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GOE 409 AIRFOIL (goe409-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 409 AIRFOIL (goe409-il)
Reynolds number: 100,000
Max Cl/Cd: 32.5 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe409-il-100000-n5.txt
Download as CSV file: xf-goe409-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 409 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.8031   0.09173   0.08590  -0.0403   1.0000   0.0471
 -14.250  -0.8401   0.08229   0.07629  -0.0463   1.0000   0.0469
 -14.000  -0.8700   0.07510   0.06891  -0.0502   1.0000   0.0467
 -13.750  -0.9020   0.06889   0.06246  -0.0530   1.0000   0.0469
 -13.500  -0.9294   0.06404   0.05737  -0.0539   1.0000   0.0471
 -13.250  -0.9558   0.06015   0.05318  -0.0534   1.0000   0.0474
 -13.000  -0.9542   0.05739   0.05042  -0.0528   1.0000   0.0486
 -12.750  -0.9544   0.05540   0.04840  -0.0518   1.0000   0.0499
 -12.500  -0.9593   0.05330   0.04618  -0.0502   1.0000   0.0511
 -12.250  -0.9643   0.05133   0.04407  -0.0481   1.0000   0.0524
 -12.000  -0.9722   0.04937   0.04191  -0.0453   1.0000   0.0537
 -11.750  -0.9812   0.04757   0.03987  -0.0417   1.0000   0.0550
 -11.500  -0.9900   0.04600   0.03803  -0.0376   1.0000   0.0563
 -11.250  -0.9958   0.04465   0.03634  -0.0337   1.0000   0.0577
 -11.000  -0.9937   0.04261   0.03408  -0.0309   1.0000   0.0593
 -10.750  -0.9799   0.04080   0.03231  -0.0298   1.0000   0.0615
 -10.500  -0.9708   0.03948   0.03086  -0.0276   1.0000   0.0634
 -10.250  -0.9617   0.03818   0.02940  -0.0252   1.0000   0.0653
 -10.000  -0.9517   0.03683   0.02784  -0.0229   1.0000   0.0669
  -9.750  -0.9397   0.03547   0.02627  -0.0207   1.0000   0.0680
  -9.500  -0.9258   0.03418   0.02477  -0.0187   1.0000   0.0689
  -9.250  -0.9118   0.03307   0.02345  -0.0166   1.0000   0.0699
  -9.000  -0.8977   0.03213   0.02228  -0.0145   1.0000   0.0709
  -8.750  -0.8783   0.03070   0.02078  -0.0134   1.0000   0.0720
  -8.500  -0.8587   0.02945   0.01951  -0.0122   1.0000   0.0729
  -8.250  -0.8408   0.02841   0.01844  -0.0107   1.0000   0.0738
  -8.000  -0.8241   0.02749   0.01749  -0.0090   1.0000   0.0747
  -7.750  -0.8084   0.02666   0.01662  -0.0070   1.0000   0.0756
  -7.500  -0.7937   0.02589   0.01582  -0.0049   1.0000   0.0766
  -7.250  -0.7797   0.02519   0.01508  -0.0026   1.0000   0.0778
  -7.000  -0.7662   0.02453   0.01438  -0.0003   1.0000   0.0793
  -6.750  -0.7529   0.02391   0.01371   0.0021   1.0000   0.0808
  -6.500  -0.7396   0.02334   0.01306   0.0046   1.0000   0.0821
  -6.250  -0.7262   0.02279   0.01245   0.0070   1.0000   0.0833
  -6.000  -0.7128   0.02228   0.01189   0.0094   1.0000   0.0843
  -5.750  -0.7005   0.02168   0.01128   0.0120   1.0000   0.0859
  -5.500  -0.6870   0.02116   0.01075   0.0143   1.0000   0.0878
  -5.250  -0.6726   0.02070   0.01025   0.0166   1.0000   0.0900
  -5.000  -0.6575   0.02028   0.00981   0.0187   1.0000   0.0929
  -4.750  -0.6419   0.01989   0.00940   0.0207   1.0000   0.0966
  -4.250  -0.5694   0.01872   0.00864   0.0160   0.9863   0.1554
  -4.000  -0.5373   0.01808   0.00827   0.0144   0.9801   0.2090
  -3.750  -0.5082   0.01732   0.00794   0.0135   0.9741   0.2846
  -3.500  -0.4807   0.01671   0.00775   0.0130   0.9678   0.3640
  -3.250  -0.4505   0.01631   0.00768   0.0122   0.9616   0.4465
  -3.000  -0.4206   0.01606   0.00758   0.0117   0.9550   0.5005
  -2.750  -0.3891   0.01583   0.00752   0.0109   0.9486   0.5439
  -2.500  -0.3566   0.01564   0.00751   0.0101   0.9427   0.5852
  -2.250  -0.3268   0.01549   0.00753   0.0099   0.9353   0.6262
  -2.000  -0.2882   0.01541   0.00757   0.0081   0.9307   0.6627
  -1.750  -0.2604   0.01536   0.00765   0.0085   0.9217   0.6992
  -1.500  -0.2211   0.01545   0.00796   0.0071   0.9169   0.7517
  -1.250  -0.1878   0.01567   0.00831   0.0070   0.9094   0.7923
  -1.000  -0.1484   0.01587   0.00855   0.0055   0.9029   0.8177
