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GOE 14 AIRFOIL (goe14-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 14 AIRFOIL (goe14-il)
Reynolds number: 100,000
Max Cl/Cd: 46.44 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe14-il-100000.txt
Download as CSV file: xf-goe14-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 14 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2012   0.11176   0.10730  -0.0233   1.0000   0.0522
  -8.250  -0.2168   0.11173   0.10738  -0.0197   1.0000   0.0525
  -8.000  -0.2316   0.11157   0.10732  -0.0164   1.0000   0.0527
  -7.750  -0.2329   0.11013   0.10593  -0.0165   0.9978   0.0533
  -7.500  -0.2089   0.10663   0.10242  -0.0228   0.9905   0.0545
  -7.250  -0.1862   0.10446   0.10024  -0.0317   0.9802   0.0554
  -7.000  -0.1572   0.10042   0.09619  -0.0398   0.9709   0.0558
  -6.750  -0.1311   0.09537   0.09114  -0.0425   0.9647   0.0566
  -6.500  -0.1007   0.09123   0.08698  -0.0484   0.9567   0.0577
  -6.250  -0.0708   0.08754   0.08328  -0.0549   0.9478   0.0589
  -6.000  -0.0335   0.08381   0.07950  -0.0636   0.9396   0.0605
  -5.750   0.0051   0.08201   0.07758  -0.0756   0.9260   0.0614
  -5.500   0.0370   0.07707   0.07264  -0.0797   0.9201   0.0620
  -5.250   0.0546   0.07364   0.06923  -0.0803   0.9077   0.0628
  -5.000   0.0840   0.07023   0.06577  -0.0841   0.8988   0.0644
  -4.750   0.1087   0.06769   0.06318  -0.0874   0.8853   0.0663
  -4.500   0.1472   0.06681   0.06208  -0.0952   0.8702   0.0680
  -4.250   0.1690   0.06350   0.05873  -0.0964   0.8586   0.0685
  -4.000   0.1852   0.06010   0.05533  -0.0957   0.8467   0.0693
  -3.750   0.2037   0.05769   0.05288  -0.0960   0.8319   0.0705
  -3.500   0.2272   0.05545   0.05054  -0.0971   0.8183   0.0722
  -3.250   0.2599   0.05361   0.04849  -0.0998   0.8068   0.0747
  -3.000   0.2927   0.05244   0.04706  -0.1025   0.7908   0.0758
  -2.750   0.3082   0.04931   0.04395  -0.1016   0.7761   0.0767
  -2.500   0.3302   0.04704   0.04160  -0.1017   0.7623   0.0785
  -2.250   0.3615   0.04549   0.03978  -0.1030   0.7504   0.0823
  -2.000   0.3913   0.04406   0.03813  -0.1042   0.7347   0.0842
  -1.750   0.4122   0.04170   0.03572  -0.1040   0.7201   0.0860
  -1.500   0.4393   0.04010   0.03395  -0.1044   0.7066   0.0892
  -1.250   0.4752   0.03946   0.03287  -0.1054   0.6949   0.0927
  -1.000   0.4963   0.03707   0.03049  -0.1054   0.6803   0.0947
  -0.750   0.5237   0.03586   0.02910  -0.1056   0.6666   0.0992
  -0.500   0.5539   0.03468   0.02763  -0.1059   0.6549   0.1031
  -0.250   0.5802   0.03323   0.02602  -0.1059   0.6426   0.1085
   0.000   0.6075   0.03208   0.02471  -0.1061   0.6296   0.1153
   0.250   0.6361   0.03109   0.02346  -0.1062   0.6186   0.1254
   0.500   0.6639   0.03008   0.02222  -0.1062   0.6071   0.1372
   0.750   0.6897   0.02900   0.02103  -0.1062   0.5952   0.1522
   1.000   0.7168   0.02787   0.01967  -0.1064   0.5857   0.1819
   1.250   0.7410   0.02678   0.01854  -0.1064   0.5740   0.2178
   1.500   0.7682   0.02616   0.01772  -0.1063   0.5641   0.2495
