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GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 178 AIRFOIL (goe178-il)
Reynolds number: 500,000
Max Cl/Cd: 104.53 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe178-il-500000.txt
Download as CSV file: xf-goe178-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3773   0.09436   0.09222  -0.0170   1.0000   0.0236
  -8.000  -0.3729   0.09070   0.08859  -0.0205   1.0000   0.0238
  -7.750  -0.3685   0.08705   0.08497  -0.0232   1.0000   0.0239
  -7.500  -0.3604   0.08280   0.08074  -0.0274   1.0000   0.0239
  -7.250  -0.3609   0.07630   0.07428  -0.0321   1.0000   0.0243
  -7.000  -0.3567   0.07353   0.07152  -0.0320   1.0000   0.0247
  -6.750  -0.3514   0.07135   0.06936  -0.0318   1.0000   0.0251
  -6.500  -0.3357   0.06856   0.06657  -0.0343   0.9982   0.0257
  -6.250  -0.3030   0.06412   0.06209  -0.0421   0.9943   0.0271
  -6.000  -0.2483   0.05601   0.05381  -0.0594   0.9880   0.0311
  -5.750  -0.2151   0.04540   0.04301  -0.0717   0.9829   0.0323
  -5.500  -0.1875   0.04339   0.04094  -0.0742   0.9746   0.0333
  -5.250  -0.1573   0.04068   0.03815  -0.0775   0.9652   0.0350
  -5.000  -0.1195   0.03169   0.02861  -0.0853   0.9545   0.0418
  -4.750  -0.0976   0.03106   0.02799  -0.0849   0.9392   0.0430
  -4.500  -0.0744   0.02971   0.02653  -0.0848   0.9205   0.0451
  -4.000  -0.0160   0.01800   0.01325  -0.0871   0.8762   0.0408
  -3.750   0.0093   0.01506   0.00986  -0.0868   0.8480   0.0384
  -3.500   0.0358   0.01358   0.00797  -0.0863   0.8201   0.0380
  -3.250   0.0628   0.01267   0.00674  -0.0859   0.7932   0.0381
  -3.000   0.0901   0.01205   0.00588  -0.0856   0.7645   0.0389
  -2.750   0.1176   0.01144   0.00502  -0.0853   0.7305   0.0391
  -2.500   0.1449   0.01102   0.00433  -0.0850   0.6887   0.0395
  -2.250   0.1722   0.01075   0.00380  -0.0847   0.6446   0.0398
  -2.000   0.1998   0.01056   0.00337  -0.0846   0.6069   0.0402
  -1.750   0.2277   0.01036   0.00299  -0.0846   0.5778   0.0405
  -1.500   0.2559   0.01012   0.00259  -0.0846   0.5558   0.0416
  -1.250   0.2843   0.00997   0.00233  -0.0846   0.5389   0.0437
  -1.000   0.3127   0.00990   0.00217  -0.0847   0.5252   0.0457
  -0.750   0.3411   0.00987   0.00205  -0.0847   0.5134   0.0486
  -0.500   0.3696   0.00981   0.00199  -0.0847   0.5030   0.0584
  -0.250   0.3980   0.00979   0.00199  -0.0848   0.4947   0.0801
   0.000   0.4264   0.00981   0.00198  -0.0848   0.4873   0.0939
   0.250   0.4547   0.00984   0.00199  -0.0848   0.4804   0.1045
   0.500   0.4830   0.00983   0.00199  -0.0849   0.4736   0.1176
   0.750   0.5113   0.00981   0.00202  -0.0850   0.4677   0.1446
   1.000   0.5398   0.00958   0.00208  -0.0853   0.4618   0.2508
   1.250   0.5664   0.00851   0.00227  -0.0857   0.4570   0.7178
   1.500   0.5894   0.00803   0.00227  -0.0842   0.4530   1.0000
   1.750   0.6179   0.00811   0.00231  -0.0842   0.4477   1.0000
   2.000   0.6460   0.00825   0.00237  -0.0842   0.4415   1.0000
