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GOE 55 AIRFOIL (goe55-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 55 AIRFOIL (goe55-il)
Reynolds number: 1,000,000
Max Cl/Cd: 72.7 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe55-il-1000000.txt
Download as CSV file: xf-goe55-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 55 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5534   0.10363   0.10207   0.0281   1.0000   0.0211
  -9.250  -0.5546   0.09885   0.09729   0.0266   1.0000   0.0212
  -8.750  -0.6718   0.10125   0.09962   0.0369   1.0000   0.0211
  -8.500  -0.6714   0.09659   0.09498   0.0342   1.0000   0.0212
  -8.250  -0.6710   0.09161   0.09000   0.0306   1.0000   0.0212
  -8.000  -0.6703   0.08552   0.08392   0.0257   1.0000   0.0216
  -7.750  -0.6576   0.08267   0.08107   0.0233   1.0000   0.0218
  -7.500  -0.6435   0.07968   0.07808   0.0206   1.0000   0.0221
  -7.250  -0.6280   0.07622   0.07461   0.0169   1.0000   0.0225
  -7.000  -0.6108   0.07213   0.07049   0.0122   1.0000   0.0232
  -6.750  -0.5804   0.05961   0.05778  -0.0037   1.0000   0.0255
  -6.250  -0.5415   0.01964   0.01566  -0.0258   1.0000   0.0261
  -6.000  -0.5141   0.01883   0.01480  -0.0260   1.0000   0.0266
  -5.750  -0.4865   0.01850   0.01446  -0.0260   1.0000   0.0270
  -5.500  -0.4585   0.01772   0.01361  -0.0261   1.0000   0.0275
  -5.250  -0.4301   0.01609   0.01174  -0.0264   1.0000   0.0279
  -5.000  -0.4014   0.01486   0.01033  -0.0266   1.0000   0.0283
  -4.750  -0.3727   0.01386   0.00918  -0.0267   1.0000   0.0289
  -4.500  -0.3439   0.01307   0.00827  -0.0268   1.0000   0.0294
  -4.250  -0.3152   0.01257   0.00769  -0.0267   1.0000   0.0300
  -4.000  -0.2864   0.01199   0.00703  -0.0267   1.0000   0.0303
  -3.750  -0.2576   0.01156   0.00654  -0.0267   1.0000   0.0306
  -3.500  -0.2287   0.01081   0.00571  -0.0267   1.0000   0.0309
  -3.250  -0.1983   0.00983   0.00463  -0.0271   0.9374   0.0316
  -3.000  -0.1788   0.01036   0.00425  -0.0248   0.6664   0.0321
  -2.750  -0.1503   0.01059   0.00390  -0.0250   0.4850   0.0328
  -2.500  -0.1215   0.01057   0.00364  -0.0251   0.4170   0.0335
  -2.250  -0.0928   0.01047   0.00343  -0.0251   0.3884   0.0345
  -2.000  -0.0639   0.01031   0.00319  -0.0251   0.3721   0.0352
  -1.750  -0.0350   0.01015   0.00297  -0.0251   0.3613   0.0359
  -1.500  -0.0061   0.01002   0.00279  -0.0250   0.3524   0.0365
  -1.250   0.0228   0.00989   0.00263  -0.0250   0.3463   0.0370
  -1.000   0.0520   0.00961   0.00229  -0.0251   0.3392   0.0390
  -0.750   0.0809   0.00951   0.00218  -0.0250   0.3328   0.0408
  -0.500   0.1098   0.00943   0.00209  -0.0250   0.3274   0.0429
  -0.250   0.1386   0.00940   0.00202  -0.0249   0.3213   0.0450
   0.000   0.1676   0.00927   0.00191  -0.0249   0.3167   0.0511
   0.250   0.1966   0.00917   0.00185  -0.0248   0.3113   0.0643
   0.500   0.2254   0.00913   0.00188  -0.0249   0.3039   0.0956
   0.750   0.2542   0.00907   0.00187  -0.0248   0.2999   0.1078
   1.000   0.2829   0.00904   0.00185  -0.0247   0.2943   0.1196
   1.250   0.3119   0.00893   0.00187  -0.0248   0.2880   0.1744
   1.500   0.3414   0.00832   0.00193  -0.0254   0.2826   0.4226
   1.750   0.3633   0.00676   0.00187  -0.0240   0.2765   1.0000
   2.000   0.3920   0.00683   0.00190  -0.0239   0.2701   1.0000
   2.250   0.4208   0.00691   0.00193  -0.0238   0.2620   1.0000
   2.500   0.4495   0.00699   0.00197  -0.0237   0.2528   1.0000
   2.750   0.4781   0.00710   0.00201  -0.0236   0.2387   1.0000
   3.000   0.5066   0.00735   0.00207  -0.0236   0.1996   1.0000
