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GOE 436 AIRFOIL (goe436-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 436 AIRFOIL (goe436-il)
Reynolds number: 50,000
Max Cl/Cd: 34.91 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe436-il-50000-n5.txt
Download as CSV file: xf-goe436-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3339   0.10721   0.09990  -0.0322   1.0000   0.1408
  -9.000  -0.3444   0.10555   0.09836  -0.0330   1.0000   0.1468
  -8.750  -0.3676   0.10451   0.09751  -0.0344   1.0000   0.1484
  -8.500  -0.3449   0.09971   0.09268  -0.0321   1.0000   0.1526
  -8.250  -0.3423   0.09711   0.09014  -0.0310   1.0000   0.1563
  -8.000  -0.3492   0.09489   0.08802  -0.0302   1.0000   0.1592
  -7.750  -0.3630   0.09303   0.08630  -0.0291   1.0000   0.1612
  -7.500  -0.4102   0.08486   0.07817  -0.0369   1.0000   0.1003
  -7.250  -0.4064   0.08216   0.07551  -0.0343   1.0000   0.0982
  -7.000  -0.4117   0.07921   0.07260  -0.0334   1.0000   0.0966
  -6.750  -0.4183   0.07612   0.06952  -0.0330   1.0000   0.0961
  -6.500  -0.4232   0.07293   0.06631  -0.0328   1.0000   0.0955
  -6.250  -0.4261   0.06963   0.06296  -0.0328   1.0000   0.0954
  -6.000  -0.4263   0.06623   0.05947  -0.0328   1.0000   0.0950
  -5.750  -0.4239   0.06267   0.05577  -0.0329   1.0000   0.0938
  -5.500  -0.4190   0.05897   0.05188  -0.0332   1.0000   0.0926
  -5.250  -0.4012   0.05479   0.04739  -0.0358   0.9965   0.0917
  -5.000  -0.3721   0.05120   0.04346  -0.0394   0.9893   0.0934
  -4.750  -0.3414   0.04780   0.03965  -0.0429   0.9822   0.0955
  -4.500  -0.3108   0.04458   0.03596  -0.0457   0.9748   0.0957
  -4.250  -0.2804   0.04177   0.03268  -0.0479   0.9672   0.0962
  -4.000  -0.2459   0.03937   0.02976  -0.0504   0.9602   0.0982
  -3.750  -0.2139   0.03740   0.02717  -0.0519   0.9507   0.1008
  -3.500  -0.1774   0.03546   0.02495  -0.0542   0.9409   0.1025
  -3.250  -0.1368   0.03377   0.02302  -0.0569   0.9306   0.1043
  -3.000  -0.1013   0.03247   0.02151  -0.0584   0.9179   0.1074
  -2.750  -0.0648   0.03132   0.02009  -0.0600   0.9059   0.1121
  -2.500  -0.0236   0.03012   0.01852  -0.0621   0.8968   0.1156
  -2.250   0.0113   0.02904   0.01730  -0.0631   0.8858   0.1182
  -2.000   0.0456   0.02819   0.01644  -0.0641   0.8747   0.1232
  -1.750   0.0898   0.02733   0.01539  -0.0666   0.8666   0.1311
  -1.500   0.1249   0.02655   0.01459  -0.0674   0.8549   0.1363
  -1.250   0.1588   0.02588   0.01387  -0.0681   0.8429   0.1435
  -1.000   0.1941   0.02520   0.01318  -0.0689   0.8315   0.1549
  -0.750   0.2310   0.02447   0.01245  -0.0700   0.8207   0.1697
  -0.500   0.2604   0.02387   0.01192  -0.0698   0.8065   0.1877
  -0.250   0.2891   0.02307   0.01147  -0.0697   0.7921   0.2387
   0.000   0.3625   0.02043   0.01100  -0.0770   0.7805   1.0000
   0.250   0.3901   0.02041   0.01069  -0.0763   0.7637   1.0000
   0.500   0.4170   0.02039   0.01044  -0.0756   0.7461   1.0000
   0.750   0.4440   0.02037   0.01021  -0.0748   0.7280   1.0000
   1.000   0.4716   0.02035   0.00999  -0.0742   0.7099   1.0000
   1.250   0.4985   0.02037   0.00981  -0.0734   0.6915   1.0000
   1.500   0.5243   0.02045   0.00972  -0.0725   0.6722   1.0000
   1.750   0.5510   0.02054   0.00963  -0.0718   0.6536   1.0000
   2.000   0.5777   0.02069   0.00960  -0.0711   0.6357   1.0000
   2.250   0.6040   0.02090   0.00963  -0.0705   0.6185   1.0000
   2.500   0.6296   0.02117   0.00976  -0.0698   0.6021   1.0000
   2.750   0.6546   0.02149   0.00994  -0.0690   0.5863   1.0000
   3.000   0.6793   0.02185   0.01019  -0.0683   0.5717   1.0000
   3.250   0.7040   0.02223   0.01049  -0.0676   0.5582   1.0000
