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GOE 612 AIRFOIL (goe612-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 612 AIRFOIL (goe612-il)
Reynolds number: 50,000
Max Cl/Cd: 27.93 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe612-il-50000-n5.txt
Download as CSV file: xf-goe612-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 612 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2936   0.12736   0.12031  -0.0385   1.0000   0.1048
 -10.000  -0.3269   0.12033   0.11339  -0.0392   0.9993   0.0902
  -9.750  -0.3073   0.11636   0.10940  -0.0423   0.9939   0.0891
  -9.500  -0.2944   0.11218   0.10520  -0.0460   0.9877   0.0883
  -9.250  -0.2840   0.10773   0.10074  -0.0506   0.9818   0.0882
  -9.000  -0.2772   0.10342   0.09642  -0.0546   0.9743   0.0883
  -8.750  -0.2694   0.09889   0.09188  -0.0591   0.9677   0.0883
  -8.500  -0.2652   0.09454   0.08754  -0.0629   0.9594   0.0881
  -8.250  -0.2627   0.09015   0.08314  -0.0667   0.9511   0.0876
  -8.000  -0.2631   0.08529   0.07828  -0.0712   0.9426   0.0871
  -7.750  -0.2736   0.08075   0.07376  -0.0742   0.9309   0.0865
  -7.500  -0.2838   0.07426   0.06721  -0.0797   0.9199   0.0859
  -7.250  -0.2965   0.06574   0.05846  -0.0869   0.9100   0.0857
  -7.000  -0.3114   0.06055   0.05301  -0.0883   0.8982   0.0861
  -6.750  -0.3081   0.05504   0.04704  -0.0916   0.8912   0.0875
  -6.500  -0.3108   0.05137   0.04293  -0.0910   0.8813   0.0888
  -6.250  -0.2948   0.04717   0.03800  -0.0929   0.8762   0.0905
  -6.000  -0.2860   0.04583   0.03656  -0.0910   0.8679   0.0916
  -5.750  -0.2644   0.04421   0.03477  -0.0911   0.8623   0.0933
  -5.500  -0.2361   0.04246   0.03275  -0.0923   0.8585   0.0959
  -5.250  -0.2278   0.04139   0.03143  -0.0899   0.8501   0.0986
  -5.000  -0.2045   0.03977   0.02931  -0.0899   0.8450   0.1026
  -4.500  -0.1627   0.03818   0.02760  -0.0886   0.8338   0.1097
  -4.250  -0.1385   0.03721   0.02627  -0.0883   0.8286   0.1155
  -4.000  -0.1086   0.03646   0.02558  -0.0889   0.8250   0.1221
  -3.750  -0.0922   0.03599   0.02492  -0.0873   0.8185   0.1291
  -3.500  -0.0717   0.03555   0.02451  -0.0864   0.8126   0.1371
  -3.250  -0.0418   0.03493   0.02382  -0.0868   0.8087   0.1501
  -3.000  -0.0144   0.03452   0.02340  -0.0869   0.8044   0.1656
  -2.750  -0.0012   0.03451   0.02337  -0.0850   0.7968   0.1801
  -2.500   0.0274   0.03424   0.02317  -0.0852   0.7925   0.2021
  -2.250   0.0620   0.03394   0.02288  -0.0863   0.7893   0.2319
  -2.000   0.0698   0.03435   0.02335  -0.0836   0.7808   0.2522
  -1.750   0.0970   0.03434   0.02338  -0.0835   0.7758   0.2860
  -1.250   0.1412   0.03463   0.02375  -0.0819   0.7640   0.3447
  -1.000   0.1690   0.03463   0.02373  -0.0818   0.7586   0.3775
  -0.750   0.2048   0.03438   0.02351  -0.0828   0.7550   0.4119
  -0.500   0.2155   0.03487   0.02401  -0.0804   0.7451   0.4358
  -0.250   0.2515   0.03443   0.02360  -0.0810   0.7393   0.4729
   0.000   0.2725   0.03438   0.02362  -0.0797   0.7295   0.5070
   0.250   0.3062   0.03372   0.02315  -0.0798   0.7223   0.5548
   0.750   0.3642   0.03250   0.02286  -0.0785   0.7063   0.7420
   1.000   0.4410   0.03167   0.02195  -0.0864   0.7023   1.0000
   1.250   0.4500   0.03239   0.02250  -0.0838   0.6908   1.0000
