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GOE 400 AIRFOIL (goe400-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 400 AIRFOIL (goe400-il)
Reynolds number: 200,000
Max Cl/Cd: 79.89 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe400-il-200000-n5.txt
Download as CSV file: xf-goe400-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 400 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3827   0.09677   0.09337  -0.0047   1.0000   0.0240
  -7.750  -0.3767   0.09333   0.08996  -0.0066   1.0000   0.0237
  -7.500  -0.3707   0.09000   0.08666  -0.0086   1.0000   0.0238
  -7.250  -0.3620   0.08656   0.08326  -0.0119   1.0000   0.0251
  -7.000  -0.3501   0.08232   0.07903  -0.0175   1.0000   0.0261
  -6.750  -0.3368   0.07811   0.07484  -0.0222   1.0000   0.0262
  -6.500  -0.3210   0.07354   0.07026  -0.0277   1.0000   0.0265
  -6.250  -0.3046   0.06865   0.06539  -0.0334   1.0000   0.0277
  -6.000  -0.2913   0.06827   0.06504  -0.0310   0.9980   0.0295
  -5.750  -0.2591   0.06470   0.06141  -0.0373   0.9769   0.0320
  -5.500  -0.2237   0.05947   0.05608  -0.0458   0.9546   0.0321
  -5.250  -0.1874   0.05445   0.05091  -0.0537   0.9318   0.0330
  -5.000  -0.1484   0.04885   0.04510  -0.0620   0.9066   0.0350
  -4.750  -0.1151   0.04400   0.04001  -0.0674   0.8816   0.0353
  -4.500  -0.0796   0.03886   0.03454  -0.0726   0.8582   0.0364
  -4.250  -0.0504   0.03416   0.02953  -0.0761   0.8356   0.0376
  -4.000  -0.0200   0.02951   0.02446  -0.0789   0.8161   0.0378
  -3.750   0.0101   0.02461   0.01902  -0.0811   0.7987   0.0383
  -3.500   0.0390   0.02067   0.01448  -0.0824   0.7827   0.0392
  -3.250   0.0661   0.01919   0.01264  -0.0826   0.7673   0.0406
  -3.000   0.0939   0.01721   0.01015  -0.0827   0.7536   0.0415
  -2.750   0.1215   0.01583   0.00834  -0.0827   0.7405   0.0420
  -2.500   0.1490   0.01490   0.00711  -0.0825   0.7283   0.0428
  -2.250   0.1765   0.01421   0.00618  -0.0822   0.7169   0.0436
  -2.000   0.2039   0.01367   0.00544  -0.0819   0.7061   0.0447
  -1.750   0.2313   0.01324   0.00483  -0.0816   0.6954   0.0459
  -1.500   0.2589   0.01289   0.00434  -0.0813   0.6850   0.0470
  -1.250   0.2863   0.01262   0.00394  -0.0810   0.6753   0.0482
  -1.000   0.3137   0.01233   0.00361  -0.0807   0.6654   0.0515
  -0.750   0.3412   0.01214   0.00340  -0.0805   0.6558   0.0562
  -0.500   0.3686   0.01199   0.00322  -0.0802   0.6469   0.0619
  -0.250   0.3963   0.01200   0.00332  -0.0799   0.6373   0.0745
   0.000   0.4240   0.01211   0.00332  -0.0796   0.6284   0.0924
   0.250   0.4515   0.01218   0.00333  -0.0794   0.6193   0.1014
   0.500   0.4791   0.01221   0.00329  -0.0791   0.6101   0.1086
   0.750   0.5064   0.01222   0.00329  -0.0789   0.6015   0.1160
   1.000   0.5337   0.01221   0.00329  -0.0787   0.5920   0.1254
   1.250   0.5610   0.01223   0.00330  -0.0785   0.5829   0.1338
   1.500   0.5882   0.01218   0.00324  -0.0782   0.5738   0.1378
   1.750   0.6155   0.01212   0.00323  -0.0780   0.5641   0.1406
   2.000   0.6427   0.01211   0.00321  -0.0777   0.5549   0.1430
   2.250   0.6699   0.01212   0.00322  -0.0775   0.5444   0.1451
   2.500   0.6970   0.01214   0.00325  -0.0772   0.5324   0.1474
   2.750   0.7239   0.01218   0.00327  -0.0769   0.5186   0.1501
   3.000   0.7507   0.01223   0.00332  -0.0766   0.5039   0.1538
   3.250   0.7775   0.01229   0.00339  -0.0763   0.4890   0.1595
   3.500   0.8042   0.01238   0.00350  -0.0760   0.4736   0.1687
   3.750   0.8307   0.01245   0.00363  -0.0756   0.4585   0.1954
   4.250   0.8839   0.01143   0.00397  -0.0751   0.4319   1.0000