   1.750   0.7945   0.02510   0.01657  -0.1061   0.5542   0.2769
   2.000   0.8219   0.02458   0.01593  -0.1059   0.5443   0.2945
   2.250   0.8518   0.02426   0.01536  -0.1056   0.5351   0.2958
   2.500   0.8808   0.02448   0.01538  -0.1050   0.5253   0.2826
   2.750   0.9121   0.02458   0.01517  -0.1044   0.5169   0.2453
   3.000   0.9407   0.02495   0.01533  -0.1035   0.5080   0.2102
   3.250   0.9696   0.02484   0.01504  -0.1028   0.4998   0.1833
   3.500   0.9968   0.02504   0.01509  -0.1021   0.4916   0.1745
   3.750   1.0229   0.02495   0.01495  -0.1014   0.4831   0.1695
   4.000   1.0498   0.02495   0.01481  -0.1007   0.4761   0.1725
   4.250   1.0737   0.02518   0.01506  -0.0998   0.4674   0.1772
   4.500   1.1013   0.02514   0.01489  -0.0995   0.4611   0.1843
   4.750   1.1246   0.02563   0.01543  -0.0988   0.4535   0.1900
   5.000   1.1502   0.02598   0.01571  -0.0984   0.4465   0.1953
   5.250   1.1782   0.02635   0.01591  -0.0982   0.4408   0.2041
   5.500   1.1993   0.02700   0.01672  -0.0974   0.4328   0.2121
   5.750   1.2259   0.02736   0.01706  -0.0971   0.4268   0.2302
   6.000   1.2492   0.02690   0.01772  -0.0963   0.4214   1.0000
   6.250   1.2696   0.02780   0.01871  -0.0954   0.4148   1.0000
   6.500   1.2950   0.02840   0.01922  -0.0950   0.4095   1.0000
   6.750   1.3214   0.02910   0.01977  -0.0947   0.4048   1.0000
   7.000   1.3383   0.03013   0.02100  -0.0935   0.3978   1.0000
   7.250   1.3630   0.03065   0.02144  -0.0930   0.3922   1.0000
   7.500   1.3898   0.03120   0.02183  -0.0928   0.3872   1.0000
   7.750   1.4043   0.03222   0.02305  -0.0913   0.3797   1.0000
   8.000   1.4306   0.03241   0.02313  -0.0909   0.3736   1.0000
   8.250   1.4523   0.03314   0.02385  -0.0902   0.3679   1.0000
   8.500   1.4677   0.03420   0.02507  -0.0888   0.3617   1.0000
   8.750   1.4925   0.03465   0.02544  -0.0884   0.3567   1.0000
   9.000   1.5179   0.03530   0.02603  -0.0881   0.3522   1.0000
   9.250   1.5259   0.03681   0.02783  -0.0861   0.3462   1.0000
   9.500   1.5466   0.03751   0.02856  -0.0853   0.3412   1.0000
   9.750   1.5778   0.03774   0.02864  -0.0856   0.3370   1.0000
  10.000   1.5800   0.03967   0.03090  -0.0831   0.3315   1.0000
  10.250   1.5926   0.04083   0.03219  -0.0816   0.3261   1.0000
  10.500   1.6232   0.04085   0.03209  -0.0817   0.3214   1.0000
  10.750   1.6297   0.04248   0.03391  -0.0796   0.3161   1.0000
  11.000   1.6324   0.04406   0.03572  -0.0771   0.3101   1.0000
  11.250   1.6660   0.04374   0.03527  -0.0775   0.3049   1.0000
  11.500   1.6681   0.04553   0.03724  -0.0750   0.2996   1.0000
  11.750   1.6580   0.04778   0.03973  -0.0715   0.2941   1.0000
  12.000   1.6939   0.04736   0.03923  -0.0720   0.2887   1.0000
  12.250   1.6920   0.04931   0.04132  -0.0692   0.2839   1.0000
  12.500   1.6447   0.05374   0.04608  -0.0633   0.2796   1.0000
  12.750   1.6640   0.05418   0.04654  -0.0624   0.2742   1.0000
  13.000   1.7005   0.05385   0.04611  -0.0627   0.2688   1.0000
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