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GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 92 AIRFOIL (goe92-il)
Reynolds number: 100,000
Max Cl/Cd: 54.99 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe92-il-100000-n5.txt
Download as CSV file: xf-goe92-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2434   0.09913   0.09490  -0.0273   1.0000   0.0267
  -7.500  -0.2503   0.09784   0.09372  -0.0259   1.0000   0.0271
  -7.250  -0.2637   0.09717   0.09316  -0.0231   1.0000   0.0273
  -7.000  -0.2548   0.09484   0.09088  -0.0276   0.9931   0.0278
  -6.750  -0.2265   0.09126   0.08727  -0.0382   0.9821   0.0282
  -6.500  -0.1955   0.08728   0.08324  -0.0480   0.9724   0.0285
  -6.250  -0.1624   0.08291   0.07879  -0.0567   0.9640   0.0286
  -6.000  -0.1299   0.07839   0.07418  -0.0639   0.9552   0.0286
  -5.750  -0.1119   0.07268   0.06850  -0.0659   0.9462   0.0290
  -5.500  -0.0919   0.06771   0.06352  -0.0674   0.9381   0.0298
  -5.250  -0.0662   0.06362   0.05936  -0.0710   0.9267   0.0307
  -5.000  -0.0383   0.05977   0.05542  -0.0752   0.9141   0.0317
  -4.750  -0.0095   0.05612   0.05164  -0.0793   0.9012   0.0330
  -4.500   0.0199   0.05266   0.04803  -0.0830   0.8885   0.0347
  -4.250   0.0695   0.05099   0.04579  -0.0895   0.8758   0.0387
  -4.000   0.0827   0.04590   0.04080  -0.0899   0.8646   0.0406
  -3.750   0.1045   0.04309   0.03791  -0.0906   0.8522   0.0437
  -3.500   0.1451   0.04224   0.03642  -0.0930   0.8388   0.0513
  -3.250   0.1642   0.03771   0.03191  -0.0936   0.8253   0.0536
  -3.000   0.1863   0.03526   0.02937  -0.0938   0.8097   0.0584
  -2.750   0.2120   0.03316   0.02703  -0.0943   0.7928   0.0728
  -2.250   0.2750   0.02791   0.02084  -0.0938   0.7572   0.0465
  -2.000   0.3040   0.02577   0.01825  -0.0934   0.7368   0.0446
  -1.750   0.3326   0.02423   0.01626  -0.0929   0.7135   0.0474
  -1.500   0.3612   0.02261   0.01415  -0.0922   0.6905   0.0464
  -1.250   0.3895   0.02153   0.01255  -0.0915   0.6676   0.0490
  -1.000   0.4173   0.02077   0.01130  -0.0907   0.6451   0.0508
  -0.750   0.4444   0.01991   0.01005  -0.0901   0.6242   0.0511
  -0.500   0.4710   0.01920   0.00903  -0.0894   0.6043   0.0520
  -0.250   0.4967   0.01839   0.00809  -0.0890   0.5853   0.0567
   0.000   0.5228   0.01796   0.00747  -0.0884   0.5674   0.0572
   0.250   0.5485   0.01761   0.00696  -0.0878   0.5506   0.0572
   0.500   0.5742   0.01735   0.00656  -0.0872   0.5347   0.0575
   0.750   0.5997   0.01720   0.00624  -0.0867   0.5193   0.0581
   1.000   0.6256   0.01714   0.00599  -0.0862   0.5043   0.0593
   1.250   0.6520   0.01716   0.00580  -0.0858   0.4897   0.0610
   1.500   0.6784   0.01722   0.00567  -0.0855   0.4758   0.0635
   1.750   0.7049   0.01729   0.00561  -0.0852   0.4631   0.0690
   2.000   0.7313   0.01736   0.00561  -0.0850   0.4518   0.0865
   2.250   0.7585   0.01571   0.00574  -0.0851   0.4424   1.0000
   2.500   0.7844   0.01600   0.00583  -0.0847   0.4334   1.0000
   2.750   0.8104   0.01631   0.00597  -0.0844   0.4256   1.0000
   3.000   0.8362   0.01662   0.00613  -0.0841   0.4185   1.0000
   3.250   0.8621   0.01695   0.00634  -0.0838   0.4117   1.0000
   3.500   0.8879   0.01728   0.00659  -0.0836   0.4053   1.0000
   3.750   0.9136   0.01763   0.00683  -0.0833   0.3999   1.0000
   4.000   0.9394   0.01797   0.00716  -0.0831   0.3941   1.0000
   4.250   0.9650   0.01833   0.00746  -0.0829   0.3891   1.0000
   4.500   0.9906   0.01871   0.00782  -0.0826   0.3842   1.0000
   4.750   1.0160   0.01908   0.00821  -0.0824   0.3786   1.0000
   5.000   1.0412   0.01946   0.00855  -0.0821   0.3733   1.0000
   5.250   1.0662   0.01984   0.00901  -0.0818   0.3673   1.0000
   5.500   1.0910   0.02022   0.00942  -0.0815   0.3615   1.0000
   5.750   1.1159   0.02064   0.00982  -0.0812   0.3568   1.0000
   6.000   1.1406   0.02105   0.01037  -0.0809   0.3516   1.0000
   6.250   1.1652   0.02147   0.01090  -0.0805   0.3467   1.0000
   6.500   1.1899   0.02191   0.01136  -0.0802   0.3423   1.0000
   6.750   1.2126   0.02228   0.01192  -0.0796   0.3340   1.0000
   7.000   1.2317   0.02249   0.01215  -0.0784   0.3169   1.0000
   7.250   1.2503   0.02276   0.01248  -0.0772   0.2993   1.0000
   7.500   1.2697   0.02309   0.01292  -0.0761   0.2821   1.0000
   7.750   1.2896   0.02345   0.01344  -0.0752   0.2614   1.0000
   8.000   1.3079   0.02395   0.01397  -0.0740   0.2284   1.0000
   8.250   1.3103   0.02585   0.01513  -0.0714   0.1422   1.0000
   8.500   1.3168   0.02775   0.01685  -0.0691   0.1076   1.0000
   8.750   1.3101   0.03064   0.01931  -0.0657   0.0285   1.0000
   9.000   1.3111   0.03246   0.02121  -0.0627   0.0229   1.0000
   9.250   1.3162   0.03398   0.02293  -0.0603   0.0211   1.0000
   9.500   1.3198   0.03567   0.02486  -0.0581   0.0202   1.0000
   9.750   1.3213   0.03764   0.02707  -0.0561   0.0194   1.0000
  10.000   1.3203   0.03994   0.02962  -0.0544   0.0186   1.0000
  10.250   1.3167   0.04267   0.03258  -0.0530   0.0178   1.0000
  10.500   1.3104   0.04588   0.03603  -0.0521   0.0170   1.0000
  10.750   1.3017   0.04964   0.04003  -0.0517   0.0164   1.0000
  11.000   1.2911   0.05401   0.04463  -0.0521   0.0160   1.0000
  11.250   1.2789   0.05899   0.04984  -0.0531   0.0157   1.0000
  11.500   1.2657   0.06445   0.05551  -0.0546   0.0156   1.0000
  11.750   1.2516   0.07021   0.06147  -0.0563   0.0155   1.0000
  12.000   1.2372   0.07616   0.06761  -0.0581   0.0154   1.0000
  12.250   1.2230   0.08212   0.07374  -0.0599   0.0154   1.0000
  12.500   1.2097   0.08804   0.07983  -0.0617   0.0153   1.0000
  12.750   1.1974   0.09386   0.08580  -0.0634   0.0152   1.0000
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