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GOE 359 AIRFOIL (goe359-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 359 AIRFOIL (goe359-il)
Reynolds number: 1,000,000
Max Cl/Cd: 130.6 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe359-il-1000000.txt
Download as CSV file: xf-goe359-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 359 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2755   0.09981   0.09829  -0.0256   1.0000   0.0103
  -8.250  -0.2721   0.09718   0.09568  -0.0258   1.0000   0.0109
  -8.000  -0.2701   0.09448   0.09300  -0.0264   0.9999   0.0115
  -7.750  -0.2498   0.09004   0.08857  -0.0335   0.9951   0.0116
  -7.500  -0.2327   0.08601   0.08454  -0.0388   0.9828   0.0117
  -7.250  -0.2061   0.08107   0.07958  -0.0468   0.9563   0.0117
  -7.000  -0.1758   0.07418   0.07257  -0.0570   0.9158   0.0119
  -6.750  -0.1616   0.07155   0.06976  -0.0586   0.8793   0.0121
  -6.500  -0.1457   0.06900   0.06710  -0.0611   0.8574   0.0124
  -6.250  -0.1273   0.06623   0.06424  -0.0645   0.8403   0.0128
  -6.000  -0.1064   0.06314   0.06108  -0.0686   0.8259   0.0138
  -5.750  -0.0690   0.05771   0.05553  -0.0793   0.8128   0.0155
  -5.500  -0.0420   0.05343   0.05115  -0.0846   0.8007   0.0155
  -5.250  -0.0139   0.04899   0.04660  -0.0897   0.7891   0.0156
  -5.000   0.0164   0.02823   0.02584  -0.0865   0.7466   0.0164
  -4.750   0.0390   0.02604   0.02358  -0.0886   0.7346   0.0172
  -4.500   0.0755   0.02235   0.01970  -0.0942   0.7246   0.0202
  -4.250   0.1045   0.01832   0.01550  -0.0978   0.7144   0.0203
  -4.000   0.1284   0.01378   0.01076  -0.1010   0.7047   0.0195
  -3.750   0.1639   0.02391   0.02036  -0.1098   0.7195   0.0215
  -3.500   0.1875   0.02458   0.02102  -0.1097   0.7056   0.0226
  -3.250   0.2188   0.02394   0.02018  -0.1095   0.6919   0.0266
  -2.750   0.2752   0.01578   0.01096  -0.1111   0.6672   0.0279
  -2.500   0.3014   0.01479   0.00987  -0.1112   0.6534   0.0290
  -2.250   0.3282   0.01430   0.00929  -0.1112   0.6404   0.0303
  -2.000   0.3556   0.01381   0.00865  -0.1112   0.6286   0.0327
  -1.750   0.3840   0.01513   0.00990  -0.1107   0.6163   0.0359
  -1.500   0.4117   0.01428   0.00881  -0.1105   0.6047   0.0360
  -1.250   0.4393   0.01347   0.00780  -0.1104   0.5933   0.0361
  -1.000   0.4667   0.01063   0.00467  -0.1105   0.5832   0.0331
  -0.750   0.4944   0.01018   0.00410  -0.1103   0.5725   0.0335
  -0.500   0.5220   0.00970   0.00350  -0.1101   0.5614   0.0335
  -0.250   0.5494   0.00943   0.00314  -0.1099   0.5498   0.0341
   0.000   0.5769   0.00922   0.00286  -0.1098   0.5385   0.0346
   0.250   0.6043   0.00903   0.00262  -0.1096   0.5278   0.0349
   0.500   0.6315   0.00888   0.00241  -0.1094   0.5139   0.0351
   0.750   0.6585   0.00878   0.00223  -0.1092   0.4973   0.0353
   1.000   0.6855   0.00878   0.00216  -0.1090   0.4816   0.0358
   1.250   0.7127   0.00876   0.00208  -0.1089   0.4693   0.0361
   1.500   0.7400   0.00857   0.00184  -0.1088   0.4595   0.0369
   1.750   0.7674   0.00848   0.00169  -0.1086   0.4506   0.0395
   2.000   0.7949   0.00847   0.00167  -0.1085   0.4427   0.0419
   2.250   0.8221   0.00852   0.00168  -0.1084   0.4345   0.0439
   2.500   0.8497   0.00855   0.00169  -0.1083   0.4268   0.0461
   2.750   0.8769   0.00861   0.00172  -0.1082   0.4187   0.0544
