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GOE 599 AIRFOIL (goe599-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 599 AIRFOIL (goe599-il)
Reynolds number: 500,000
Max Cl/Cd: 72.82 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe599-il-500000.txt
Download as CSV file: xf-goe599-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 599 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6751   0.06941   0.06701  -0.0408   1.0000   0.0153
 -10.750  -0.6993   0.05910   0.05661  -0.0507   1.0000   0.0149
 -10.500  -0.7230   0.05229   0.04966  -0.0571   1.0000   0.0146
 -10.250  -0.7493   0.04856   0.04578  -0.0559   1.0000   0.0145
 -10.000  -0.7724   0.04450   0.04149  -0.0532   1.0000   0.0144
  -9.750  -0.7896   0.04036   0.03704  -0.0500   1.0000   0.0144
  -9.500  -0.7992   0.03649   0.03281  -0.0468   1.0000   0.0146
  -9.250  -0.8011   0.03311   0.02905  -0.0438   1.0000   0.0149
  -9.000  -0.7967   0.03023   0.02579  -0.0411   1.0000   0.0152
  -8.750  -0.7871   0.02792   0.02314  -0.0388   1.0000   0.0154
  -8.500  -0.7754   0.02574   0.02062  -0.0368   1.0000   0.0157
  -8.250  -0.7645   0.02247   0.01703  -0.0348   1.0000   0.0162
  -8.000  -0.7465   0.02127   0.01573  -0.0335   1.0000   0.0167
  -7.750  -0.7272   0.02041   0.01478  -0.0323   1.0000   0.0174
  -7.500  -0.7073   0.01953   0.01379  -0.0311   1.0000   0.0181
  -7.250  -0.6868   0.01879   0.01294  -0.0300   1.0000   0.0191
  -7.000  -0.6656   0.01827   0.01230  -0.0289   1.0000   0.0201
  -6.750  -0.6453   0.01701   0.01089  -0.0277   1.0000   0.0210
  -6.500  -0.6204   0.01584   0.00968  -0.0277   0.9994   0.0223
  -6.250  -0.5860   0.01522   0.00901  -0.0294   0.9976   0.0239
  -6.000  -0.5508   0.01468   0.00840  -0.0312   0.9957   0.0259
  -5.750  -0.5164   0.01381   0.00743  -0.0330   0.9943   0.0283
  -5.500  -0.4835   0.01308   0.00669  -0.0344   0.9916   0.0311
  -5.250  -0.4487   0.01262   0.00618  -0.0361   0.9889   0.0341
  -5.000  -0.4137   0.01195   0.00545  -0.0379   0.9867   0.0383
  -4.750  -0.3772   0.01148   0.00495  -0.0400   0.9848   0.0432
  -4.500  -0.3399   0.01106   0.00449  -0.0422   0.9834   0.0493
  -4.250  -0.3085   0.01060   0.00407  -0.0432   0.9787   0.0617
  -4.000  -0.2737   0.01007   0.00379  -0.0449   0.9756   0.1135
  -3.750  -0.2375   0.00962   0.00350  -0.0471   0.9734   0.1487
  -3.500  -0.2007   0.00908   0.00329  -0.0494   0.9717   0.2319
  -3.250  -0.1627   0.00868   0.00310  -0.0520   0.9704   0.2924
  -3.000  -0.1329   0.00836   0.00293  -0.0525   0.9640   0.3355
  -2.750  -0.0982   0.00797   0.00276  -0.0542   0.9606   0.3986
  -2.500  -0.0633   0.00758   0.00261  -0.0558   0.9577   0.4649
  -2.250  -0.0342   0.00725   0.00247  -0.0560   0.9496   0.5234
  -2.000  -0.0020   0.00692   0.00228  -0.0568   0.9425   0.5767
  -1.750   0.0245   0.00667   0.00214  -0.0562   0.9304   0.6152
  -1.500   0.0520   0.00648   0.00204  -0.0560   0.9202   0.6472
  -1.250   0.0802   0.00630   0.00195  -0.0559   0.9111   0.6810
  -1.000   0.1076   0.00613   0.00188  -0.0556   0.9005   0.7162
  -0.750   0.1342   0.00597   0.00183  -0.0551   0.8887   0.7549
  -0.500   0.1604   0.00583   0.00176  -0.0543   0.8736   0.7929
  -0.250   0.1859   0.00574   0.00172  -0.0534   0.8566   0.8316
   0.000   0.2107   0.00570   0.00173  -0.0523   0.8414   0.8701
   0.250   0.2356   0.00571   0.00175  -0.0512   0.8260   0.9074
   0.500   0.2629   0.00576   0.00179  -0.0507   0.8088   0.9392
   0.750   0.2956   0.00584   0.00181  -0.0515   0.7919   0.9612
   1.000   0.3318   0.00592   0.00184  -0.0532   0.7755   0.9778