   4.500   0.9103   0.01166   0.00415  -0.0748   0.4186   1.0000
   4.750   0.9366   0.01190   0.00435  -0.0744   0.4052   1.0000
   5.000   0.9627   0.01215   0.00460  -0.0740   0.3902   1.0000
   5.250   0.9886   0.01243   0.00485  -0.0737   0.3750   1.0000
   5.500   1.0145   0.01272   0.00512  -0.0733   0.3600   1.0000
   5.750   1.0402   0.01302   0.00543  -0.0729   0.3455   1.0000
   6.000   1.0656   0.01336   0.00577  -0.0725   0.3275   1.0000
   6.250   1.0909   0.01371   0.00613  -0.0721   0.3113   1.0000
   6.500   1.1155   0.01412   0.00652  -0.0717   0.2908   1.0000
   6.750   1.1390   0.01468   0.00699  -0.0711   0.2571   1.0000
   7.000   1.1612   0.01541   0.00753  -0.0705   0.2146   1.0000
   7.250   1.1821   0.01634   0.00822  -0.0698   0.1681   1.0000
   7.500   1.2020   0.01741   0.00903  -0.0691   0.1225   1.0000
   7.750   1.2221   0.01842   0.00987  -0.0683   0.0962   1.0000
   8.000   1.2422   0.01939   0.01080  -0.0675   0.0801   1.0000
   8.250   1.2634   0.02018   0.01159  -0.0668   0.0551   1.0000
   8.500   1.2790   0.02166   0.01282  -0.0656   0.0294   1.0000
   8.750   1.2970   0.02278   0.01401  -0.0644   0.0241   1.0000
   9.000   1.3134   0.02401   0.01532  -0.0632   0.0207   1.0000
   9.250   1.3295   0.02520   0.01664  -0.0619   0.0188   1.0000
   9.500   1.3450   0.02637   0.01800  -0.0605   0.0176   1.0000
   9.750   1.3584   0.02767   0.01944  -0.0590   0.0166   1.0000
  10.000   1.3697   0.02907   0.02097  -0.0573   0.0156   1.0000
  10.250   1.3773   0.03064   0.02266  -0.0554   0.0148   1.0000
  10.500   1.3776   0.03263   0.02475  -0.0529   0.0140   1.0000
  10.750   1.3780   0.03474   0.02698  -0.0509   0.0134   1.0000
  11.000   1.3824   0.03665   0.02903  -0.0495   0.0130   1.0000
  11.250   1.3850   0.03888   0.03141  -0.0483   0.0127   1.0000
  11.500   1.3870   0.04132   0.03399  -0.0474   0.0124   1.0000
  11.750   1.3886   0.04392   0.03674  -0.0467   0.0121   1.0000
  12.000   1.3897   0.04667   0.03966  -0.0462   0.0118   1.0000
  12.250   1.3903   0.04954   0.04267  -0.0458   0.0115   1.0000
  12.500   1.3903   0.05254   0.04581  -0.0454   0.0113   1.0000
  12.750   1.3899   0.05565   0.04906  -0.0453   0.0110   1.0000
  13.000   1.3886   0.05890   0.05244  -0.0453   0.0107   1.0000
  13.250   1.3865   0.06231   0.05598  -0.0455   0.0105   1.0000
  13.500   1.3833   0.06591   0.05970  -0.0460   0.0103   1.0000
  13.750   1.3790   0.06971   0.06362  -0.0465   0.0100   1.0000
  14.000   1.3733   0.07376   0.06777  -0.0471   0.0098   1.0000
  14.250   1.3658   0.07811   0.07225  -0.0476   0.0096   1.0000
  14.500   1.3572   0.08287   0.07718  -0.0488   0.0095   1.0000
  14.750   1.3485   0.08788   0.08239  -0.0506   0.0093   1.0000
  15.000   1.3391   0.09321   0.08792  -0.0526   0.0093   1.0000
  15.250   1.3286   0.09893   0.09384  -0.0549   0.0092   1.0000
  15.500   1.3172   0.10506   0.10016  -0.0577   0.0092   1.0000
  15.750   1.3051   0.11152   0.10681  -0.0608   0.0091   1.0000
  16.000   1.2924   0.11840   0.11388  -0.0643   0.0091   1.0000
  16.250   1.2791   0.12568   0.12133  -0.0683   0.0091   1.0000
  16.500   1.2653   0.13336   0.12918  -0.0726   0.0091   1.0000
  16.750   1.2510   0.14154   0.13753  -0.0775   0.0091   1.0000
  17.000   1.2365   0.15015   0.14630  -0.0827   0.0091   1.0000
  17.250   1.2218   0.15933   0.15563  -0.0885   0.0092   1.0000
  17.500   1.2063   0.16932   0.16576  -0.0948   0.0093   1.0000
  17.750   1.1903   0.18015   0.17671  -0.1016   0.0094   1.0000
  18.000   1.1729   0.19249   0.18913  -0.1091   0.0095   1.0000
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