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GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 178 AIRFOIL (goe178-il)
Reynolds number: 50,000
Max Cl/Cd: 37.82 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe178-il-50000.txt
Download as CSV file: xf-goe178-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3674   0.10221   0.09582  -0.0166   1.0000   0.1764
  -7.250  -0.3509   0.09698   0.09057  -0.0150   1.0000   0.1826
  -7.000  -0.3543   0.09561   0.08931  -0.0180   1.0000   0.1908
  -6.750  -0.3422   0.09129   0.08503  -0.0162   1.0000   0.1991
  -6.500  -0.3476   0.09030   0.08418  -0.0225   1.0000   0.2072
  -6.250  -0.3344   0.08600   0.07991  -0.0187   1.0000   0.2184
  -6.000  -0.3288   0.08281   0.07680  -0.0188   1.0000   0.2265
  -5.750  -0.3275   0.08063   0.07471  -0.0215   1.0000   0.2378
  -5.500  -0.3233   0.07847   0.07262  -0.0235   1.0000   0.2515
  -5.000  -0.3117   0.07296   0.06725  -0.0222   1.0000   0.2814
  -4.750  -0.3068   0.06985   0.06421  -0.0189   1.0000   0.2980
  -4.500  -0.3026   0.06725   0.06170  -0.0151   1.0000   0.3187
  -4.250  -0.3005   0.06504   0.05958  -0.0135   1.0000   0.3448
  -4.000  -0.2989   0.06296   0.05760  -0.0112   1.0000   0.3734
  -3.750  -0.2984   0.06086   0.05560  -0.0078   1.0000   0.4031
  -3.500  -0.2996   0.05876   0.05362  -0.0031   1.0000   0.4344
  -3.250  -0.3027   0.05689   0.05188   0.0023   1.0000   0.4702
  -3.000  -0.3107   0.05551   0.05063   0.0081   1.0000   0.5195
  -2.750  -0.3190   0.05354   0.04882   0.0157   1.0000   0.5559
  -2.500  -0.3282   0.05215   0.04755   0.0213   1.0000   0.5971
  -2.250  -0.0466   0.03866   0.03118  -0.0650   0.9874   0.1967
  -2.000   0.0336   0.03455   0.02610  -0.0761   0.9722   0.1703
  -1.750   0.1043   0.03183   0.02263  -0.0846   0.9551   0.1675
  -1.500   0.1655   0.03009   0.02029  -0.0910   0.9344   0.1764
  -1.250   0.2250   0.02823   0.01817  -0.0967   0.9164   0.1875
  -1.000   0.2816   0.02656   0.01625  -0.1011   0.8998   0.2183
  -0.750   0.3293   0.02495   0.01487  -0.1041   0.8828   0.2985
  -0.500   0.3671   0.02357   0.01419  -0.1055   0.8647   0.4282
  -0.250   0.4007   0.02169   0.01317  -0.1043   0.8486   1.0000
   0.000   0.4355   0.02195   0.01296  -0.1051   0.8321   1.0000
   0.250   0.4676   0.02229   0.01296  -0.1054   0.8166   1.0000
   0.500   0.4974   0.02271   0.01312  -0.1055   0.8021   1.0000
   0.750   0.5259   0.02321   0.01340  -0.1055   0.7886   1.0000
   1.000   0.5539   0.02373   0.01374  -0.1054   0.7760   1.0000
   1.250   0.5825   0.02418   0.01403  -0.1052   0.7646   1.0000
   1.500   0.6086   0.02483   0.01455  -0.1050   0.7527   1.0000
   1.750   0.6332   0.02560   0.01523  -0.1048   0.7405   1.0000
   2.000   0.6581   0.02635   0.01591  -0.1045   0.7290   1.0000
   2.250   0.6845   0.02693   0.01642  -0.1040   0.7182   1.0000
