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GOE 595 AIRFOIL (goe595-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 595 AIRFOIL (goe595-il)
Reynolds number: 200,000
Max Cl/Cd: 68.76 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe595-il-200000-n5.txt
Download as CSV file: xf-goe595-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 595 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4045   0.08774   0.08435  -0.0371   1.0000   0.0151
  -8.500  -0.4128   0.08487   0.08154  -0.0364   1.0000   0.0149
  -8.250  -0.4250   0.08226   0.07901  -0.0352   1.0000   0.0146
  -8.000  -0.4436   0.07996   0.07679  -0.0332   1.0000   0.0145
  -7.750  -0.4411   0.07456   0.07141  -0.0394   0.9952   0.0141
  -7.500  -0.4276   0.06656   0.06335  -0.0499   0.9883   0.0137
  -7.250  -0.4157   0.05822   0.05487  -0.0585   0.9811   0.0135
  -7.000  -0.4032   0.04938   0.04575  -0.0651   0.9746   0.0130
  -6.750  -0.3912   0.04093   0.03683  -0.0686   0.9680   0.0128
  -6.500  -0.3772   0.03494   0.03031  -0.0696   0.9621   0.0130
  -6.250  -0.3567   0.03128   0.02620  -0.0702   0.9572   0.0137
  -6.000  -0.3310   0.02791   0.02228  -0.0711   0.9543   0.0147
  -5.750  -0.3107   0.02521   0.01902  -0.0701   0.9489   0.0156
  -5.500  -0.2855   0.02296   0.01628  -0.0698   0.9447   0.0162
  -5.250  -0.2553   0.02135   0.01421  -0.0704   0.9421   0.0169
  -5.000  -0.2253   0.01951   0.01225  -0.0714   0.9402   0.0187
  -4.750  -0.1994   0.01871   0.01131  -0.0712   0.9355   0.0207
  -4.500  -0.1704   0.01761   0.01003  -0.0713   0.9311   0.0225
  -4.250  -0.1364   0.01668   0.00890  -0.0725   0.9280   0.0246
  -4.000  -0.1022   0.01550   0.00767  -0.0740   0.9253   0.0283
  -3.750  -0.0783   0.01484   0.00694  -0.0731   0.9178   0.0310
  -3.500  -0.0458   0.01426   0.00625  -0.0740   0.9136   0.0349
  -3.250  -0.0148   0.01354   0.00547  -0.0747   0.9091   0.0400
  -3.000   0.0119   0.01315   0.00499  -0.0743   0.9014   0.0454
  -2.750   0.0462   0.01264   0.00454  -0.0756   0.8966   0.0586
  -2.500   0.0710   0.01234   0.00424  -0.0748   0.8878   0.0841
  -2.250   0.1011   0.01180   0.00395  -0.0754   0.8828   0.1472
  -2.000   0.1252   0.01146   0.00380  -0.0748   0.8754   0.2081
  -1.750   0.1538   0.01112   0.00359  -0.0750   0.8695   0.2703
  -1.500   0.1782   0.01076   0.00345  -0.0744   0.8616   0.3451
  -1.250   0.2020   0.01012   0.00335  -0.0737   0.8547   0.5110
  -1.000   0.2227   0.00971   0.00332  -0.0720   0.8459   0.6212
  -0.750   0.2488   0.00920   0.00330  -0.0710   0.8396   0.7764
  -0.500   0.3317   0.00902   0.00339  -0.0820   0.8352   0.9573
  -0.250   0.3898   0.00898   0.00325  -0.0883   0.8261   0.9888
   0.000   0.4330   0.00894   0.00311  -0.0916   0.8129   1.0000
   0.250   0.4569   0.00892   0.00299  -0.0907   0.7975   1.0000
   0.500   0.4807   0.00891   0.00289  -0.0897   0.7811   1.0000
   0.750   0.5043   0.00893   0.00282  -0.0887   0.7624   1.0000
   1.000   0.5282   0.00897   0.00276  -0.0878   0.7441   1.0000
   1.250   0.5521   0.00904   0.00271  -0.0869   0.7245   1.0000
   1.500   0.5748   0.00914   0.00270  -0.0857   0.7008   1.0000
   1.750   0.5970   0.00928   0.00271  -0.0844   0.6744   1.0000
   2.000   0.6184   0.00944   0.00273  -0.0830   0.6457   1.0000
   2.250   0.6398   0.00963   0.00280  -0.0816   0.6191   1.0000
   2.750   0.6815   0.01006   0.00301  -0.0786   0.5673   1.0000
   3.000   0.7019   0.01031   0.00314  -0.0771   0.5428   1.0000
