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GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 178 AIRFOIL (goe178-il)
Reynolds number: 500,000
Max Cl/Cd: 98.49 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe178-il-500000-n5.txt
Download as CSV file: xf-goe178-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 178 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  -0.4131   0.10080   0.09862  -0.0107   1.0000   0.0094
  -9.000  -0.4141   0.09549   0.09333  -0.0133   1.0000   0.0098
  -8.750  -0.4164   0.09006   0.08792  -0.0163   1.0000   0.0103
  -8.500  -0.4083   0.08753   0.08541  -0.0179   1.0000   0.0105
  -8.250  -0.4005   0.08501   0.08291  -0.0196   1.0000   0.0108
  -8.000  -0.3946   0.08221   0.08014  -0.0213   1.0000   0.0112
  -7.750  -0.3854   0.07819   0.07613  -0.0256   0.9898   0.0117
  -7.250  -0.3542   0.05704   0.05488  -0.0549   0.9602   0.0141
  -7.000  -0.3300   0.02242   0.01870  -0.0873   0.9477   0.0187
  -6.750  -0.3049   0.02073   0.01678  -0.0879   0.9361   0.0194
  -6.500  -0.2792   0.02037   0.01638  -0.0878   0.9217   0.0199
  -6.250  -0.2538   0.02007   0.01598  -0.0874   0.9011   0.0206
  -6.000  -0.2295   0.01944   0.01516  -0.0869   0.8717   0.0215
  -5.750  -0.2049   0.01836   0.01374  -0.0865   0.8414   0.0224
  -5.500  -0.1792   0.01741   0.01244  -0.0863   0.8152   0.0234
  -5.250  -0.1525   0.01667   0.01139  -0.0862   0.7916   0.0244
  -5.000  -0.1253   0.01598   0.01040  -0.0861   0.7685   0.0249
  -4.750  -0.0978   0.01551   0.00967  -0.0861   0.7437   0.0254
  -4.500  -0.0705   0.01459   0.00842  -0.0862   0.7157   0.0261
  -4.250  -0.0432   0.01351   0.00702  -0.0863   0.6834   0.0268
  -4.000  -0.0157   0.01294   0.00619  -0.0863   0.6489   0.0272
  -3.750   0.0120   0.01251   0.00552  -0.0863   0.6170   0.0276
  -3.500   0.0398   0.01216   0.00497  -0.0863   0.5893   0.0280
  -3.250   0.0678   0.01186   0.00448  -0.0863   0.5648   0.0283
  -3.000   0.0959   0.01160   0.00408  -0.0864   0.5435   0.0289
  -2.750   0.1241   0.01137   0.00372  -0.0865   0.5256   0.0295
  -2.500   0.1524   0.01114   0.00337  -0.0865   0.5113   0.0298
  -2.250   0.1808   0.01092   0.00306  -0.0866   0.4999   0.0301
  -2.000   0.2093   0.01075   0.00279  -0.0867   0.4901   0.0306
  -1.750   0.2378   0.01059   0.00256  -0.0868   0.4815   0.0311
  -1.500   0.2663   0.01048   0.00237  -0.0868   0.4743   0.0318
  -1.250   0.2948   0.01037   0.00221  -0.0869   0.4673   0.0325
  -1.000   0.3232   0.01032   0.00208  -0.0870   0.4604   0.0332
  -0.750   0.3517   0.01026   0.00197  -0.0870   0.4534   0.0338
  -0.500   0.3801   0.01025   0.00188  -0.0871   0.4468   0.0343
  -0.250   0.4086   0.01022   0.00182  -0.0872   0.4417   0.0351
   0.000   0.4370   0.01019   0.00177  -0.0872   0.4369   0.0366
   0.250   0.4654   0.01019   0.00174  -0.0873   0.4319   0.0405
   0.500   0.4938   0.01011   0.00176  -0.0874   0.4269   0.0640
   0.750   0.5222   0.01012   0.00178  -0.0874   0.4218   0.0754
   1.000   0.5504   0.01017   0.00181  -0.0875   0.4173   0.0819
   1.250   0.5786   0.01018   0.00184  -0.0876   0.4130   0.0894
   1.500   0.6070   0.01018   0.00188  -0.0876   0.4091   0.1002
   1.750   0.6352   0.01020   0.00193  -0.0877   0.4048   0.1139
   2.000   0.6634   0.01012   0.00203  -0.0879   0.3992   0.1912
   2.250   0.6919   0.00980   0.00215  -0.0883   0.3930   0.3718
   3.250   0.7977   0.00884   0.00252  -0.0871   0.3695   1.0000
   3.500   0.8258   0.00893   0.00262  -0.0872   0.3636   1.0000
   3.750   0.8536   0.00907   0.00273  -0.0872   0.3568   1.0000
   4.000   0.8815   0.00919   0.00284  -0.0872   0.3489   1.0000
   4.250   0.9092   0.00934   0.00296  -0.0872   0.3386   1.0000
   4.500   0.9366   0.00951   0.00310  -0.0872   0.3237   1.0000
   4.750   0.9624   0.00995   0.00329  -0.0870   0.2780   1.0000
