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GOE 406 AIRFOIL (goe406-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 406 AIRFOIL (goe406-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.24 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe406-il-1000000.txt
Download as CSV file: xf-goe406-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 406 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1786   0.10801   0.10626  -0.0636   0.9873   0.0192
 -10.500  -0.1699   0.10337   0.10160  -0.0692   0.9856   0.0193
 -10.250  -0.1579   0.09882   0.09705  -0.0745   0.9842   0.0194
 -10.000  -0.1407   0.09472   0.09295  -0.0768   0.9833   0.0195
  -9.750  -0.1326   0.09207   0.09031  -0.0773   0.9780   0.0196
  -9.500  -0.1160   0.08929   0.08753  -0.0796   0.9749   0.0198
  -9.250  -0.0970   0.08563   0.08387  -0.0841   0.9714   0.0199
  -9.000  -0.0884   0.08336   0.08160  -0.0847   0.9613   0.0202
  -8.750  -0.0726   0.07998   0.07821  -0.0885   0.9519   0.0204
  -8.500  -0.0463   0.07602   0.07421  -0.0953   0.9352   0.0208
  -8.250   0.0028   0.07036   0.06839  -0.1092   0.8957   0.0217
  -8.000   0.0389   0.06176   0.05931  -0.1310   0.8235   0.0228
  -7.750   0.0655   0.04490   0.04232  -0.1230   0.7721   0.0231
  -7.500   0.0564   0.04256   0.03994  -0.1220   0.7627   0.0231
  -7.250   0.0366   0.05328   0.05054  -0.1306   0.7752   0.0231
  -7.000   0.0422   0.05125   0.04843  -0.1299   0.7658   0.0232
  -6.750   0.0487   0.04915   0.04628  -0.1292   0.7570   0.0233
  -6.500   0.0573   0.04749   0.04455  -0.1281   0.7488   0.0234
  -6.250   0.0662   0.04552   0.04253  -0.1272   0.7416   0.0236
  -6.000   0.0754   0.04350   0.04044  -0.1262   0.7347   0.0238
  -5.750   0.0854   0.04152   0.03836  -0.1250   0.7279   0.0241
  -5.500   0.0961   0.03937   0.03614  -0.1238   0.7218   0.0245
  -5.250   0.1071   0.03721   0.03387  -0.1222   0.7152   0.0253
  -5.000   0.1151   0.03205   0.02832  -0.1187   0.7101   0.0267
  -4.750   0.1171   0.02896   0.02511  -0.1155   0.7043   0.0271
  -4.500   0.1309   0.02765   0.02370  -0.1135   0.6979   0.0272
  -4.250   0.1468   0.02665   0.02262  -0.1117   0.6913   0.0275
  -4.000   0.1628   0.02551   0.02140  -0.1098   0.6848   0.0277
  -3.750   0.1787   0.02433   0.02009  -0.1077   0.6794   0.0281
  -3.500   0.1955   0.02307   0.01871  -0.1057   0.6744   0.0287
  -3.250   0.2113   0.02096   0.01618  -0.1018   0.6695   0.0310
  -3.000   0.2179   0.01813   0.01309  -0.0978   0.6647   0.0316
  -2.750   0.2380   0.01751   0.01242  -0.0964   0.6596   0.0319
  -2.500   0.2587   0.01687   0.01174  -0.0950   0.6544   0.0324
  -2.250   0.2788   0.01623   0.01101  -0.0934   0.6483   0.0329
  -2.000   0.2989   0.01551   0.01015  -0.0916   0.6428   0.0341
  -1.750   0.3224   0.01564   0.00999  -0.0897   0.6370   0.0361
  -1.500   0.3395   0.01369   0.00799  -0.0879   0.6314   0.0377
  -1.250   0.3619   0.01327   0.00751  -0.0867   0.6256   0.0386
  -1.000   0.3869   0.01141   0.00515  -0.0848   0.6198   0.0313
  -0.750   0.4115   0.01080   0.00450  -0.0840   0.6122   0.0305
  -0.500   0.4368   0.01029   0.00394  -0.0833   0.6058   0.0302
  -0.250   0.4605   0.01012   0.00370  -0.0823   0.5971   0.0307
   0.000   0.4845   0.00988   0.00342  -0.0813   0.5893   0.0308
   0.250   0.5077   0.00962   0.00311  -0.0802   0.5802   0.0309
   0.500   0.5309   0.00946   0.00292  -0.0791   0.5707   0.0310
   0.750   0.5513   0.00914   0.00255  -0.0773   0.5598   0.0316
   1.000   0.5725   0.00900   0.00238  -0.0758   0.5467   0.0322
   1.250   0.5930   0.00896   0.00229  -0.0742   0.5307   0.0328
   1.500   0.6123   0.00898   0.00222  -0.0722   0.5108   0.0333
   1.750   0.6313   0.00903   0.00219  -0.0703   0.4882   0.0340
   2.000   0.6473   0.00916   0.00220  -0.0677   0.4611   0.0348
   2.250   0.6633   0.00932   0.00224  -0.0652   0.4338   0.0352
   2.500   0.6796   0.00948   0.00229  -0.0627   0.4101   0.0364
   2.750   0.6969   0.00961   0.00232  -0.0604   0.3902   0.0382
   3.000   0.7151   0.00975   0.00239  -0.0584   0.3746   0.0401
   3.250   0.7338   0.00989   0.00248  -0.0564   0.3623   0.0427
