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GOE 368 AIRFOIL (goe368-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 368 AIRFOIL (goe368-il)
Reynolds number: 200,000
Max Cl/Cd: 64.35 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe368-il-200000.txt
Download as CSV file: xf-goe368-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 368 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4112   0.10336   0.09994  -0.0027   1.0000   0.0386
  -8.500  -0.4071   0.10020   0.09681  -0.0042   1.0000   0.0400
  -8.250  -0.4082   0.09733   0.09400  -0.0074   1.0000   0.0422
  -8.000  -0.3277   0.08178   0.07875  -0.0118   1.0000   0.0457
  -7.750  -0.3206   0.07862   0.07560  -0.0116   1.0000   0.0474
  -7.500  -0.3174   0.07537   0.07239  -0.0121   1.0000   0.0492
  -7.250  -0.4052   0.08342   0.08032  -0.0138   1.0000   0.0452
  -7.000  -0.3947   0.08096   0.07787  -0.0126   1.0000   0.0469
  -6.750  -0.3870   0.07803   0.07497  -0.0139   1.0000   0.0491
  -6.500  -0.3794   0.07459   0.07156  -0.0169   1.0000   0.0519
  -6.250  -0.3613   0.06849   0.06538  -0.0318   1.0000   0.0559
  -6.000  -0.3589   0.06509   0.06205  -0.0279   1.0000   0.0575
  -5.750  -0.3473   0.06323   0.06023  -0.0259   1.0000   0.0602
  -5.500  -0.3257   0.05715   0.05400  -0.0353   1.0000   0.0687
  -5.250  -0.3158   0.05563   0.05253  -0.0318   1.0000   0.0709
  -5.000  -0.2937   0.05143   0.04820  -0.0365   1.0000   0.0810
  -4.750  -0.2820   0.05041   0.04727  -0.0332   1.0000   0.0854
  -4.500  -0.2467   0.02753   0.02277  -0.0460   1.0000   0.0438
  -4.250  -0.2271   0.02170   0.01634  -0.0458   1.0000   0.0370
  -4.000  -0.2026   0.01909   0.01295  -0.0446   1.0000   0.0333
  -3.750  -0.1798   0.01792   0.01149  -0.0433   1.0000   0.0325
  -3.500  -0.1581   0.01654   0.00992  -0.0421   1.0000   0.0325
  -3.250  -0.1218   0.01484   0.00808  -0.0437   0.9952   0.0335
  -3.000  -0.0769   0.01357   0.00677  -0.0471   0.9855   0.0387
  -2.750  -0.0320   0.01272   0.00575  -0.0501   0.9734   0.0426
  -2.500   0.0117   0.01174   0.00467  -0.0528   0.9595   0.0544
  -2.250   0.0567   0.01224   0.00544  -0.0558   0.9401   0.1554
  -2.000   0.0981   0.01284   0.00593  -0.0581   0.9136   0.1767
  -1.750   0.1368   0.01318   0.00624  -0.0599   0.8815   0.1946
  -1.500   0.1702   0.01302   0.00581  -0.0604   0.8468   0.2002
  -1.250   0.1977   0.01279   0.00530  -0.0596   0.8121   0.2026
  -1.000   0.2231   0.01260   0.00498  -0.0587   0.7796   0.2059
  -0.750   0.2485   0.01246   0.00468  -0.0577   0.7494   0.2094
  -0.500   0.2742   0.01233   0.00438  -0.0569   0.7209   0.2132
  -0.250   0.2998   0.01215   0.00406  -0.0560   0.6931   0.2174
   0.000   0.3251   0.01204   0.00384  -0.0552   0.6659   0.2226
   0.250   0.3508   0.01204   0.00366  -0.0544   0.6399   0.2294
   0.500   0.3761   0.01193   0.00351  -0.0537   0.6149   0.2369
   0.750   0.4017   0.01188   0.00338  -0.0530   0.5893   0.2462
