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GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 92 AIRFOIL (goe92-il)
Reynolds number: 100,000
Max Cl/Cd: 53.82 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe92-il-100000.txt
Download as CSV file: xf-goe92-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 92 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2666   0.09502   0.09079  -0.0252   1.0000   0.0402
  -7.250  -0.2710   0.09318   0.08905  -0.0242   1.0000   0.0409
  -7.000  -0.2785   0.09164   0.08762  -0.0227   1.0000   0.0416
  -6.750  -0.2867   0.09018   0.08624  -0.0212   1.0000   0.0423
  -6.500  -0.2944   0.08867   0.08481  -0.0200   1.0000   0.0431
  -6.250  -0.2999   0.08702   0.08322  -0.0194   1.0000   0.0440
  -6.000  -0.3023   0.08531   0.08156  -0.0200   1.0000   0.0452
  -5.750  -0.2991   0.08396   0.08023  -0.0231   1.0000   0.0464
  -5.500  -0.2866   0.08330   0.07947  -0.0291   1.0000   0.0473
  -5.250  -0.2754   0.08104   0.07714  -0.0321   0.9996   0.0477
  -5.000  -0.2597   0.07301   0.06929  -0.0312   0.9936   0.0499
  -4.750  -0.2153   0.06775   0.06393  -0.0390   0.9843   0.0540
  -4.500  -0.1309   0.06497   0.06050  -0.0579   0.9720   0.0611
  -4.250  -0.1122   0.05768   0.05347  -0.0594   0.9637   0.0636
  -4.000  -0.0643   0.05336   0.04902  -0.0665   0.9565   0.0717
  -3.750  -0.0201   0.04904   0.04451  -0.0729   0.9455   0.0794
  -3.500   0.0253   0.04526   0.04051  -0.0789   0.9356   0.0940
  -3.250   0.0838   0.04223   0.03701  -0.0868   0.9287   0.1195
  -3.000   0.1164   0.03831   0.03316  -0.0892   0.9169   0.1379
  -2.750   0.1536   0.03575   0.03039  -0.0922   0.9042   0.1784
  -2.000   0.2179   0.02866   0.02361  -0.0884   0.8585   0.3954
  -1.750   0.2358   0.02659   0.02162  -0.0852   0.8405   0.4550
  -1.500   0.2570   0.02448   0.01953  -0.0827   0.8205   0.4925
  -1.250   0.3469   0.02353   0.01648  -0.0931   0.8016   0.2171
  -1.000   0.3861   0.02247   0.01443  -0.0912   0.7810   0.1321
  -0.750   0.4147   0.02101   0.01262  -0.0897   0.7587   0.1150
  -0.500   0.4417   0.01990   0.01124  -0.0883   0.7338   0.1112
  -0.250   0.4693   0.01910   0.01006  -0.0869   0.7088   0.1066
   0.000   0.4963   0.01859   0.00922  -0.0855   0.6838   0.1033
   0.250   0.5223   0.01797   0.00839  -0.0844   0.6582   0.1022
   0.500   0.5477   0.01761   0.00785  -0.0833   0.6331   0.1022
   0.750   0.5728   0.01736   0.00741  -0.0823   0.6107   0.1072
   1.000   0.5983   0.01734   0.00719  -0.0815   0.5891   0.1116
   1.250   0.6251   0.01746   0.00703  -0.0809   0.5711   0.1158
   1.500   0.6521   0.01759   0.00696  -0.0805   0.5555   0.1249
   1.750   0.6763   0.01665   0.00713  -0.0802   0.5420   0.5759
   2.000   0.7094   0.01627   0.00718  -0.0805   0.5289   1.0000
   2.250   0.7358   0.01671   0.00736  -0.0801   0.5179   1.0000
   2.500   0.7623   0.01714   0.00755  -0.0798   0.5087   1.0000
   2.750   0.7886   0.01756   0.00784  -0.0795   0.4995   1.0000
   3.000   0.8148   0.01804   0.00820  -0.0793   0.4917   1.0000
   3.250   0.8413   0.01849   0.00855  -0.0791   0.4848   1.0000
   3.500   0.8675   0.01901   0.00900  -0.0790   0.4786   1.0000
   3.750   0.8936   0.01950   0.00949  -0.0788   0.4721   1.0000
   4.000   0.9203   0.02000   0.00989  -0.0787   0.4667   1.0000
   4.250   0.9453   0.02053   0.01050  -0.0785   0.4599   1.0000
   4.500   0.9718   0.02100   0.01090  -0.0783   0.4546   1.0000
   4.750   0.9967   0.02159   0.01157  -0.0781   0.4485   1.0000
   5.000   1.0223   0.02204   0.01206  -0.0778   0.4421   1.0000
   5.250   1.0475   0.02255   0.01259  -0.0775   0.4358   1.0000
   5.500   1.0723   0.02303   0.01314  -0.0772   0.4288   1.0000
   5.750   1.0981   0.02349   0.01358  -0.0769   0.4228   1.0000
   6.000   1.1217   0.02397   0.01424  -0.0764   0.4150   1.0000
   6.250   1.1474   0.02438   0.01463  -0.0761   0.4086   1.0000
   6.500   1.1704   0.02495   0.01540  -0.0756   0.4015   1.0000
   6.750   1.1967   0.02531   0.01572  -0.0754   0.3949   1.0000
   7.000   1.2205   0.02520   0.01558  -0.0745   0.3816   1.0000
   7.250   1.2426   0.02514   0.01555  -0.0735   0.3678   1.0000
   7.500   1.2636   0.02540   0.01600  -0.0726   0.3567   1.0000
   7.750   1.2847   0.02526   0.01587  -0.0714   0.3415   1.0000
   8.000   1.3047   0.02514   0.01578  -0.0701   0.3255   1.0000
   8.250   1.3239   0.02526   0.01608  -0.0688   0.3121   1.0000
   8.500   1.3420   0.02534   0.01632  -0.0673   0.2973   1.0000
   8.750   1.3570   0.02536   0.01652  -0.0654   0.2765   1.0000
   9.000   1.3719   0.02549   0.01682  -0.0636   0.2488   1.0000
   9.250   1.3872   0.02597   0.01737  -0.0619   0.2104   1.0000
   9.500   1.3885   0.02772   0.01855  -0.0590   0.1474   1.0000
   9.750   1.3894   0.02987   0.02045  -0.0562   0.1112   1.0000
  10.250   1.3705   0.03521   0.02545  -0.0492   0.0469   1.0000
  10.500   1.3639   0.03786   0.02823  -0.0468   0.0431   1.0000
  10.750   1.3596   0.04050   0.03107  -0.0451   0.0408   1.0000
  11.000   1.3532   0.04358   0.03438  -0.0440   0.0391   1.0000
  11.250   1.3445   0.04719   0.03821  -0.0434   0.0381   1.0000
  11.500   1.3340   0.05139   0.04263  -0.0436   0.0375   1.0000
  11.750   1.3216   0.05627   0.04773  -0.0445   0.0371   1.0000
  12.000   1.3078   0.06169   0.05336  -0.0461   0.0369   1.0000
  12.250   1.2930   0.06750   0.05936  -0.0479   0.0367   1.0000
  12.500   1.2779   0.07342   0.06547  -0.0497   0.0366   1.0000
  12.750   1.2635   0.07928   0.07149  -0.0515   0.0365   1.0000
  13.000   1.2502   0.08496   0.07732  -0.0531   0.0363   1.0000
  13.250   1.2386   0.09039   0.08289  -0.0546   0.0362   1.0000
  13.500   1.2290   0.09550   0.08812  -0.0559   0.0359   1.0000
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