   3.500   0.7536   0.00995   0.00261  -0.0547   0.3528   0.0821
   3.750   1.0673   0.00956   0.00397  -0.1209   0.3249   1.0000
   4.000   1.0891   0.00973   0.00411  -0.1197   0.3201   1.0000
   4.250   1.1098   0.00994   0.00427  -0.1183   0.3148   1.0000
   4.500   1.1326   0.01006   0.00439  -0.1173   0.3121   1.0000
   4.750   1.1548   0.01019   0.00453  -0.1162   0.3088   1.0000
   5.000   1.1763   0.01036   0.00468  -0.1149   0.3055   1.0000
   5.250   1.1965   0.01057   0.00486  -0.1134   0.3009   1.0000
   5.500   1.2170   0.01076   0.00504  -0.1120   0.2970   1.0000
   5.750   1.2393   0.01087   0.00517  -0.1109   0.2932   1.0000
   6.000   1.2601   0.01103   0.00532  -0.1096   0.2896   1.0000
   6.250   1.2797   0.01123   0.00551  -0.1080   0.2859   1.0000
   6.500   1.2979   0.01147   0.00573  -0.1062   0.2812   1.0000
   6.750   1.3192   0.01159   0.00589  -0.1049   0.2792   1.0000
   7.000   1.3386   0.01173   0.00605  -0.1033   0.2763   1.0000
   7.250   1.3553   0.01190   0.00622  -0.1011   0.2724   1.0000
   7.500   1.3699   0.01211   0.00643  -0.0986   0.2684   1.0000
   7.750   1.3864   0.01229   0.00662  -0.0964   0.2643   1.0000
   8.000   1.4045   0.01243   0.00679  -0.0945   0.2615   1.0000
   8.250   1.4212   0.01262   0.00699  -0.0925   0.2578   1.0000
   8.500   1.4363   0.01287   0.00724  -0.0901   0.2529   1.0000
   8.750   1.4530   0.01309   0.00748  -0.0881   0.2486   1.0000
   9.000   1.4705   0.01329   0.00770  -0.0863   0.2439   1.0000
   9.250   1.4855   0.01358   0.00798  -0.0841   0.2383   1.0000
   9.500   1.5016   0.01385   0.00827  -0.0820   0.2327   1.0000
   9.750   1.5153   0.01421   0.00860  -0.0796   0.2228   1.0000
  10.000   1.5284   0.01463   0.00898  -0.0772   0.2104   1.0000
  10.250   1.5357   0.01529   0.00954  -0.0739   0.1904   1.0000
  10.500   1.5288   0.01664   0.01062  -0.0684   0.1474   1.0000
  10.750   1.5159   0.01841   0.01213  -0.0623   0.1090   1.0000
  11.000   1.5085   0.02006   0.01360  -0.0574   0.0788   1.0000
  11.250   1.4959   0.02214   0.01548  -0.0523   0.0471   1.0000
  11.500   1.4996   0.02339   0.01673  -0.0495   0.0402   1.0000
  11.750   1.5055   0.02457   0.01792  -0.0472   0.0365   1.0000
  12.000   1.5127   0.02572   0.01910  -0.0452   0.0342   1.0000
  12.250   1.5176   0.02710   0.02052  -0.0431   0.0322   1.0000
  12.500   1.5245   0.02837   0.02185  -0.0414   0.0307   1.0000
  12.750   1.5318   0.02966   0.02320  -0.0398   0.0295   1.0000
  13.000   1.5372   0.03114   0.02471  -0.0381   0.0282   1.0000
  13.250   1.5400   0.03289   0.02651  -0.0364   0.0271   1.0000
  13.500   1.5428   0.03468   0.02837  -0.0349   0.0260   1.0000
  13.750   1.5483   0.03628   0.03004  -0.0336   0.0255   1.0000
  14.000   1.5530   0.03801   0.03183  -0.0323   0.0247   1.0000
  14.250   1.5565   0.03989   0.03376  -0.0312   0.0237   1.0000
  14.500   1.5575   0.04205   0.03599  -0.0300   0.0232   1.0000
  14.750   1.5523   0.04489   0.03890  -0.0287   0.0222   1.0000
  15.000   1.5495   0.04760   0.04169  -0.0278   0.0218   1.0000
  15.250   1.5525   0.04977   0.04393  -0.0271   0.0213   1.0000
  15.500   1.5533   0.05221   0.04645  -0.0264   0.0207   1.0000
  15.750   1.5512   0.05505   0.04937  -0.0258   0.0202   1.0000
  16.000   1.5499   0.05787   0.05226  -0.0254   0.0197   1.0000
  16.250   1.5441   0.06134   0.05582  -0.0251   0.0195   1.0000
  16.500   1.5378   0.06492   0.05949  -0.0250   0.0191   1.0000
  16.750   1.5284   0.06902   0.06367  -0.0250   0.0188   1.0000
  17.000   1.5133   0.07403   0.06879  -0.0254   0.0183   1.0000
  17.250   1.4986   0.07912   0.07399  -0.0260   0.0181   1.0000
  17.500   1.4930   0.08299   0.07795  -0.0264   0.0178   1.0000
  17.750   1.4854   0.08720   0.08225  -0.0270   0.0176   1.0000
  18.000   1.4754   0.09184   0.08700  -0.0278   0.0174   1.0000
  18.250   1.4668   0.09632   0.09157  -0.0287   0.0171   1.0000
  18.500   1.4555   0.10121   0.09655  -0.0297   0.0168   1.0000
  18.750   1.4460   0.10588   0.10131  -0.0308   0.0167   1.0000
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