   2.500   0.7113   0.02741   0.01682  -0.1033   0.7073   1.0000
   2.750   0.7344   0.02825   0.01764  -0.1028   0.6948   1.0000
   3.000   0.7577   0.02910   0.01848  -0.1023   0.6828   1.0000
   3.250   0.7820   0.02985   0.01925  -0.1016   0.6717   1.0000
   3.500   0.8101   0.03019   0.01954  -0.1007   0.6621   1.0000
   3.750   0.8313   0.03136   0.02077  -0.1003   0.6500   1.0000
   4.000   0.8525   0.03259   0.02208  -0.1000   0.6385   1.0000
   4.250   0.8757   0.03360   0.02316  -0.0994   0.6280   1.0000
   4.500   0.9027   0.03415   0.02374  -0.0985   0.6184   1.0000
   4.750   0.9208   0.03582   0.02554  -0.0982   0.6063   1.0000
   5.000   0.9395   0.03746   0.02730  -0.0977   0.5947   1.0000
   5.250   0.9611   0.03877   0.02875  -0.0971   0.5844   1.0000
   5.500   0.9844   0.03997   0.03005  -0.0965   0.5748   1.0000
   5.750   0.9955   0.04266   0.03293  -0.0963   0.5631   1.0000
   6.000   1.0094   0.04506   0.03547  -0.0960   0.5528   1.0000
   6.250   1.0353   0.04604   0.03661  -0.0952   0.5447   1.0000
   6.500   1.0276   0.05123   0.04198  -0.0959   0.5343   1.0000
   6.750   1.0578   0.05194   0.04285  -0.0950   0.5285   1.0000
   7.000   1.0210   0.06047   0.05146  -0.0969   0.5189   1.0000
   7.250   1.0490   0.06156   0.05273  -0.0960   0.5132   1.0000
   7.500   0.9927   0.07202   0.06309  -0.0988   0.5114   1.0000
   7.750   0.9757   0.07801   0.06910  -0.1000   0.5117   1.0000
   8.000   0.9705   0.08295   0.07411  -0.1010   0.5127   1.0000
   8.750   1.2864   0.03401   0.02628  -0.0684   0.3273   1.0000
   9.000   1.2782   0.03409   0.02562  -0.0627   0.2091   1.0000
   9.250   1.2656   0.03756   0.02837  -0.0592   0.1454   1.0000
   9.500   1.2534   0.04091   0.03138  -0.0561   0.1279   1.0000
   9.750   1.2416   0.04432   0.03465  -0.0537   0.1185   1.0000
  10.000   1.2343   0.04767   0.03800  -0.0520   0.1104   1.0000
  10.250   1.2272   0.05116   0.04137  -0.0506   0.1046   1.0000
  10.500   1.2293   0.05394   0.04430  -0.0490   0.0987   1.0000
  10.750   1.2440   0.05564   0.04576  -0.0456   0.0928   1.0000
  11.000   1.2778   0.05677   0.04714  -0.0426   0.0877   1.0000
  11.250   1.3428   0.05945   0.04968  -0.0420   0.0799   1.0000
  11.500   1.3586   0.06284   0.05349  -0.0407   0.0787   1.0000
  11.750   1.3687   0.06665   0.05773  -0.0394   0.0785   1.0000
  12.000   1.3704   0.07064   0.06208  -0.0379   0.0786   1.0000
  12.250   1.3662   0.07483   0.06661  -0.0365   0.0789   1.0000
  12.500   1.3578   0.07928   0.07135  -0.0355   0.0794   1.0000
  12.750   1.3470   0.08407   0.07640  -0.0350   0.0798   1.0000
  13.000   1.3362   0.08926   0.08182  -0.0351   0.0804   1.0000
  13.250   1.3183   0.09450   0.08733  -0.0359   0.0809   1.0000
  13.500   1.2792   0.10060   0.09375  -0.0394   0.0817   1.0000
  13.750   1.2196   0.11108   0.10451  -0.0481   0.0831   1.0000
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