  -0.750  -0.1124   0.01598   0.00866   0.0044   0.8951   0.8349
  -0.500  -0.0732   0.01607   0.00876   0.0027   0.8874   0.8481
  -0.250  -0.0365   0.01612   0.00881   0.0013   0.8786   0.8590
   0.000   0.0000   0.01609   0.00876   0.0000   0.8700   0.8700
   0.250   0.0364   0.01612   0.00880  -0.0013   0.8590   0.8786
   0.500   0.0732   0.01607   0.00876  -0.0027   0.8481   0.8874
   0.750   0.1123   0.01597   0.00866  -0.0044   0.8349   0.8951
   1.250   0.1876   0.01568   0.00832  -0.0070   0.7926   0.9094
   1.500   0.2213   0.01545   0.00797  -0.0071   0.7524   0.9170
   1.750   0.2605   0.01535   0.00766  -0.0085   0.6994   0.9218
   2.000   0.2883   0.01541   0.00757  -0.0081   0.6628   0.9308
   2.250   0.3268   0.01549   0.00753  -0.0099   0.6262   0.9353
   2.500   0.3566   0.01564   0.00751  -0.0101   0.5851   0.9428
   2.750   0.3891   0.01583   0.00752  -0.0109   0.5430   0.9486
   3.000   0.4204   0.01607   0.00758  -0.0116   0.4991   0.9551
   3.250   0.4504   0.01631   0.00768  -0.0122   0.4442   0.9616
   3.500   0.4805   0.01672   0.00775  -0.0130   0.3622   0.9678
   3.750   0.5080   0.01733   0.00793  -0.0134   0.2832   0.9741
   4.000   0.5374   0.01807   0.00827  -0.0145   0.2097   0.9801
   4.250   0.5694   0.01872   0.00863  -0.0160   0.1554   0.9863
   4.750   0.6418   0.01989   0.00940  -0.0206   0.0965   1.0000
   5.000   0.6575   0.02027   0.00980  -0.0186   0.0929   1.0000
   5.250   0.6725   0.02069   0.01025  -0.0165   0.0901   1.0000
   5.500   0.6869   0.02116   0.01074  -0.0143   0.0878   1.0000
   5.750   0.7004   0.02168   0.01128  -0.0120   0.0859   1.0000
   6.000   0.7128   0.02227   0.01188  -0.0094   0.0844   1.0000
   6.250   0.7261   0.02279   0.01245  -0.0070   0.0833   1.0000
   6.500   0.7395   0.02333   0.01306  -0.0046   0.0821   1.0000
   6.750   0.7528   0.02391   0.01370  -0.0021   0.0808   1.0000
   7.000   0.7661   0.02453   0.01437   0.0003   0.0792   1.0000
   7.250   0.7796   0.02518   0.01507   0.0027   0.0777   1.0000
   7.500   0.7936   0.02589   0.01582   0.0049   0.0766   1.0000
   7.750   0.8084   0.02666   0.01661   0.0070   0.0756   1.0000
   8.000   0.8241   0.02748   0.01749   0.0090   0.0747   1.0000
   8.250   0.8407   0.02840   0.01843   0.0107   0.0738   1.0000
   8.500   0.8587   0.02944   0.01950   0.0122   0.0729   1.0000
   8.750   0.8783   0.03069   0.02078   0.0134   0.0720   1.0000
   9.000   0.8978   0.03213   0.02228   0.0144   0.0709   1.0000
   9.250   0.9120   0.03309   0.02346   0.0166   0.0699   1.0000
   9.500   0.9259   0.03419   0.02477   0.0186   0.0689   1.0000
   9.750   0.9398   0.03547   0.02627   0.0206   0.0680   1.0000
  10.000   0.9517   0.03681   0.02783   0.0229   0.0669   1.0000
  10.250   0.9618   0.03816   0.02938   0.0252   0.0653   1.0000
  10.500   0.9709   0.03947   0.03084   0.0276   0.0634   1.0000
  10.750   0.9801   0.04079   0.03229   0.0297   0.0614   1.0000
  11.000   0.9939   0.04261   0.03409   0.0309   0.0593   1.0000
  11.250   0.9960   0.04464   0.03633   0.0336   0.0576   1.0000
  11.500   0.9901   0.04600   0.03803   0.0376   0.0563   1.0000
  11.750   0.9815   0.04756   0.03987   0.0417   0.0549   1.0000
  12.000   0.9728   0.04932   0.04185   0.0452   0.0536   1.0000
  12.250   0.9648   0.05135   0.04409   0.0480   0.0524   1.0000
  12.500   0.9609   0.05324   0.04610   0.0501   0.0509   1.0000
  12.750   0.9564   0.05530   0.04828   0.0517   0.0497   1.0000
  13.000   0.9555   0.05737   0.05040   0.0527   0.0485   1.0000
  13.250   0.9558   0.06017   0.05321   0.0533   0.0474   1.0000
  13.500   0.9288   0.06409   0.05743   0.0538   0.0470   1.0000
  13.750   0.9009   0.06903   0.06263   0.0527   0.0468   1.0000
  14.000   0.8728   0.07497   0.06878   0.0502   0.0468   1.0000
  14.250   0.8386   0.08267   0.07668   0.0458   0.0468   1.0000
  14.500   0.8033   0.09195   0.08612   0.0399   0.0471   1.0000
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