   2.250   0.6743   0.00836   0.00243  -0.0842   0.4360   1.0000
   2.500   0.7025   0.00846   0.00250  -0.0843   0.4310   1.0000
   2.750   0.7305   0.00862   0.00259  -0.0843   0.4262   1.0000
   3.000   0.7587   0.00873   0.00270  -0.0843   0.4218   1.0000
   3.250   0.7869   0.00882   0.00280  -0.0843   0.4171   1.0000
   3.500   0.8148   0.00897   0.00290  -0.0843   0.4123   1.0000
   3.750   0.8427   0.00910   0.00303  -0.0843   0.4072   1.0000
   4.000   0.8708   0.00918   0.00313  -0.0844   0.4006   1.0000
   4.250   0.8984   0.00933   0.00325  -0.0843   0.3937   1.0000
   4.500   0.9265   0.00941   0.00336  -0.0843   0.3865   1.0000
   4.750   0.9541   0.00952   0.00346  -0.0843   0.3763   1.0000
   5.000   0.9816   0.00965   0.00357  -0.0843   0.3650   1.0000
   5.250   1.0093   0.00976   0.00369  -0.0843   0.3532   1.0000
   5.500   1.0365   0.00992   0.00383  -0.0842   0.3357   1.0000
   5.750   1.0631   0.01017   0.00399  -0.0841   0.3062   1.0000
   6.000   1.0883   0.01065   0.00427  -0.0839   0.2675   1.0000
   6.250   1.1129   0.01123   0.00467  -0.0836   0.2337   1.0000
   6.500   1.1370   0.01187   0.00516  -0.0832   0.2003   1.0000
   6.750   1.1514   0.01404   0.00652  -0.0820   0.0632   1.0000
   7.000   1.1749   0.01475   0.00719  -0.0814   0.0444   1.0000
   7.250   1.1980   0.01546   0.00779  -0.0808   0.0247   1.0000
   7.500   1.2211   0.01616   0.00851  -0.0801   0.0204   1.0000
   7.750   1.2443   0.01679   0.00923  -0.0795   0.0189   1.0000
   8.000   1.2663   0.01753   0.01006  -0.0787   0.0174   1.0000
   8.250   1.2864   0.01848   0.01109  -0.0777   0.0162   1.0000
   8.500   1.3025   0.01982   0.01258  -0.0762   0.0153   1.0000
   8.750   1.3198   0.02089   0.01376  -0.0748   0.0149   1.0000
   9.000   1.3368   0.02191   0.01489  -0.0734   0.0145   1.0000
   9.250   1.3515   0.02307   0.01616  -0.0717   0.0141   1.0000
   9.500   1.3642   0.02431   0.01749  -0.0698   0.0137   1.0000
   9.750   1.3755   0.02557   0.01884  -0.0678   0.0132   1.0000
  10.000   1.3842   0.02686   0.02020  -0.0655   0.0127   1.0000
  10.250   1.3884   0.02824   0.02166  -0.0626   0.0123   1.0000
  10.500   1.3907   0.02992   0.02343  -0.0599   0.0120   1.0000
  10.750   1.3921   0.03187   0.02545  -0.0575   0.0118   1.0000
  11.000   1.3931   0.03407   0.02772  -0.0553   0.0116   1.0000
  11.250   1.3951   0.03646   0.03019  -0.0533   0.0114   1.0000
  11.500   1.3998   0.03905   0.03286  -0.0511   0.0112   1.0000
  11.750   1.4103   0.04171   0.03562  -0.0491   0.0111   1.0000
  12.000   1.4159   0.04407   0.03813  -0.0477   0.0110   1.0000
  12.250   1.4184   0.04633   0.04056  -0.0465   0.0109   1.0000
  12.500   1.4209   0.04892   0.04332  -0.0455   0.0109   1.0000
  12.750   1.4225   0.05188   0.04648  -0.0444   0.0108   1.0000
  13.000   1.4232   0.05539   0.05017  -0.0431   0.0109   1.0000
  13.250   1.4351   0.05838   0.05325  -0.0416   0.0112   1.0000
  13.500   1.4307   0.06154   0.05659  -0.0413   0.0113   1.0000
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