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GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il)
Reynolds number: 500,000
Max Cl/Cd: 106.93 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe167-il-500000.txt
Download as CSV file: xf-goe167-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 167 (V.KARMAN PROP.2) AIRFOIL               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3673   0.09650   0.09442  -0.0178   1.0000   0.0219
  -8.250  -0.3673   0.09260   0.09056  -0.0228   1.0000   0.0221
  -8.000  -0.3652   0.08862   0.08662  -0.0271   1.0000   0.0222
  -7.750  -0.3557   0.08383   0.08184  -0.0336   1.0000   0.0223
  -7.500  -0.3439   0.07733   0.07533  -0.0391   0.9805   0.0226
  -7.250  -0.3280   0.07419   0.07216  -0.0403   0.9554   0.0230
  -7.000  -0.3172   0.07128   0.06918  -0.0413   0.9171   0.0233
  -6.750  -0.3076   0.06833   0.06605  -0.0425   0.8641   0.0238
  -6.500  -0.2937   0.06499   0.06248  -0.0451   0.8201   0.0244
  -6.250  -0.2754   0.06118   0.05846  -0.0490   0.7864   0.0254
  -6.000  -0.2365   0.05497   0.05183  -0.0586   0.7599   0.0279
  -5.750  -0.2120   0.05052   0.04704  -0.0617   0.7329   0.0281
  -5.500  -0.1994   0.04460   0.04095  -0.0639   0.7083   0.0289
  -5.250  -0.1785   0.04247   0.03864  -0.0647   0.6825   0.0294
  -5.000  -0.1553   0.04031   0.03629  -0.0658   0.6606   0.0302
  -4.750  -0.1297   0.03787   0.03362  -0.0672   0.6435   0.0315
  -4.500  -0.0929   0.03629   0.03156  -0.0680   0.6299   0.0354
  -4.250  -0.0684   0.03020   0.02503  -0.0701   0.6204   0.0366
  -4.000  -0.0432   0.02845   0.02317  -0.0709   0.6102   0.0374
  -3.750  -0.0165   0.02702   0.02162  -0.0715   0.6013   0.0385
  -3.500   0.0112   0.02565   0.02005  -0.0721   0.5937   0.0403
  -3.250   0.0434   0.02615   0.02024  -0.0717   0.5863   0.0452
  -3.000   0.0711   0.02200   0.01570  -0.0731   0.5807   0.0475
  -2.750   0.0990   0.02091   0.01455  -0.0736   0.5751   0.0491
  -2.500   0.1277   0.02002   0.01354  -0.0740   0.5698   0.0517
  -2.250   0.1579   0.02104   0.01430  -0.0737   0.5649   0.0572
  -2.000   0.1864   0.01804   0.01112  -0.0747   0.5609   0.0610
  -1.750   0.2151   0.01745   0.01048  -0.0751   0.5564   0.0651
  -1.500   0.2444   0.01676   0.00959  -0.0755   0.5523   0.0741
  -1.250   0.2772   0.01446   0.00682  -0.0746   0.5486   0.0444
  -1.000   0.3065   0.01349   0.00577  -0.0748   0.5443   0.0434
  -0.750   0.3355   0.01288   0.00510  -0.0749   0.5397   0.0429
  -0.500   0.3642   0.01251   0.00465  -0.0750   0.5355   0.0433
  -0.250   0.3931   0.01221   0.00431  -0.0752   0.5321   0.0439
   0.000   0.4222   0.01184   0.00394  -0.0755   0.5288   0.0440
   0.250   0.4512   0.01158   0.00366  -0.0757   0.5253   0.0444
   0.500   0.4802   0.01142   0.00346  -0.0759   0.5216   0.0451
   0.750   0.5091   0.01129   0.00328  -0.0762   0.5180   0.0461
   1.000   0.5384   0.01109   0.00309  -0.0765   0.5146   0.0485
   1.250   0.5676   0.01101   0.00301  -0.0768   0.5112   0.0519
   1.500   0.5966   0.01098   0.00297  -0.0770   0.5082   0.0572
   1.750   0.6189   0.00903   0.00317  -0.0766   0.5048   0.8599
   2.000   0.6478   0.00879   0.00304  -0.0766   0.5002   1.0000
   2.250   0.6767   0.00884   0.00305  -0.0768   0.4953   1.0000
   2.500   0.7055   0.00894   0.00309  -0.0770   0.4917   1.0000
   2.750   0.7340   0.00911   0.00319  -0.0772   0.4881   1.0000
   3.000   0.7629   0.00914   0.00325  -0.0775   0.4843   1.0000
   3.250   0.7917   0.00920   0.00330  -0.0777   0.4793   1.0000
   3.500   0.8200   0.00931   0.00335  -0.0779   0.4736   1.0000
   3.750   0.8487   0.00934   0.00342  -0.0782   0.4679   1.0000
   4.000   0.8772   0.00940   0.00347  -0.0784   0.4619   1.0000