   1.500   0.4875   0.03212   0.02199  -0.0847   0.6852   1.0000
   1.750   0.5004   0.03270   0.02243  -0.0825   0.6743   1.0000
   2.000   0.5345   0.03248   0.02205  -0.0828   0.6676   1.0000
   2.250   0.5497   0.03298   0.02243  -0.0809   0.6570   1.0000
   2.500   0.5823   0.03275   0.02208  -0.0809   0.6496   1.0000
   2.750   0.5966   0.03325   0.02249  -0.0789   0.6382   1.0000
   3.000   0.6315   0.03289   0.02202  -0.0791   0.6311   1.0000
   3.250   0.6427   0.03350   0.02256  -0.0766   0.6184   1.0000
   3.500   0.6826   0.03286   0.02182  -0.0774   0.6121   1.0000
   3.750   0.6910   0.03356   0.02248  -0.0746   0.5982   1.0000
   4.250   0.7422   0.03342   0.02223  -0.0728   0.5780   1.0000
   4.500   0.7539   0.03400   0.02277  -0.0705   0.5640   1.0000
   4.750   0.7745   0.03417   0.02290  -0.0691   0.5522   1.0000
   5.000   0.8058   0.03379   0.02245  -0.0687   0.5428   1.0000
   5.250   0.8178   0.03443   0.02307  -0.0665   0.5285   1.0000
   5.500   0.8351   0.03483   0.02343  -0.0649   0.5157   1.0000
   5.750   0.8718   0.03415   0.02267  -0.0650   0.5074   1.0000
   6.000   0.8833   0.03493   0.02343  -0.0630   0.4934   1.0000
   6.250   0.8998   0.03548   0.02394  -0.0614   0.4809   1.0000
   6.500   0.9296   0.03525   0.02363  -0.0610   0.4712   1.0000
   6.750   0.9483   0.03573   0.02407  -0.0597   0.4596   1.0000
   7.000   0.9651   0.03638   0.02468  -0.0583   0.4483   1.0000
   7.250   0.9984   0.03603   0.02421  -0.0581   0.4394   1.0000
   7.500   1.0081   0.03715   0.02536  -0.0563   0.4279   1.0000
   7.750   1.0294   0.03760   0.02575  -0.0553   0.4182   1.0000
   8.000   1.0515   0.03801   0.02610  -0.0544   0.4085   1.0000
   8.250   1.0645   0.03905   0.02715  -0.0529   0.3987   1.0000
   8.500   1.0928   0.03913   0.02713  -0.0525   0.3899   1.0000
   8.750   1.0985   0.04062   0.02868  -0.0505   0.3802   1.0000
   9.000   1.1306   0.04054   0.02849  -0.0504   0.3720   1.0000
   9.250   1.1303   0.04243   0.03050  -0.0482   0.3628   1.0000
   9.500   1.1624   0.04238   0.03032  -0.0481   0.3547   1.0000
   9.750   1.1592   0.04452   0.03262  -0.0458   0.3462   1.0000
  10.000   1.1860   0.04479   0.03284  -0.0453   0.3384   1.0000
  10.250   1.1863   0.04683   0.03500  -0.0434   0.3306   1.0000
  10.500   1.2015   0.04785   0.03604  -0.0423   0.3230   1.0000
  10.750   1.2151   0.04908   0.03730  -0.0413   0.3160   1.0000
  11.000   1.2124   0.05143   0.03981  -0.0395   0.3085   1.0000
  11.250   1.2482   0.05110   0.03938  -0.0395   0.3021   1.0000
  11.500   1.2245   0.05513   0.04368  -0.0371   0.2952   1.0000
  11.750   1.2317   0.05690   0.04552  -0.0360   0.2886   1.0000
  12.000   1.2563   0.05735   0.04594  -0.0355   0.2831   1.0000
  12.250   1.2147   0.06359   0.05250  -0.0337   0.2762   1.0000
  12.500   1.2243   0.06532   0.05431  -0.0330   0.2707   1.0000
  12.750   1.2428   0.06622   0.05521  -0.0323   0.2658   1.0000
  13.000   1.1393   0.08123   0.07061  -0.0335   0.2564   1.0000
  13.250   1.1704   0.08020   0.06960  -0.0323   0.2527   1.0000
  13.500   1.0454   0.10259   0.09221  -0.0390   0.2381   1.0000
  13.750   1.0702   0.10196   0.09162  -0.0378   0.2356   1.0000
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