   3.250   0.5349   0.00781   0.00227  -0.0237   0.1473   1.0000
   3.500   0.5633   0.00814   0.00245  -0.0238   0.1213   1.0000
   3.750   0.5916   0.00851   0.00266  -0.0238   0.0921   1.0000
   4.000   0.6198   0.00917   0.00303  -0.0239   0.0418   1.0000
   4.250   0.6482   0.00945   0.00328  -0.0239   0.0374   1.0000
   4.500   0.6766   0.00966   0.00351  -0.0238   0.0364   1.0000
   4.750   0.7050   0.00991   0.00377  -0.0237   0.0354   1.0000
   5.000   0.7332   0.01018   0.00405  -0.0236   0.0342   1.0000
   5.250   0.7614   0.01049   0.00437  -0.0236   0.0331   1.0000
   5.500   0.7895   0.01086   0.00476  -0.0235   0.0320   1.0000
   5.750   0.8174   0.01135   0.00531  -0.0234   0.0310   1.0000
   6.000   0.8452   0.01181   0.00581  -0.0234   0.0305   1.0000
   6.250   0.8730   0.01215   0.00619  -0.0233   0.0302   1.0000
   6.500   0.9006   0.01254   0.00661  -0.0232   0.0299   1.0000
   6.750   0.9282   0.01293   0.00703  -0.0231   0.0294   1.0000
   7.000   0.9555   0.01335   0.00749  -0.0230   0.0288   1.0000
   7.250   0.9827   0.01382   0.00801  -0.0228   0.0284   1.0000
   7.500   1.0096   0.01432   0.00855  -0.0227   0.0279   1.0000
   7.750   1.0364   0.01485   0.00912  -0.0226   0.0274   1.0000
   8.000   1.0628   0.01543   0.00974  -0.0224   0.0269   1.0000
   8.250   1.0890   0.01605   0.01039  -0.0223   0.0263   1.0000
   8.500   1.1139   0.01701   0.01139  -0.0221   0.0256   1.0000
   8.750   1.1359   0.01893   0.01342  -0.0216   0.0248   1.0000
   9.000   1.1621   0.01931   0.01386  -0.0214   0.0246   1.0000
   9.250   1.1880   0.01976   0.01437  -0.0212   0.0243   1.0000
   9.500   1.2136   0.02022   0.01490  -0.0209   0.0238   1.0000
   9.750   1.2384   0.02087   0.01563  -0.0206   0.0233   1.0000
  10.000   1.2628   0.02160   0.01643  -0.0203   0.0229   1.0000
  10.250   1.2869   0.02231   0.01721  -0.0200   0.0224   1.0000
  10.500   1.3110   0.02293   0.01788  -0.0197   0.0219   1.0000
  10.750   1.3349   0.02352   0.01852  -0.0194   0.0214   1.0000
  11.000   1.3574   0.02436   0.01940  -0.0190   0.0209   1.0000
  11.250   1.3738   0.02653   0.02167  -0.0183   0.0203   1.0000
  11.500   1.3928   0.02799   0.02328  -0.0177   0.0199   1.0000
  11.750   1.4153   0.02854   0.02394  -0.0173   0.0197   1.0000
  12.000   1.4369   0.02920   0.02470  -0.0168   0.0193   1.0000
  12.250   1.4575   0.03000   0.02560  -0.0163   0.0188   1.0000
  12.500   1.4770   0.03088   0.02658  -0.0158   0.0184   1.0000
  12.750   1.4955   0.03184   0.02764  -0.0152   0.0180   1.0000
  13.000   1.5135   0.03277   0.02864  -0.0147   0.0176   1.0000
  13.250   1.5309   0.03368   0.02963  -0.0141   0.0173   1.0000
  13.500   1.5469   0.03470   0.03070  -0.0135   0.0171   1.0000
  13.750   1.5594   0.03603   0.03209  -0.0128   0.0168   1.0000
  14.000   1.5602   0.03841   0.03459  -0.0116   0.0165   1.0000
  14.500   1.5203   0.05011   0.04673  -0.0173   0.0162   1.0000
  14.750   1.5152   0.05683   0.05363  -0.0240   0.0161   1.0000
  15.000   1.5010   0.06434   0.06129  -0.0296   0.0161   1.0000
  15.250   1.4813   0.07200   0.06908  -0.0345   0.0160   1.0000
  15.500   1.4570   0.08004   0.07724  -0.0392   0.0160   1.0000
  15.750   1.4315   0.08815   0.08548  -0.0436   0.0160   1.0000
  16.000   1.4056   0.09643   0.09387  -0.0481   0.0160   1.0000
  16.250   1.3778   0.10519   0.10274  -0.0528   0.0160   1.0000
  16.500   1.3532   0.11421   0.11189  -0.0579   0.0159   1.0000
  16.750   1.3247   0.12444   0.12225  -0.0636   0.0159   1.0000
  17.000   1.2916   0.13634   0.13430  -0.0704   0.0159   1.0000
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