   4.250   0.9056   0.00951   0.00357  -0.0786   0.4568   1.0000
   4.500   0.9342   0.00955   0.00366  -0.0788   0.4504   1.0000
   4.750   0.9623   0.00967   0.00374  -0.0790   0.4442   1.0000
   5.000   0.9908   0.00973   0.00386  -0.0792   0.4375   1.0000
   5.250   1.0188   0.00984   0.00396  -0.0794   0.4287   1.0000
   5.500   1.0468   0.00991   0.00404  -0.0795   0.4126   1.0000
   5.750   1.0746   0.01005   0.00416  -0.0797   0.3926   1.0000
   6.000   1.1015   0.01031   0.00433  -0.0797   0.3632   1.0000
   6.500   1.1461   0.01229   0.00553  -0.0791   0.2249   1.0000
   6.750   1.1704   0.01294   0.00605  -0.0789   0.1979   1.0000
   7.000   1.1920   0.01391   0.00670  -0.0785   0.1352   1.0000
   7.250   1.2098   0.01530   0.00774  -0.0776   0.0749   1.0000
   7.500   1.2338   0.01582   0.00827  -0.0772   0.0673   1.0000
   7.750   1.2566   0.01643   0.00887  -0.0768   0.0596   1.0000
   8.000   1.2810   0.01682   0.00932  -0.0765   0.0542   1.0000
   8.250   1.3038   0.01737   0.00986  -0.0760   0.0451   1.0000
   8.500   1.3240   0.01816   0.01048  -0.0752   0.0247   1.0000
   8.750   1.3427   0.01904   0.01134  -0.0741   0.0198   1.0000
   9.000   1.3612   0.01989   0.01226  -0.0730   0.0178   1.0000
   9.250   1.3794   0.02069   0.01316  -0.0718   0.0170   1.0000
   9.500   1.3951   0.02162   0.01419  -0.0703   0.0163   1.0000
   9.750   1.4080   0.02267   0.01534  -0.0684   0.0156   1.0000
  10.000   1.4163   0.02389   0.01665  -0.0660   0.0150   1.0000
  10.250   1.4168   0.02534   0.01820  -0.0624   0.0146   1.0000
  10.500   1.4120   0.02734   0.02032  -0.0589   0.0141   1.0000
  10.750   1.4060   0.02986   0.02297  -0.0563   0.0138   1.0000
  11.000   1.4120   0.03167   0.02488  -0.0551   0.0135   1.0000
  11.250   1.4151   0.03393   0.02726  -0.0542   0.0132   1.0000
  11.500   1.4167   0.03652   0.02995  -0.0536   0.0130   1.0000
  11.750   1.4174   0.03930   0.03283  -0.0531   0.0127   1.0000
  12.000   1.4178   0.04217   0.03581  -0.0527   0.0125   1.0000
  12.250   1.4178   0.04509   0.03882  -0.0522   0.0123   1.0000
  12.500   1.4177   0.04802   0.04183  -0.0518   0.0121   1.0000
  12.750   1.4177   0.05092   0.04483  -0.0514   0.0119   1.0000
  13.000   1.4176   0.05379   0.04780  -0.0509   0.0117   1.0000
  13.250   1.4177   0.05663   0.05071  -0.0503   0.0115   1.0000
  13.500   1.4179   0.05942   0.05357  -0.0497   0.0114   1.0000
  13.750   1.4182   0.06214   0.05637  -0.0490   0.0112   1.0000
  14.000   1.4193   0.06475   0.05904  -0.0482   0.0110   1.0000
  14.250   1.4216   0.06721   0.06155  -0.0471   0.0109   1.0000
  14.500   1.4254   0.06930   0.06371  -0.0452   0.0107   1.0000
  14.750   1.4303   0.07148   0.06601  -0.0421   0.0104   1.0000
  15.000   1.4254   0.07536   0.07006  -0.0432   0.0103   1.0000
  15.250   1.4210   0.07928   0.07416  -0.0443   0.0102   1.0000
  15.500   1.4170   0.08322   0.07826  -0.0451   0.0101   1.0000
  15.750   1.4122   0.08737   0.08258  -0.0460   0.0100   1.0000
  16.000   1.4066   0.09169   0.08706  -0.0469   0.0099   1.0000
  16.250   1.3996   0.09628   0.09182  -0.0479   0.0099   1.0000
  16.500   1.3912   0.10122   0.09694  -0.0493   0.0098   1.0000
  16.750   1.3815   0.10650   0.10239  -0.0510   0.0098   1.0000
  17.000   1.3708   0.11214   0.10821  -0.0531   0.0098   1.0000
  17.250   1.3590   0.11810   0.11434  -0.0556   0.0099   1.0000
  17.500   1.3462   0.12447   0.12089  -0.0585   0.0099   1.0000
  17.750   1.3325   0.13124   0.12783  -0.0619   0.0099   1.0000
  18.000   1.3184   0.13841   0.13517  -0.0658   0.0099   1.0000
  18.250   1.3035   0.14602   0.14295  -0.0702   0.0100   1.0000
  18.500   1.2882   0.15404   0.15113  -0.0750   0.0101   1.0000
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