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GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 401 AIRFOIL (goe401-il)
Reynolds number: 500,000
Max Cl/Cd: 100.77 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe401-il-500000-n5.txt
Download as CSV file: xf-goe401-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 401 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3436   0.10242   0.10007  -0.0190   1.0000   0.0136
  -9.000  -0.3403   0.09937   0.09704  -0.0198   1.0000   0.0140
  -8.750  -0.3439   0.09488   0.09257  -0.0215   1.0000   0.0150
  -8.500  -0.3394   0.09259   0.09031  -0.0217   1.0000   0.0151
  -8.250  -0.3331   0.09092   0.08866  -0.0215   1.0000   0.0155
  -8.000  -0.3288   0.08909   0.08686  -0.0213   1.0000   0.0160
  -7.750  -0.3309   0.08658   0.08439  -0.0210   1.0000   0.0160
  -7.500  -0.3239   0.08357   0.08140  -0.0233   0.9979   0.0163
  -7.250  -0.3054   0.07938   0.07721  -0.0289   0.9881   0.0167
  -7.000  -0.2909   0.07546   0.07328  -0.0334   0.9693   0.0171
  -6.500  -0.2123   0.06581   0.06350  -0.0536   0.9281   0.0200
  -6.250  -0.1556   0.05961   0.05713  -0.0683   0.9070   0.0205
  -6.000  -0.1183   0.05492   0.05222  -0.0770   0.8742   0.0208
  -5.750  -0.0960   0.05064   0.04772  -0.0816   0.8472   0.0221
  -5.500  -0.0753   0.04515   0.04198  -0.0859   0.8269   0.0229
  -5.250  -0.0574   0.04444   0.04121  -0.0854   0.8096   0.0235
  -5.000  -0.0377   0.04267   0.03932  -0.0859   0.7937   0.0239
  -4.750  -0.0162   0.03931   0.03577  -0.0873   0.7790   0.0238
  -4.500   0.0052   0.03744   0.03377  -0.0877   0.7641   0.0244
  -4.000   0.0507   0.03239   0.02833  -0.0887   0.7359   0.0254
  -3.750   0.0741   0.02948   0.02520  -0.0889   0.7236   0.0253
  -3.500   0.0975   0.02674   0.02221  -0.0887   0.7108   0.0253
  -3.250   0.1208   0.02386   0.01904  -0.0883   0.6982   0.0253
  -3.000   0.1439   0.02090   0.01575  -0.0875   0.6846   0.0258
  -2.750   0.1652   0.01650   0.01072  -0.0862   0.6720   0.0259
  -2.500   0.1890   0.01489   0.00874  -0.0853   0.6569   0.0261
  -2.250   0.2135   0.01394   0.00749  -0.0845   0.6399   0.0265
  -2.000   0.2383   0.01325   0.00655  -0.0837   0.6199   0.0267
  -1.750   0.2633   0.01272   0.00579  -0.0829   0.5979   0.0270
  -1.500   0.2881   0.01232   0.00518  -0.0822   0.5741   0.0272
  -1.000   0.3377   0.01185   0.00431  -0.0806   0.5186   0.0277
  -0.750   0.3628   0.01177   0.00407  -0.0799   0.4947   0.0280
  -0.500   0.3877   0.01146   0.00361  -0.0792   0.4752   0.0283
  -0.250   0.4127   0.01116   0.00320  -0.0785   0.4600   0.0286
   0.000   0.4378   0.01090   0.00287  -0.0779   0.4481   0.0289
   0.250   0.4629   0.01073   0.00263  -0.0772   0.4374   0.0293
   0.500   0.4884   0.01058   0.00246  -0.0766   0.4284   0.0298
   0.750   0.5139   0.01050   0.00234  -0.0760   0.4204   0.0304
   1.000   0.5397   0.01043   0.00225  -0.0755   0.4131   0.0311
   1.500   0.5915   0.01037   0.00215  -0.0744   0.4006   0.0326
   1.750   0.6174   0.01037   0.00213  -0.0739   0.3943   0.0333
   2.000   0.6433   0.01039   0.00213  -0.0734   0.3888   0.0344
   2.250   0.6695   0.01040   0.00214  -0.0730   0.3828   0.0357
   2.500   0.6953   0.01044   0.00215  -0.0725   0.3769   0.0379
   2.750   0.7214   0.01046   0.00219  -0.0720   0.3718   0.0412
   3.000   0.7471   0.01042   0.00228  -0.0715   0.3661   0.0857