   5.000   0.9871   0.01057   0.00366  -0.0868   0.2341   1.0000
   5.250   1.0127   0.01104   0.00401  -0.0866   0.2101   1.0000
   5.500   1.0379   0.01155   0.00437  -0.0864   0.1801   1.0000
   5.750   1.0562   0.01322   0.00542  -0.0855   0.0620   1.0000
   6.000   1.0818   0.01362   0.00580  -0.0852   0.0527   1.0000
   6.250   1.1072   0.01402   0.00622  -0.0850   0.0441   1.0000
   6.500   1.1323   0.01446   0.00663  -0.0847   0.0266   1.0000
   6.750   1.1558   0.01513   0.00721  -0.0842   0.0159   1.0000
   7.000   1.1803   0.01562   0.00776  -0.0837   0.0130   1.0000
   7.250   1.2048   0.01608   0.00830  -0.0833   0.0121   1.0000
   7.500   1.2286   0.01660   0.00890  -0.0828   0.0111   1.0000
   7.750   1.2517   0.01719   0.00957  -0.0822   0.0102   1.0000
   8.000   1.2732   0.01796   0.01041  -0.0814   0.0093   1.0000
   8.250   1.2941   0.01874   0.01128  -0.0805   0.0086   1.0000
   8.500   1.3157   0.01939   0.01202  -0.0798   0.0081   1.0000
   8.750   1.3358   0.02015   0.01287  -0.0788   0.0077   1.0000
   9.000   1.3548   0.02099   0.01379  -0.0778   0.0073   1.0000
   9.250   1.3726   0.02188   0.01476  -0.0766   0.0069   1.0000
   9.500   1.3889   0.02283   0.01579  -0.0752   0.0066   1.0000
   9.750   1.4028   0.02393   0.01696  -0.0735   0.0064   1.0000
  10.000   1.4111   0.02537   0.01849  -0.0713   0.0061   1.0000
  10.250   1.4147   0.02685   0.02008  -0.0683   0.0059   1.0000
  10.500   1.4221   0.02800   0.02136  -0.0659   0.0058   1.0000
  10.750   1.4279   0.02937   0.02283  -0.0637   0.0056   1.0000
  11.000   1.4326   0.03096   0.02453  -0.0618   0.0054   1.0000
  11.250   1.4356   0.03284   0.02653  -0.0601   0.0052   1.0000
  11.500   1.4372   0.03508   0.02889  -0.0589   0.0051   1.0000
  11.750   1.4380   0.03762   0.03155  -0.0582   0.0049   1.0000
  12.000   1.4383   0.04040   0.03445  -0.0577   0.0048   1.0000
  12.250   1.4386   0.04335   0.03751  -0.0576   0.0047   1.0000
  12.500   1.4381   0.04650   0.04078  -0.0577   0.0046   1.0000
  12.750   1.4369   0.04984   0.04423  -0.0579   0.0046   1.0000
  13.000   1.4358   0.05325   0.04774  -0.0583   0.0045   1.0000
  13.250   1.4337   0.05680   0.05142  -0.0588   0.0044   1.0000
  13.500   1.4308   0.06048   0.05521  -0.0593   0.0044   1.0000
  13.750   1.4276   0.06422   0.05904  -0.0599   0.0043   1.0000
  14.000   1.4233   0.06809   0.06302  -0.0605   0.0043   1.0000
  14.250   1.4185   0.07207   0.06710  -0.0611   0.0042   1.0000
  14.500   1.4130   0.07617   0.07130  -0.0618   0.0041   1.0000
  14.750   1.4068   0.08042   0.07566  -0.0625   0.0041   1.0000
  15.000   1.3992   0.08490   0.08027  -0.0633   0.0040   1.0000
  15.250   1.3909   0.08955   0.08503  -0.0640   0.0040   1.0000
  15.500   1.3848   0.09418   0.08981  -0.0653   0.0040   1.0000
  15.750   1.3778   0.09901   0.09479  -0.0667   0.0039   1.0000
  16.000   1.3701   0.10411   0.10004  -0.0684   0.0039   1.0000
  16.250   1.3614   0.10946   0.10555  -0.0702   0.0039   1.0000
  16.500   1.3522   0.11505   0.11128  -0.0724   0.0038   1.0000
  16.750   1.3422   0.12094   0.11733  -0.0748   0.0038   1.0000
  17.000   1.3314   0.12718   0.12374  -0.0776   0.0038   1.0000
  17.250   1.3201   0.13368   0.13039  -0.0807   0.0038   1.0000
  17.500   1.3080   0.14062   0.13750  -0.0842   0.0038   1.0000
  17.750   1.2960   0.14781   0.14483  -0.0881   0.0038   1.0000
  18.000   1.2837   0.15539   0.15256  -0.0924   0.0038   1.0000
  18.250   1.2706   0.16352   0.16085  -0.0973   0.0038   1.0000
  18.500   1.2571   0.17207   0.16954  -0.1025   0.0038   1.0000
  18.750   1.2432   0.18118   0.17880  -0.1082   0.0038   1.0000
  19.000   1.2280   0.19136   0.18911  -0.1147   0.0038   1.0000
  19.250   1.2106   0.20334   0.20122  -0.1222   0.0039   1.0000
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