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GOE 427 AIRFOIL (goe427-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 427 AIRFOIL (goe427-il)
Reynolds number: 200,000
Max Cl/Cd: 89.01 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe427-il-200000.txt
Download as CSV file: xf-goe427-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 427 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3420   0.09533   0.09193  -0.0213   1.0000   0.0241
  -7.500  -0.3468   0.09366   0.09032  -0.0196   1.0000   0.0244
  -7.250  -0.3527   0.09203   0.08875  -0.0177   1.0000   0.0247
  -7.000  -0.3546   0.08995   0.08673  -0.0170   1.0000   0.0252
  -6.750  -0.3555   0.08786   0.08469  -0.0165   1.0000   0.0256
  -6.500  -0.3555   0.08574   0.08261  -0.0162   1.0000   0.0260
  -6.250  -0.3545   0.08352   0.08042  -0.0163   1.0000   0.0267
  -6.000  -0.3520   0.08125   0.07819  -0.0167   1.0000   0.0273
  -5.750  -0.3474   0.07890   0.07586  -0.0175   1.0000   0.0282
  -5.500  -0.3395   0.07656   0.07353  -0.0192   1.0000   0.0290
  -5.250  -0.3080   0.07394   0.07085  -0.0273   0.9985   0.0303
  -5.000  -0.2501   0.06979   0.06653  -0.0404   0.9940   0.0310
  -4.750  -0.2072   0.06529   0.06191  -0.0483   0.9891   0.0311
  -4.500  -0.1859   0.05778   0.05441  -0.0526   0.9852   0.0324
  -4.250  -0.1595   0.05415   0.05075  -0.0552   0.9809   0.0346
  -4.000  -0.1220   0.05068   0.04718  -0.0606   0.9754   0.0391
  -3.750  -0.0510   0.04751   0.04360  -0.0720   0.9720   0.0438
  -3.500  -0.0158   0.04136   0.03734  -0.0774   0.9694   0.0454
  -2.500   0.1281   0.02991   0.02518  -0.0899   0.9497   0.0742
  -2.250   0.1675   0.02758   0.02262  -0.0929   0.9458   0.0874
  -2.000   0.2083   0.02547   0.02031  -0.0961   0.9431   0.1019
  -1.500   0.2874   0.01786   0.01113  -0.0980   0.9339   0.0602
  -1.250   0.3280   0.01645   0.00948  -0.1003   0.9307   0.0634
  -1.000   0.3720   0.01520   0.00799  -0.1030   0.9285   0.0669
  -0.750   0.4030   0.01433   0.00699  -0.1032   0.9195   0.0691
  -0.500   0.4455   0.01335   0.00600  -0.1057   0.9157   0.0754
  -0.250   0.4763   0.01272   0.00539  -0.1059   0.9061   0.0799
   0.000   0.5151   0.01202   0.00475  -0.1076   0.9011   0.0899
   0.250   0.5435   0.01154   0.00437  -0.1074   0.8903   0.1159
   0.500   0.5883   0.00933   0.00414  -0.1110   0.8840   1.0000
   0.750   0.6209   0.00916   0.00382  -0.1115   0.8738   1.0000
   1.000   0.6499   0.00907   0.00362  -0.1112   0.8605   1.0000
   1.250   0.6790   0.00900   0.00347  -0.1110   0.8463   1.0000
   1.500   0.7057   0.00897   0.00337  -0.1103   0.8272   1.0000
   1.750   0.7330   0.00892   0.00318  -0.1095   0.8022   1.0000
   2.000   0.7585   0.00898   0.00309  -0.1085   0.7747   1.0000
   2.250   0.7836   0.00910   0.00309  -0.1075   0.7490   1.0000
   2.500   0.8079   0.00925   0.00318  -0.1065   0.7227   1.0000
   2.750   0.8319   0.00943   0.00326  -0.1054   0.6952   1.0000
   3.000   0.8554   0.00964   0.00336  -0.1043   0.6664   1.0000
   3.250   0.8785   0.00987   0.00348  -0.1031   0.6354   1.0000
   3.500   0.9005   0.01014   0.00361  -0.1017   0.5985   1.0000
   3.750   0.9217   0.01052   0.00382  -0.1002   0.5597   1.0000
   4.000   0.9430   0.01095   0.00407  -0.0988   0.5256   1.0000
   4.250   0.9650   0.01134   0.00438  -0.0976   0.4954   1.0000
   4.500   0.9871   0.01169   0.00469  -0.0964   0.4624   1.0000
   4.750   1.0071   0.01214   0.00500  -0.0948   0.4081   1.0000
   5.000   1.0214   0.01310   0.00549  -0.0924   0.3059   1.0000
   5.250   1.0243   0.01570   0.00674  -0.0888   0.0879   1.0000
   5.500   1.0427   0.01673   0.00767  -0.0871   0.0632   1.0000
   5.750   1.0623   0.01756   0.00855  -0.0856   0.0541   1.0000
   6.000   1.0784   0.01875   0.00978  -0.0836   0.0479   1.0000
   6.250   1.0954   0.01983   0.01098  -0.0816   0.0447   1.0000
   6.500   1.1107   0.02113   0.01235  -0.0796   0.0399   1.0000
   6.750   1.1230   0.02363   0.01486  -0.0770   0.0368   1.0000
   7.000   1.1446   0.02527   0.01661  -0.0757   0.0353   1.0000
   7.250   1.1676   0.02701   0.01851  -0.0746   0.0331   1.0000
   7.500   1.1901   0.02885   0.02049  -0.0737   0.0302   1.0000
   7.750   1.2147   0.03143   0.02328  -0.0729   0.0293   1.0000
   8.000   1.2382   0.03466   0.02690  -0.0716   0.0299   1.0000
   8.250   1.2585   0.03940   0.03223  -0.0695   0.0333   1.0000
  15.750   0.8650   0.19534   0.19250  -0.0948   0.0363   1.0000
  16.000   0.8632   0.19971   0.19687  -0.0978   0.0360   1.0000
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