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GOE 767 AIRFOIL (goe767-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 767 AIRFOIL (goe767-il)
Reynolds number: 50,000
Max Cl/Cd: 23.94 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe767-il-50000-n5.txt
Download as CSV file: xf-goe767-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 767 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6192   0.09237   0.08433  -0.0031   1.0000   0.0877
 -10.000  -0.6460   0.08224   0.07423  -0.0105   1.0000   0.0880
  -9.750  -0.6903   0.07150   0.06344  -0.0185   1.0000   0.0877
  -9.500  -0.7282   0.06455   0.05631  -0.0204   1.0000   0.0879
  -9.250  -0.7565   0.05809   0.04949  -0.0210   1.0000   0.0887
  -9.000  -0.7579   0.05454   0.04574  -0.0205   1.0000   0.0903
  -8.750  -0.7446   0.05283   0.04402  -0.0196   1.0000   0.0925
  -8.500  -0.7395   0.04978   0.04074  -0.0188   1.0000   0.0948
  -8.250  -0.7368   0.04599   0.03652  -0.0178   1.0000   0.0976
  -8.000  -0.7295   0.04255   0.03263  -0.0166   1.0000   0.1008
  -7.750  -0.7103   0.04131   0.03141  -0.0157   1.0000   0.1041
  -7.500  -0.6951   0.03920   0.02902  -0.0146   1.0000   0.1090
  -7.250  -0.6785   0.03714   0.02671  -0.0135   1.0000   0.1140
  -7.000  -0.6584   0.03593   0.02547  -0.0125   1.0000   0.1194
  -6.750  -0.6401   0.03410   0.02329  -0.0114   1.0000   0.1263
  -6.500  -0.6185   0.03321   0.02248  -0.0105   1.0000   0.1326
  -6.250  -0.5983   0.03188   0.02090  -0.0094   1.0000   0.1408
  -6.000  -0.5763   0.03107   0.02016  -0.0085   1.0000   0.1485
  -5.750  -0.5548   0.03002   0.01895  -0.0075   1.0000   0.1571
  -5.500  -0.5323   0.02915   0.01808  -0.0065   1.0000   0.1653
  -5.250  -0.5096   0.02813   0.01697  -0.0056   1.0000   0.1731
  -5.000  -0.4862   0.02723   0.01608  -0.0047   1.0000   0.1802
  -4.750  -0.4624   0.02632   0.01501  -0.0038   1.0000   0.1877
  -4.500  -0.4384   0.02545   0.01427  -0.0030   1.0000   0.1941
  -4.250  -0.4142   0.02468   0.01343  -0.0021   1.0000   0.2019
  -4.000  -0.3900   0.02390   0.01276  -0.0013   1.0000   0.2091
  -3.750  -0.3658   0.02322   0.01214  -0.0004   1.0000   0.2170
  -3.500  -0.3417   0.02258   0.01158   0.0004   1.0000   0.2259
  -3.250  -0.3182   0.02200   0.01113   0.0012   1.0000   0.2362
  -3.000  -0.2927   0.02143   0.01074   0.0014   0.9951   0.2475
  -2.750  -0.2366   0.02073   0.01022  -0.0041   0.9297   0.2718
  -2.500  -0.1832   0.02004   0.00971  -0.0085   0.8462   0.3072
  -2.250  -0.1448   0.01948   0.00926  -0.0096   0.7637   0.3592
  -2.000  -0.1203   0.01904   0.00898  -0.0080   0.7060   0.4327
  -1.750  -0.1002   0.01869   0.00890  -0.0054   0.6651   0.5320
  -1.500  -0.0783   0.01853   0.00901  -0.0026   0.6324   0.6450
  -1.250  -0.0498   0.01861   0.00917  -0.0009   0.6037   0.7438
  -1.000  -0.0111   0.01886   0.00937  -0.0010   0.5762   0.8254
  -0.750   0.0355   0.01923   0.00954  -0.0030   0.5506   0.8882
  -0.500   0.0876   0.01961   0.00964  -0.0064   0.5271   0.9385