   1.250   0.3712   0.00603   0.00187  -0.0556   0.7532   0.9899
   1.500   0.4152   0.00612   0.00191  -0.0591   0.7285   0.9990
   1.750   0.4415   0.00622   0.00190  -0.0588   0.6991   1.0000
   2.000   0.4643   0.00638   0.00191  -0.0577   0.6578   1.0000
   2.250   0.4857   0.00667   0.00194  -0.0564   0.5992   1.0000
   2.500   0.5058   0.00711   0.00204  -0.0549   0.5242   1.0000
   2.750   0.5247   0.00772   0.00222  -0.0533   0.4308   1.0000
   3.000   0.5447   0.00833   0.00245  -0.0519   0.3467   1.0000
   3.250   0.5589   0.00967   0.00290  -0.0499   0.1563   1.0000
   3.500   0.5797   0.01041   0.00327  -0.0487   0.0816   1.0000
   3.750   0.6041   0.01075   0.00355  -0.0481   0.0722   1.0000
   4.000   0.6293   0.01101   0.00385  -0.0476   0.0695   1.0000
   4.250   0.6542   0.01132   0.00417  -0.0471   0.0665   1.0000
   4.500   0.6787   0.01169   0.00454  -0.0465   0.0638   1.0000
   4.750   0.7024   0.01215   0.00502  -0.0457   0.0613   1.0000
   5.000   0.7248   0.01277   0.00571  -0.0447   0.0592   1.0000
   5.250   0.7495   0.01313   0.00610  -0.0442   0.0584   1.0000
   5.500   0.7742   0.01345   0.00646  -0.0437   0.0563   1.0000
   5.750   0.7986   0.01383   0.00686  -0.0431   0.0536   1.0000
   6.000   0.8222   0.01429   0.00735  -0.0425   0.0511   1.0000
   6.250   0.8428   0.01514   0.00821  -0.0413   0.0481   1.0000
   6.500   0.8651   0.01584   0.00897  -0.0405   0.0461   1.0000
   6.750   0.8908   0.01599   0.00917  -0.0402   0.0438   1.0000
   7.000   0.9160   0.01619   0.00942  -0.0398   0.0407   1.0000
   7.250   0.9389   0.01669   0.00989  -0.0392   0.0375   1.0000
   7.500   0.9625   0.01711   0.01039  -0.0386   0.0344   1.0000
   7.750   0.9895   0.01705   0.01034  -0.0385   0.0308   1.0000
   8.000   1.0124   0.01750   0.01078  -0.0378   0.0274   1.0000
   8.250   1.0376   0.01768   0.01101  -0.0375   0.0246   1.0000
   8.500   1.0600   0.01817   0.01146  -0.0367   0.0222   1.0000
   8.750   1.0797   0.01900   0.01239  -0.0354   0.0206   1.0000
   9.000   1.1010   0.01960   0.01306  -0.0344   0.0191   1.0000
   9.250   1.1223   0.02014   0.01364  -0.0335   0.0178   1.0000
   9.500   1.1365   0.02156   0.01513  -0.0316   0.0165   1.0000
   9.750   1.1558   0.02237   0.01607  -0.0303   0.0158   1.0000
  10.000   1.1733   0.02337   0.01719  -0.0289   0.0151   1.0000
  10.250   1.1901   0.02438   0.01832  -0.0274   0.0144   1.0000
  10.500   1.2061   0.02540   0.01942  -0.0258   0.0138   1.0000
  10.750   1.2199   0.02659   0.02071  -0.0240   0.0133   1.0000
  11.000   1.2278   0.02852   0.02282  -0.0215   0.0128   1.0000
  11.250   1.2293   0.03141   0.02600  -0.0182   0.0125   1.0000
  11.500   1.2363   0.03291   0.02771  -0.0156   0.0123   1.0000
  11.750   1.2408   0.03463   0.02965  -0.0129   0.0121   1.0000
  12.000   1.2429   0.03654   0.03178  -0.0102   0.0118   1.0000
  12.250   1.2425   0.03867   0.03413  -0.0077   0.0115   1.0000
  12.500   1.2391   0.04111   0.03679  -0.0053   0.0112   1.0000
  12.750   1.2347   0.04370   0.03957  -0.0034   0.0110   1.0000
  13.000   1.2270   0.04679   0.04287  -0.0019   0.0109   1.0000
  13.250   1.2165   0.05042   0.04670  -0.0011   0.0107   1.0000
  13.500   1.2016   0.05487   0.05138  -0.0010   0.0107   1.0000
  13.750   1.1820   0.06042   0.05717  -0.0021   0.0106   1.0000
  14.000   1.1574   0.06733   0.06433  -0.0048   0.0107   1.0000
  14.250   1.1196   0.07762   0.07492  -0.0103   0.0108   1.0000
  14.500   1.0708   0.09212   0.08973  -0.0196   0.0112   1.0000
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