   3.000   0.9009   0.00701   0.00205  -0.1080   0.4101   1.0000
   3.250   0.9280   0.00714   0.00213  -0.1079   0.4004   1.0000
   3.500   0.9547   0.00731   0.00222  -0.1077   0.3874   1.0000
   3.750   0.9804   0.00757   0.00233  -0.1073   0.3604   1.0000
   4.000   1.0053   0.00793   0.00249  -0.1069   0.3223   1.0000
   4.250   1.0281   0.00852   0.00279  -0.1062   0.2681   1.0000
   4.500   1.0513   0.00907   0.00311  -0.1055   0.2305   1.0000
   4.750   1.0754   0.00951   0.00339  -0.1050   0.2047   1.0000
   5.000   1.0997   0.00991   0.00365  -0.1045   0.1798   1.0000
   5.250   1.1190   0.01088   0.00422  -0.1033   0.1130   1.0000
   5.500   1.1379   0.01188   0.00490  -0.1020   0.0526   1.0000
   5.750   1.1619   0.01228   0.00524  -0.1014   0.0399   1.0000
   6.000   1.1841   0.01288   0.00571  -0.1006   0.0152   1.0000
   6.250   1.2087   0.01321   0.00607  -0.1001   0.0140   1.0000
   6.500   1.2327   0.01358   0.00651  -0.0995   0.0128   1.0000
   6.750   1.2559   0.01404   0.00703  -0.0987   0.0115   1.0000
   7.000   1.2783   0.01456   0.00761  -0.0979   0.0106   1.0000
   7.250   1.3012   0.01500   0.00809  -0.0972   0.0101   1.0000
   7.500   1.3232   0.01551   0.00866  -0.0963   0.0096   1.0000
   7.750   1.3445   0.01608   0.00928  -0.0953   0.0092   1.0000
   8.000   1.3649   0.01671   0.00996  -0.0942   0.0087   1.0000
   8.250   1.3837   0.01744   0.01076  -0.0929   0.0082   1.0000
   8.500   1.3987   0.01847   0.01187  -0.0910   0.0078   1.0000
   8.750   1.4040   0.02019   0.01373  -0.0877   0.0073   1.0000
   9.000   1.4243   0.02063   0.01420  -0.0867   0.0070   1.0000
   9.250   1.4383   0.02148   0.01511  -0.0847   0.0069   1.0000
   9.500   1.4475   0.02241   0.01612  -0.0820   0.0067   1.0000
   9.750   1.4543   0.02349   0.01726  -0.0790   0.0066   1.0000
  10.000   1.4601   0.02468   0.01852  -0.0761   0.0064   1.0000
  10.250   1.4645   0.02605   0.01997  -0.0734   0.0063   1.0000
  10.500   1.4687   0.02756   0.02157  -0.0710   0.0061   1.0000
  10.750   1.4723   0.02926   0.02335  -0.0690   0.0059   1.0000
  11.000   1.4754   0.03116   0.02532  -0.0672   0.0058   1.0000
  11.250   1.4786   0.03317   0.02739  -0.0657   0.0056   1.0000
  11.500   1.4810   0.03534   0.02963  -0.0644   0.0055   1.0000
  11.750   1.4829   0.03764   0.03200  -0.0632   0.0054   1.0000
  12.000   1.4843   0.04006   0.03448  -0.0621   0.0053   1.0000
  12.250   1.4846   0.04262   0.03709  -0.0609   0.0051   1.0000
  12.500   1.4855   0.04512   0.03965  -0.0595   0.0051   1.0000
  12.750   1.4880   0.04744   0.04200  -0.0577   0.0050   1.0000
  13.000   1.5049   0.04882   0.04332  -0.0539   0.0049   1.0000
  13.250   1.4997   0.05192   0.04662  -0.0534   0.0047   1.0000
  13.500   1.4978   0.05475   0.04959  -0.0533   0.0046   1.0000
  13.750   1.4991   0.05743   0.05238  -0.0527   0.0046   1.0000
  14.000   1.5025   0.06004   0.05510  -0.0514   0.0046   1.0000
  14.250   1.5036   0.06293   0.05810  -0.0505   0.0046   1.0000
  14.500   1.5332   0.06326   0.05835  -0.0479   0.0050   1.0000
  14.750   1.5246   0.06677   0.06203  -0.0481   0.0051   1.0000
  15.750   1.4575   0.08881   0.08510  -0.0520   0.0058   1.0000
  16.000   1.4469   0.09384   0.09027  -0.0536   0.0058   1.0000
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