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GOE 436 AIRFOIL (goe436-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 436 AIRFOIL (goe436-il)
Reynolds number: 50,000
Max Cl/Cd: 23.53 at α=12°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe436-il-50000.txt
Download as CSV file: xf-goe436-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 436 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3379   0.10675   0.09966  -0.0257   1.0000   0.2365
  -8.500  -0.3258   0.10276   0.09569  -0.0245   1.0000   0.2442
  -8.250  -0.3433   0.10227   0.09534  -0.0240   1.0000   0.2536
  -8.000  -0.3265   0.09815   0.09124  -0.0222   1.0000   0.2663
  -7.750  -0.3645   0.09910   0.09243  -0.0208   1.0000   0.2712
  -7.500  -0.3455   0.09496   0.08830  -0.0189   1.0000   0.2864
  -7.250  -0.3335   0.09145   0.08483  -0.0170   1.0000   0.2981
  -7.000  -0.3771   0.09244   0.08608  -0.0133   1.0000   0.3043
  -6.750  -0.3640   0.08901   0.08267  -0.0110   1.0000   0.3194
  -6.500  -0.3598   0.08631   0.08004  -0.0082   1.0000   0.3334
  -6.250  -0.3657   0.08439   0.07820  -0.0048   1.0000   0.3479
  -6.000  -0.3741   0.08268   0.07660  -0.0011   1.0000   0.3645
  -5.750  -0.3828   0.08106   0.07508   0.0026   1.0000   0.3831
  -5.500  -0.3991   0.07987   0.07401   0.0064   1.0000   0.4030
  -5.250  -0.3886   0.07719   0.07139   0.0106   1.0000   0.4300
  -5.000  -0.4139   0.07663   0.07096   0.0151   1.0000   0.4545
  -4.750  -0.4131   0.07472   0.06912   0.0203   1.0000   0.4879
  -4.500  -0.3871   0.07181   0.06622   0.0253   1.0000   0.5355
  -4.250  -0.1360   0.05951   0.05329   0.0112   1.0000   0.8276
  -4.000   0.0600   0.04703   0.04032  -0.0241   1.0000   0.9857
  -3.750  -0.0066   0.04977   0.04336  -0.0080   1.0000   0.9485
  -3.500  -0.0776   0.05226   0.04613   0.0071   1.0000   0.9074
  -3.250  -0.1486   0.05387   0.04801   0.0200   1.0000   0.8591
  -3.000  -0.3296   0.04698   0.03978  -0.0210   1.0000   0.2733
  -2.750  -0.2914   0.04274   0.03457  -0.0258   1.0000   0.2194
  -2.500  -0.2713   0.04064   0.03226  -0.0259   1.0000   0.2131
  -2.250  -0.2460   0.03910   0.02994  -0.0266   1.0000   0.2046
  -2.000  -0.2273   0.03762   0.02832  -0.0263   1.0000   0.2027
  -1.750  -0.2079   0.03641   0.02687  -0.0260   1.0000   0.2003
  -1.500  -0.1555   0.03549   0.02547  -0.0313   0.9867   0.2013
  -1.250  -0.0966   0.03485   0.02435  -0.0373   0.9703   0.2054
  -1.000  -0.0453   0.03402   0.02337  -0.0421   0.9525   0.2097
  -0.750   0.0052   0.03362   0.02272  -0.0464   0.9336   0.2207
  -0.500   0.0583   0.03301   0.02208  -0.0508   0.9150   0.2329
  -0.250   0.1151   0.03249   0.02150  -0.0556   0.8967   0.2539
   0.000   0.1694   0.03169   0.02093  -0.0599   0.8790   0.2897
   0.250   0.2506   0.02853   0.01994  -0.0676   0.8638   1.0000
   0.500   0.2970   0.02872   0.01965  -0.0703   0.8432   1.0000
   0.750   0.3396   0.02885   0.01950  -0.0723   0.8221   1.0000
   1.000   0.3883   0.02876   0.01920  -0.0752   0.8035   1.0000
   1.250   0.4334   0.02865   0.01892  -0.0773   0.7858   1.0000
   1.500   0.4744   0.02855   0.01868  -0.0786   0.7686   1.0000
   1.750   0.5111   0.02854   0.01854  -0.0793   0.7520   1.0000
   2.000   0.5443   0.02863   0.01852  -0.0795   0.7360   1.0000
   2.250   0.5743   0.02883   0.01864  -0.0792   0.7205   1.0000
   2.500   0.6014   0.02918   0.01891  -0.0787   0.7057   1.0000
   2.750   0.6263   0.02968   0.01936  -0.0779   0.6917   1.0000
   3.000   0.6517   0.03019   0.01981  -0.0773   0.6788   1.0000
   3.250   0.6873   0.03022   0.01977  -0.0776   0.6684   1.0000
   3.500   0.7085   0.03101   0.02053  -0.0766   0.6563   1.0000
   3.750   0.7217   0.03231   0.02185  -0.0749   0.6442   1.0000
   4.000   0.7476   0.03297   0.02249  -0.0744   0.6345   1.0000
   4.250   0.7699   0.03383   0.02336  -0.0736   0.6245   1.0000
   4.500   0.7753   0.03580   0.02537  -0.0715   0.6138   1.0000
   4.750   0.8138   0.03579   0.02536  -0.0721   0.6064   1.0000
   5.000   0.8036   0.03881   0.02844  -0.0689   0.5952   1.0000
   5.250   0.8377   0.03913   0.02878  -0.0691   0.5880   1.0000
   5.500   0.8227   0.04265   0.03236  -0.0660   0.5778   1.0000
   5.750   0.8306   0.04475   0.03451  -0.0645   0.5693   1.0000
   6.000   0.8291   0.04754   0.03735  -0.0626   0.5606   1.0000
   6.250   0.8020   0.05218   0.04198  -0.0595   0.5521   1.0000
   6.500   0.8111   0.05437   0.04421  -0.0584   0.5438   1.0000
   6.750   0.7799   0.05993   0.04975  -0.0568   0.5361   1.0000
   7.000   0.7979   0.06152   0.05140  -0.0561   0.5275   1.0000
   7.250   0.7775   0.06628   0.05616  -0.0551   0.5203   1.0000
   7.500   0.8206   0.06587   0.05589  -0.0545   0.5100   1.0000
   7.750   0.7789   0.07250   0.06246  -0.0539   0.5042   1.0000
   8.000   0.8222   0.07218   0.06229  -0.0531   0.4929   1.0000
   8.250   0.7817   0.07884   0.06891  -0.0531   0.4881   1.0000
   8.500   0.8180   0.07933   0.06953  -0.0523   0.4769   1.0000
   8.750   0.7859   0.08550   0.07569  -0.0528   0.4733   1.0000
   9.000   0.7744   0.09021   0.08044  -0.0533   0.4705   1.0000
   9.250   0.7954   0.09223   0.08256  -0.0528   0.4595   1.0000
   9.500   0.7853   0.09726   0.08763  -0.0538   0.4594   1.0000
   9.750   0.7939   0.10181   0.09228  -0.0550   0.4617   1.0000
  11.500   1.2362   0.06124   0.05346  -0.0242   0.2869   1.0000
  12.000   1.3059   0.05551   0.04747  -0.0185   0.2285   1.0000
  12.250   1.2496   0.06241   0.05469  -0.0152   0.2301   1.0000
  12.500   1.2010   0.07016   0.06256  -0.0148   0.2293   1.0000
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