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GOE 437 AIRFOIL (goe437-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 437 AIRFOIL (goe437-il)
Reynolds number: 50,000
Max Cl/Cd: 41.18 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe437-il-50000.txt
Download as CSV file: xf-goe437-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 437 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3268   0.10470   0.09808  -0.0247   1.0000   0.1328
  -7.750  -0.3322   0.10347   0.09697  -0.0250   1.0000   0.1364
  -7.500  -0.3465   0.10357   0.09726  -0.0255   1.0000   0.1380
  -7.250  -0.3349   0.09841   0.09214  -0.0238   1.0000   0.1415
  -7.000  -0.3317   0.09557   0.08938  -0.0228   1.0000   0.1470
  -6.750  -0.3390   0.09467   0.08861  -0.0246   1.0000   0.1514
  -6.500  -0.3396   0.09206   0.08612  -0.0252   1.0000   0.1539
  -6.250  -0.3323   0.08828   0.08239  -0.0224   1.0000   0.1612
  -6.000  -0.3378   0.08795   0.08215  -0.0271   1.0000   0.1664
  -5.500  -0.3322   0.08275   0.07709  -0.0278   1.0000   0.1808
  -5.250  -0.3285   0.07854   0.07297  -0.0220   1.0000   0.1904
  -4.750  -0.3215   0.07378   0.06830  -0.0243   1.0000   0.2097
  -4.500  -0.3150   0.07143   0.06595  -0.0254   1.0000   0.2228
  -4.250  -0.3081   0.06877   0.06326  -0.0254   1.0000   0.2365
  -4.000  -0.3016   0.06582   0.06035  -0.0244   1.0000   0.2508
  -3.750  -0.2958   0.06284   0.05743  -0.0225   1.0000   0.2663
  -3.500  -0.2890   0.06015   0.05478  -0.0207   1.0000   0.2860
  -3.250  -0.2815   0.05757   0.05223  -0.0194   1.0000   0.3138
  -3.000  -0.2760   0.05511   0.04983  -0.0172   1.0000   0.3524
  -2.750  -0.2753   0.05283   0.04765  -0.0124   1.0000   0.3975
  -1.750  -0.0529   0.03713   0.02920  -0.0525   1.0000   0.1639
  -1.500  -0.0246   0.03486   0.02652  -0.0536   1.0000   0.1588
  -1.250   0.0020   0.03315   0.02437  -0.0542   1.0000   0.1607
  -1.000   0.0282   0.03160   0.02234  -0.0545   1.0000   0.1598
  -0.750   0.0511   0.03061   0.02102  -0.0546   1.0000   0.1714
  -0.500   0.0776   0.02977   0.01985  -0.0553   0.9982   0.1851
  -0.250   0.1366   0.02886   0.01842  -0.0612   0.9842   0.2234
   0.000   0.1975   0.02780   0.01725  -0.0673   0.9703   0.2891
   0.500   0.3059   0.02561   0.01622  -0.0769   0.9371   1.0000
   0.750   0.3545   0.02626   0.01642  -0.0812   0.9182   1.0000
   1.000   0.4057   0.02679   0.01663  -0.0857   0.9009   1.0000
   1.250   0.4434   0.02727   0.01692  -0.0879   0.8816   1.0000
   1.500   0.4862   0.02764   0.01712  -0.0907   0.8639   1.0000
   1.750   0.5322   0.02787   0.01723  -0.0938   0.8477   1.0000
   2.000   0.5796   0.02795   0.01725  -0.0968   0.8323   1.0000
   2.250   0.6161   0.02822   0.01748  -0.0981   0.8156   1.0000
   2.500   0.6491   0.02853   0.01778  -0.0987   0.7984   1.0000
   2.750   0.6842   0.02875   0.01800  -0.0994   0.7823   1.0000
   3.000   0.7188   0.02897   0.01828  -0.0999   0.7668   1.0000
   3.250   0.7523   0.02919   0.01853  -0.1002   0.7515   1.0000
   3.500   0.7838   0.02949   0.01888  -0.1002   0.7366   1.0000
   3.750   0.8136   0.02988   0.01933  -0.0999   0.7218   1.0000
   4.000   0.8416   0.03037   0.01990  -0.0995   0.7072   1.0000
   4.250   0.8676   0.03100   0.02068  -0.0988   0.6930   1.0000
   4.500   0.8920   0.03174   0.02153  -0.0980   0.6789   1.0000
   4.750   0.9144   0.03263   0.02254  -0.0972   0.6652   1.0000
   5.000   0.9357   0.03361   0.02367  -0.0962   0.6517   1.0000
   5.250   0.9553   0.03476   0.02497  -0.0952   0.6385   1.0000
   5.500   0.9744   0.03596   0.02641  -0.0941   0.6256   1.0000
   5.750   0.9929   0.03723   0.02786  -0.0930   0.6128   1.0000
   6.000   1.0120   0.03845   0.02929  -0.0919   0.6001   1.0000
   6.250   1.0311   0.03967   0.03074  -0.0907   0.5874   1.0000
   6.500   1.0508   0.04084   0.03215  -0.0894   0.5746   1.0000
   6.750   1.0710   0.04200   0.03365  -0.0882   0.5618   1.0000
   7.000   1.1471   0.03273   0.02438  -0.0820   0.5022   1.0000
   7.250   1.1727   0.03002   0.02160  -0.0772   0.4549   1.0000
   7.500   1.1740   0.02851   0.02011  -0.0705   0.3949   1.0000
   7.750   1.1683   0.02843   0.01982  -0.0640   0.3141   1.0000
   8.000   1.1545   0.03075   0.02104  -0.0583   0.1676   1.0000
   8.250   1.1461   0.03410   0.02375  -0.0545   0.1210   1.0000
   8.500   1.1432   0.03671   0.02620  -0.0510   0.1061   1.0000
   8.750   1.1425   0.03913   0.02861  -0.0477   0.0979   1.0000
   9.000   1.1446   0.04150   0.03098  -0.0449   0.0917   1.0000
   9.250   1.1581   0.04374   0.03332  -0.0425   0.0861   1.0000
   9.500   1.1947   0.04643   0.03582  -0.0422   0.0776   1.0000
   9.750   1.2363   0.04938   0.03921  -0.0425   0.0728   1.0000
  10.000   1.2740   0.05340   0.04363  -0.0426   0.0718   1.0000
  10.250   1.2930   0.05754   0.04825  -0.0414   0.0720   1.0000
  10.500   1.3016   0.06179   0.05305  -0.0396   0.0729   1.0000
  10.750   1.3028   0.06611   0.05779  -0.0375   0.0739   1.0000
  11.000   1.2991   0.07045   0.06250  -0.0353   0.0749   1.0000
  11.250   1.2903   0.07465   0.06698  -0.0330   0.0757   1.0000
  11.500   1.2791   0.07896   0.07154  -0.0311   0.0764   1.0000
  11.750   1.2678   0.08368   0.07645  -0.0298   0.0771   1.0000
  12.000   1.2592   0.08893   0.08191  -0.0293   0.0777   1.0000
  12.250   1.2193   0.09240   0.08570  -0.0294   0.0787   1.0000
  12.500   1.1780   0.09849   0.09203  -0.0326   0.0794   1.0000
  12.750   1.1381   0.10658   0.10022  -0.0383   0.0800   1.0000
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