   1.000   0.4274   0.01184   0.00329  -0.0524   0.5619   0.2578
   1.250   0.4529   0.01177   0.00320  -0.0518   0.5332   0.2719
   1.500   0.4781   0.01170   0.00313  -0.0511   0.5042   0.2894
   1.750   0.5032   0.01167   0.00309  -0.0505   0.4770   0.3147
   2.000   0.5255   0.01107   0.00311  -0.0497   0.4540   0.5413
   2.250   0.5624   0.01047   0.00316  -0.0509   0.4301   1.0000
   2.500   0.5879   0.01077   0.00328  -0.0503   0.4103   1.0000
   2.750   0.6133   0.01109   0.00345  -0.0498   0.3920   1.0000
   3.000   0.6389   0.01139   0.00362  -0.0492   0.3739   1.0000
   3.250   0.6645   0.01168   0.00382  -0.0487   0.3556   1.0000
   3.500   0.6899   0.01199   0.00403  -0.0482   0.3381   1.0000
   3.750   0.7153   0.01233   0.00428  -0.0477   0.3219   1.0000
   4.000   0.7407   0.01267   0.00454  -0.0472   0.3073   1.0000
   4.250   0.7662   0.01302   0.00484  -0.0467   0.2945   1.0000
   4.500   0.7918   0.01340   0.00519  -0.0462   0.2838   1.0000
   4.750   0.8172   0.01381   0.00556  -0.0458   0.2747   1.0000
   5.000   0.8424   0.01405   0.00577  -0.0453   0.2616   1.0000
   5.250   0.8676   0.01425   0.00595  -0.0449   0.2476   1.0000
   5.500   0.8930   0.01452   0.00624  -0.0444   0.2379   1.0000
   5.750   0.9185   0.01478   0.00656  -0.0440   0.2283   1.0000
   6.000   0.9437   0.01495   0.00677  -0.0436   0.2132   1.0000
   6.250   0.9688   0.01516   0.00697  -0.0432   0.1967   1.0000
   6.500   0.9938   0.01545   0.00725  -0.0427   0.1803   1.0000
   6.750   1.0186   0.01583   0.00757  -0.0422   0.1544   1.0000
   7.000   1.0396   0.01683   0.00819  -0.0414   0.0783   1.0000
   7.250   1.0560   0.01867   0.00971  -0.0400   0.0288   1.0000
   7.500   1.0787   0.01950   0.01071  -0.0390   0.0261   1.0000
   7.750   1.1007   0.02039   0.01184  -0.0380   0.0250   1.0000
   8.000   1.1209   0.02147   0.01315  -0.0369   0.0233   1.0000
   8.250   1.1389   0.02275   0.01466  -0.0357   0.0218   1.0000
   8.500   1.1551   0.02411   0.01622  -0.0342   0.0213   1.0000
   8.750   1.1687   0.02562   0.01791  -0.0325   0.0211   1.0000
   9.000   1.1804   0.02724   0.01964  -0.0306   0.0209   1.0000
   9.250   1.1917   0.02889   0.02139  -0.0286   0.0211   1.0000
   9.500   1.2033   0.03056   0.02317  -0.0266   0.0214   1.0000
   9.750   1.2159   0.03234   0.02505  -0.0247   0.0220   1.0000
  10.000   1.2308   0.03436   0.02716  -0.0229   0.0229   1.0000
  10.250   1.2474   0.03673   0.02967  -0.0214   0.0241   1.0000
  10.500   1.2628   0.03921   0.03231  -0.0200   0.0244   1.0000
  10.750   1.2756   0.04183   0.03512  -0.0186   0.0245   1.0000
  11.000   1.3056   0.04750   0.04089  -0.0190   0.0270   1.0000
  11.250   1.3100   0.04746   0.04146  -0.0154   0.0307   1.0000
  11.500   1.3219   0.05194   0.04658  -0.0130   0.0403   1.0000
  15.750   0.7791   0.18499   0.18213  -0.0801   0.0716   1.0000
  16.000   0.7815   0.18895   0.18610  -0.0818   0.0709   1.0000
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