   3.250   0.7725   0.01048   0.00239  -0.0710   0.3599   0.1232
   3.500   0.7986   0.01051   0.00250  -0.0706   0.3545   0.1524
   3.750   0.8242   0.01053   0.00263  -0.0701   0.3490   0.1949
   4.250   0.9141   0.00941   0.00303  -0.0785   0.3243   1.0000
   4.500   0.9388   0.00958   0.00316  -0.0778   0.3154   1.0000
   4.750   0.9636   0.00973   0.00329  -0.0771   0.3083   1.0000
   5.000   0.9880   0.00992   0.00345  -0.0764   0.2999   1.0000
   5.250   1.0126   0.01009   0.00361  -0.0757   0.2917   1.0000
   5.500   1.0366   0.01030   0.00378  -0.0750   0.2814   1.0000
   5.750   1.0603   0.01054   0.00397  -0.0742   0.2696   1.0000
   6.000   1.0843   0.01076   0.00419  -0.0734   0.2592   1.0000
   6.250   1.1078   0.01101   0.00441  -0.0726   0.2492   1.0000
   6.500   1.1308   0.01130   0.00466  -0.0717   0.2360   1.0000
   6.750   1.1530   0.01167   0.00496  -0.0707   0.2179   1.0000
   7.000   1.1752   0.01202   0.00526  -0.0698   0.2028   1.0000
   7.250   1.1966   0.01245   0.00561  -0.0687   0.1840   1.0000
   7.500   1.2167   0.01299   0.00601  -0.0675   0.1586   1.0000
   7.750   1.2346   0.01372   0.00656  -0.0659   0.1239   1.0000
   8.000   1.2448   0.01513   0.00758  -0.0633   0.0628   1.0000
   8.250   1.2646   0.01565   0.00810  -0.0620   0.0555   1.0000
   8.500   1.2849   0.01611   0.00858  -0.0608   0.0497   1.0000
   8.750   1.3048   0.01659   0.00909  -0.0596   0.0445   1.0000
   9.000   1.3241   0.01710   0.00962  -0.0583   0.0392   1.0000
   9.250   1.3420   0.01768   0.01019  -0.0568   0.0305   1.0000
   9.750   1.3728   0.01915   0.01158  -0.0531   0.0169   1.0000
  10.000   1.3881   0.01982   0.01231  -0.0513   0.0151   1.0000
  10.250   1.4032   0.02046   0.01302  -0.0494   0.0141   1.0000
  10.500   1.4154   0.02115   0.01378  -0.0471   0.0132   1.0000
  10.750   1.4245   0.02193   0.01462  -0.0442   0.0124   1.0000
  11.000   1.4314   0.02285   0.01562  -0.0412   0.0116   1.0000
  11.250   1.4404   0.02369   0.01654  -0.0388   0.0112   1.0000
  11.500   1.4491   0.02457   0.01752  -0.0364   0.0107   1.0000
  11.750   1.4563   0.02561   0.01865  -0.0341   0.0102   1.0000
  12.000   1.4619   0.02682   0.01995  -0.0319   0.0098   1.0000
  12.250   1.4664   0.02820   0.02142  -0.0300   0.0095   1.0000
  12.500   1.4696   0.02980   0.02312  -0.0282   0.0092   1.0000
  12.750   1.4707   0.03173   0.02514  -0.0267   0.0090   1.0000
  13.000   1.4694   0.03406   0.02758  -0.0256   0.0087   1.0000
  13.250   1.4640   0.03700   0.03065  -0.0247   0.0085   1.0000
  13.500   1.4619   0.03982   0.03359  -0.0244   0.0083   1.0000
  13.750   1.4604   0.04272   0.03661  -0.0243   0.0082   1.0000
  14.000   1.4581   0.04587   0.03988  -0.0245   0.0080   1.0000
  14.250   1.4532   0.04947   0.04361  -0.0249   0.0079   1.0000
  14.500   1.4460   0.05353   0.04779  -0.0257   0.0078   1.0000
  14.750   1.4405   0.05748   0.05186  -0.0266   0.0077   1.0000
  15.000   1.4325   0.06188   0.05639  -0.0277   0.0076   1.0000
  15.250   1.4254   0.06625   0.06087  -0.0289   0.0074   1.0000
  15.500   1.4165   0.07095   0.06568  -0.0302   0.0073   1.0000
  15.750   1.4087   0.07555   0.07038  -0.0316   0.0072   1.0000
  16.000   1.3981   0.08062   0.07557  -0.0332   0.0072   1.0000
  16.250   1.3882   0.08563   0.08068  -0.0348   0.0070   1.0000
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