   3.500   0.7293   0.02261   0.01076  -0.0670   0.5460   1.0000
   3.750   0.7538   0.02303   0.01112  -0.0663   0.5343   1.0000
   4.000   0.7773   0.02351   0.01159  -0.0655   0.5231   1.0000
   4.250   0.8024   0.02395   0.01198  -0.0650   0.5135   1.0000
   4.500   0.8268   0.02442   0.01244  -0.0644   0.5039   1.0000
   4.750   0.8503   0.02496   0.01301  -0.0637   0.4948   1.0000
   5.000   0.8761   0.02543   0.01344  -0.0632   0.4868   1.0000
   5.250   0.8983   0.02606   0.01414  -0.0624   0.4783   1.0000
   5.500   0.9243   0.02656   0.01463  -0.0620   0.4710   1.0000
   5.750   0.9455   0.02726   0.01544  -0.0611   0.4628   1.0000
   6.000   0.9711   0.02782   0.01600  -0.0607   0.4558   1.0000
   6.250   0.9916   0.02858   0.01690  -0.0597   0.4479   1.0000
   6.500   1.0160   0.02920   0.01756  -0.0592   0.4407   1.0000
   6.750   1.0363   0.02999   0.01847  -0.0581   0.4329   1.0000
   7.000   1.0593   0.03064   0.01919  -0.0574   0.4250   1.0000
   7.250   1.0784   0.03146   0.02016  -0.0562   0.4168   1.0000
   7.500   1.1010   0.03210   0.02086  -0.0553   0.4084   1.0000
   7.750   1.1177   0.03300   0.02193  -0.0539   0.3998   1.0000
   8.000   1.1414   0.03354   0.02251  -0.0531   0.3911   1.0000
   8.250   1.1537   0.03450   0.02371  -0.0510   0.3812   1.0000
   8.500   1.1746   0.03498   0.02424  -0.0498   0.3712   1.0000
   8.750   1.1891   0.03565   0.02506  -0.0479   0.3603   1.0000
   9.000   1.2001   0.03648   0.02607  -0.0457   0.3497   1.0000
   9.250   1.2186   0.03691   0.02659  -0.0441   0.3395   1.0000
   9.500   1.2279   0.03776   0.02764  -0.0417   0.3290   1.0000
   9.750   1.2354   0.03864   0.02870  -0.0391   0.3185   1.0000
  10.000   1.2496   0.03910   0.02924  -0.0372   0.3084   1.0000
  10.250   1.2518   0.04018   0.03054  -0.0341   0.2978   1.0000
  10.500   1.2516   0.04128   0.03181  -0.0308   0.2878   1.0000
  10.750   1.2549   0.04204   0.03268  -0.0278   0.2770   1.0000
  11.000   1.2512   0.04335   0.03415  -0.0247   0.2660   1.0000
  11.250   1.2430   0.04532   0.03630  -0.0219   0.2552   1.0000
  11.500   1.2388   0.04713   0.03825  -0.0197   0.2444   1.0000
  11.750   1.2361   0.04893   0.04013  -0.0178   0.2332   1.0000
  12.000   1.2278   0.05160   0.04296  -0.0164   0.2220   1.0000
  12.250   1.2175   0.05481   0.04630  -0.0156   0.2106   1.0000
  12.500   1.2099   0.05788   0.04945  -0.0150   0.1990   1.0000
  12.750   1.2038   0.06095   0.05254  -0.0146   0.1871   1.0000
  13.000   1.1988   0.06402   0.05558  -0.0145   0.1754   1.0000
  13.250   1.1948   0.06704   0.05854  -0.0143   0.1641   1.0000
  13.500   1.1833   0.07161   0.06320  -0.0151   0.1544   1.0000
  13.750   1.1774   0.07541   0.06699  -0.0155   0.1458   1.0000
  14.000   1.1770   0.07833   0.06983  -0.0154   0.1376   1.0000
  14.250   1.1661   0.08342   0.07507  -0.0167   0.1311   1.0000
  14.500   1.1667   0.08634   0.07793  -0.0169   0.1238   1.0000
  14.750   1.1546   0.09191   0.08367  -0.0187   0.1183   1.0000
  15.000   1.1469   0.09668   0.08853  -0.0203   0.1124   1.0000
  15.250   1.1431   0.10068   0.09252  -0.0215   0.1064   1.0000
  15.500   1.1249   0.10800   0.10006  -0.0248   0.1022   1.0000
  15.750   1.1330   0.10947   0.10137  -0.0248   0.0953   1.0000
  16.000   1.1087   0.11856   0.11076  -0.0293   0.0926   1.0000
  16.250   1.0815   0.12877   0.12118  -0.0346   0.0902   1.0000
  16.500   1.1013   0.12758   0.11986  -0.0332   0.0834   1.0000
  16.750   1.0653   0.14059   0.13309  -0.0403   0.0822   1.0000
  17.000   1.0176   0.15842   0.15094  -0.0502   0.0811   1.0000
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