  -0.250   0.1573   0.01987   0.00961  -0.0137   0.5020   0.9831
   0.000   0.2009   0.01997   0.00947  -0.0170   0.4836   1.0000
   0.250   0.2215   0.02011   0.00946  -0.0159   0.4703   1.0000
   0.500   0.2429   0.02029   0.00953  -0.0149   0.4573   1.0000
   0.750   0.2644   0.02051   0.00960  -0.0138   0.4463   1.0000
   1.000   0.2860   0.02076   0.00975  -0.0128   0.4345   1.0000
   1.250   0.3083   0.02105   0.00994  -0.0118   0.4235   1.0000
   1.500   0.3309   0.02136   0.01012  -0.0108   0.4138   1.0000
   1.750   0.3537   0.02173   0.01045  -0.0099   0.4041   1.0000
   2.000   0.3764   0.02210   0.01072  -0.0089   0.3953   1.0000
   2.250   0.3992   0.02253   0.01111  -0.0080   0.3864   1.0000
   2.500   0.4220   0.02295   0.01147  -0.0070   0.3779   1.0000
   2.750   0.4449   0.02342   0.01187  -0.0061   0.3703   1.0000
   3.000   0.4676   0.02394   0.01240  -0.0052   0.3618   1.0000
   3.250   0.4907   0.02436   0.01268  -0.0041   0.3551   1.0000
   3.500   0.5129   0.02497   0.01340  -0.0032   0.3456   1.0000
   3.750   0.5357   0.02539   0.01372  -0.0021   0.3383   1.0000
   4.000   0.5577   0.02600   0.01440  -0.0012   0.3290   1.0000
   4.250   0.5804   0.02642   0.01475  -0.0001   0.3211   1.0000
   4.500   0.6023   0.02704   0.01544   0.0008   0.3124   1.0000
   4.750   0.6248   0.02754   0.01591   0.0018   0.3043   1.0000
   5.000   0.6470   0.02817   0.01656   0.0028   0.2967   1.0000
   5.250   0.6687   0.02884   0.01731   0.0037   0.2884   1.0000
   5.500   0.6917   0.02933   0.01771   0.0047   0.2819   1.0000
   5.750   0.7119   0.03029   0.01887   0.0056   0.2731   1.0000
   6.000   0.7353   0.03072   0.01920   0.0066   0.2670   1.0000
   6.250   0.7541   0.03188   0.02060   0.0075   0.2584   1.0000
   6.500   0.7764   0.03250   0.02119   0.0084   0.2519   1.0000
   6.750   0.7956   0.03361   0.02243   0.0093   0.2447   1.0000
   7.000   0.8152   0.03460   0.02353   0.0103   0.2375   1.0000
   7.250   0.8388   0.03505   0.02385   0.0112   0.2325   1.0000
   7.500   0.8511   0.03711   0.02628   0.0121   0.2247   1.0000
   7.750   0.8717   0.03792   0.02712   0.0130   0.2192   1.0000
   8.000   0.8890   0.03923   0.02851   0.0140   0.2138   1.0000
   8.250   0.8982   0.04147   0.03104   0.0149   0.2072   1.0000
   8.500   0.9177   0.04240   0.03197   0.0158   0.2027   1.0000
   8.750   0.9315   0.04404   0.03372   0.0167   0.1982   1.0000
   9.000   0.9253   0.04779   0.03786   0.0175   0.1925   1.0000
   9.250   0.9366   0.04940   0.03954   0.0184   0.1881   1.0000
   9.500   0.9655   0.04923   0.03925   0.0195   0.1848   1.0000
   9.750   0.8960   0.05902   0.04956   0.0185   0.1807   1.0000
  10.000   0.7742   0.07994   0.07056   0.0053   0.1745   1.0000
  10.250   0.7942   0.08003   0.07066   0.0068   0.1718   1.0000
  10.750   0.7286   0.09933   0.08994  -0.0042   0.1621   1.0000
  11.000   0.7394   0.10133   0.09196  -0.0041   0.1588   1.0000
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