   0.0029   1.0000
   9.000   1.4811   0.02333   0.01725  -0.1354   0.0028   1.0000
   9.250   1.4884   0.02486   0.01891  -0.1323   0.0027   1.0000
   9.500   1.5002   0.02602   0.02017  -0.1300   0.0026   1.0000
   9.750   1.5113   0.02733   0.02161  -0.1277   0.0026   1.0000
  10.000   1.5219   0.02886   0.02327  -0.1254   0.0025   1.0000
  10.250   1.5322   0.03069   0.02527  -0.1230   0.0024   1.0000
  10.500   1.5424   0.03303   0.02783  -0.1208   0.0023   1.0000
  11.000   1.5559   0.04427   0.04000  -0.1154   0.0020   1.0000
  11.250   1.5535   0.04754   0.04351  -0.1121   0.0019   1.0000
  11.500   1.5473   0.05096   0.04716  -0.1087   0.0018   1.0000
  11.750   1.5348   0.05529   0.05175  -0.1052   0.0018   1.0000
  12.000   1.5235   0.05913   0.05584  -0.1023   0.0018   1.0000
  12.250   1.5072   0.06384   0.06078  -0.0997   0.0018   1.0000
  12.500   1.4876   0.06910   0.06626  -0.0977   0.0017   1.0000
  12.750   1.4604   0.07583   0.07321  -0.0963   0.0017   1.0000
  13.000   1.4409   0.08151   0.07908  -0.0961   0.0017   1.0000
  13.250   1.4181   0.08814   0.08590  -0.0969   0.0017   1.0000
  13.500   1.3867   0.09701   0.09499  -0.0994   0.0018   1.0000
  13.750   1.3651   0.10472   0.10285  -0.1026   0.0018   1.0000
  14.000   1.3407   0.11396   0.11225  -0.1075   0.0018   1.0000
  14.250   1.3066   0.12704   0.12553  -0.1154   0.0018   1.0000
  14.500   1.2827   0.13897   0.13760  -0.1234   0.0018   1.0000
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