   3.500   0.7430   0.01084   0.00350  -0.0741   0.5002   1.0000
   3.750   0.7639   0.01111   0.00371  -0.0728   0.4823   1.0000
   4.000   0.7843   0.01142   0.00393  -0.0713   0.4629   1.0000
   4.250   0.8045   0.01173   0.00419  -0.0699   0.4409   1.0000
   4.500   0.8242   0.01208   0.00445  -0.0683   0.4180   1.0000
   4.750   0.8448   0.01238   0.00471  -0.0669   0.3954   1.0000
   5.000   0.8659   0.01267   0.00501  -0.0657   0.3767   1.0000
   5.250   0.8865   0.01298   0.00530  -0.0644   0.3535   1.0000
   5.500   0.9060   0.01335   0.00559  -0.0629   0.3233   1.0000
   5.750   0.9249   0.01376   0.00593  -0.0613   0.2934   1.0000
   6.000   0.9428   0.01427   0.00631  -0.0596   0.2646   1.0000
   6.250   0.9605   0.01481   0.00679  -0.0579   0.2397   1.0000
   6.500   0.9789   0.01533   0.00727  -0.0564   0.2180   1.0000
   6.750   0.9966   0.01591   0.00778  -0.0547   0.1894   1.0000
   7.250   1.0147   0.01851   0.00951  -0.0491   0.0562   1.0000
   7.500   1.0313   0.01921   0.01028  -0.0473   0.0475   1.0000
   7.750   1.0454   0.02008   0.01122  -0.0452   0.0403   1.0000
   8.000   1.0618   0.02070   0.01197  -0.0434   0.0348   1.0000
   8.250   1.0729   0.02160   0.01292  -0.0408   0.0298   1.0000
   8.500   1.0862   0.02231   0.01376  -0.0385   0.0256   1.0000
   8.750   1.0962   0.02324   0.01472  -0.0358   0.0219   1.0000
   9.000   1.1057   0.02419   0.01578  -0.0331   0.0197   1.0000
   9.250   1.1141   0.02523   0.01695  -0.0304   0.0181   1.0000
   9.500   1.1223   0.02633   0.01815  -0.0278   0.0167   1.0000
   9.750   1.1310   0.02742   0.01935  -0.0254   0.0152   1.0000
  10.000   1.1341   0.02897   0.02097  -0.0226   0.0139   1.0000
  10.250   1.1382   0.03057   0.02269  -0.0200   0.0130   1.0000
  10.500   1.1446   0.03208   0.02435  -0.0178   0.0125   1.0000
  10.750   1.1504   0.03377   0.02617  -0.0156   0.0119   1.0000
  11.000   1.1564   0.03554   0.02808  -0.0137   0.0114   1.0000
  11.250   1.1623   0.03736   0.03004  -0.0119   0.0109   1.0000
  11.500   1.1680   0.03919   0.03201  -0.0103   0.0105   1.0000
  11.750   1.1725   0.04114   0.03408  -0.0088   0.0101   1.0000
  12.000   1.1755   0.04307   0.03612  -0.0075   0.0096   1.0000
  12.250   1.1766   0.04565   0.03884  -0.0062   0.0094   1.0000
  12.500   1.1754   0.04860   0.04197  -0.0049   0.0090   1.0000
  12.750   1.1760   0.05118   0.04478  -0.0041   0.0087   1.0000
  13.000   1.1730   0.05446   0.04832  -0.0033   0.0085   1.0000
  13.250   1.1677   0.05805   0.05218  -0.0028   0.0082   1.0000
  13.500   1.1608   0.06194   0.05630  -0.0028   0.0083   1.0000
  13.750   1.1514   0.06627   0.06087  -0.0033   0.0081   1.0000
  14.000   1.1393   0.07117   0.06601  -0.0044   0.0079   1.0000
  14.250   1.1267   0.07642   0.07149  -0.0060   0.0079   1.0000
  14.500   1.1120   0.08231   0.07760  -0.0084   0.0079   1.0000
  14.750   1.0965   0.08871   0.08421  -0.0113   0.0079   1.0000
  15.000   1.0790   0.09591   0.09162  -0.0150   0.0079   1.0000
  15.250   1.0614   0.10352   0.09941  -0.0192   0.0080   1.0000
  15.500   1.0431   0.11173   0.10779  -0.0240   0.0080   1.0000
  15.750   1.0237   0.12073   0.11692  -0.0294   0.0081   1.0000
  16.000   1.0028   0.13081   0.12715  -0.0355   0.0082   1.0000
  16.250   0.9842   0.14090   0.13735  -0.0415   0.0084   1.0000
  16.500   0.9622   0.15286   0.14940  -0.0484   0.0086   1.0000
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