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GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 178 AIRFOIL (goe178-il)
Reynolds number: 100,000
Max Cl/Cd: 58.14 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe178-il-100000.txt
Download as CSV file: xf-goe178-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3520   0.09695   0.09227  -0.0173   1.0000   0.0837
  -7.500  -0.3525   0.09478   0.09018  -0.0199   1.0000   0.0865
  -7.250  -0.3538   0.09371   0.08920  -0.0315   1.0000   0.0883
  -7.000  -0.3475   0.08909   0.08464  -0.0341   1.0000   0.0892
  -6.750  -0.3372   0.08471   0.08026  -0.0256   1.0000   0.0920
  -6.500  -0.3290   0.08181   0.07741  -0.0255   1.0000   0.0956
  -6.250  -0.3228   0.07900   0.07464  -0.0286   1.0000   0.0998
  -6.000  -0.3108   0.07596   0.07152  -0.0428   1.0000   0.1035
  -5.750  -0.3078   0.07206   0.06774  -0.0372   1.0000   0.1048
  -5.500  -0.3022   0.06930   0.06505  -0.0344   1.0000   0.1071
  -5.250  -0.2945   0.06669   0.06246  -0.0342   1.0000   0.1106
  -5.000  -0.2721   0.06295   0.05850  -0.0449   1.0000   0.1187
  -4.750  -0.2708   0.06024   0.05595  -0.0403   1.0000   0.1207
  -4.500  -0.2642   0.05821   0.05397  -0.0384   1.0000   0.1258
  -4.250  -0.2445   0.05484   0.05042  -0.0435   1.0000   0.1349
  -4.000  -0.2302   0.05244   0.04808  -0.0431   0.9984   0.1395
  -3.750  -0.1764   0.04799   0.04344  -0.0522   0.9897   0.1544
  -3.500  -0.1187   0.04395   0.03911  -0.0621   0.9804   0.1794
  -3.250  -0.0674   0.04074   0.03573  -0.0689   0.9709   0.2086
  -3.000  -0.0196   0.03768   0.03259  -0.0744   0.9592   0.2383
  -2.750   0.0715   0.02713   0.01995  -0.0871   0.9536   0.1013
  -2.500   0.1247   0.02451   0.01682  -0.0918   0.9421   0.1018
  -2.250   0.1683   0.02227   0.01420  -0.0943   0.9229   0.1007
  -2.000   0.2093   0.02051   0.01208  -0.0959   0.9010   0.1015
  -1.750   0.2444   0.01902   0.01032  -0.0961   0.8742   0.1042
  -1.500   0.2752   0.01783   0.00904  -0.0956   0.8452   0.1102
  -1.250   0.3030   0.01702   0.00809  -0.0945   0.8151   0.1224
  -1.000   0.3291   0.01628   0.00730  -0.0933   0.7857   0.1422
  -0.750   0.3548   0.01563   0.00668  -0.0922   0.7591   0.1849
  -0.500   0.3805   0.01531   0.00633  -0.0912   0.7367   0.2294
  -0.250   0.4070   0.01475   0.00613  -0.0909   0.7161   0.3257
   0.000   0.4298   0.01313   0.00588  -0.0887   0.6999   1.0000
   0.250   0.4574   0.01341   0.00580  -0.0884   0.6847   1.0000
   0.500   0.4850   0.01369   0.00580  -0.0881   0.6713   1.0000
   0.750   0.5126   0.01399   0.00585  -0.0879   0.6598   1.0000
   1.000   0.5403   0.01431   0.00596  -0.0877   0.6490   1.0000
   1.250   0.5680   0.01463   0.00615  -0.0877   0.6382   1.0000
   1.500   0.5956   0.01497   0.00633  -0.0875   0.6285   1.0000
   1.750   0.6229   0.01529   0.00647  -0.0872   0.6185   1.0000
   2.000   0.6500   0.01560   0.00670  -0.0871   0.6069   1.0000
   2.250   0.6771   0.01594   0.00695  -0.0869   0.5965   1.0000
   2.500   0.7044   0.01629   0.00715  -0.0866   0.5882   1.0000
   2.750   0.7316   0.01667   0.00755  -0.0866   0.5790   1.0000
   3.000   0.7590   0.01707   0.00788  -0.0864   0.5716   1.0000
   3.250   0.7860   0.01747   0.00831  -0.0864   0.5631   1.0000
   3.500   0.8131   0.01790   0.00871  -0.0862   0.5555   1.0000
   3.750   0.8401   0.01832   0.00914  -0.0861   0.5471   1.0000
   4.000   0.8668   0.01879   0.00966  -0.0859   0.5391   1.0000
   4.250   0.8937   0.01923   0.01010  -0.0857   0.5312   1.0000
   4.500   0.9200   0.01976   0.01072  -0.0856   0.5228   1.0000
   4.750   0.9469   0.02016   0.01109  -0.0852   0.5144   1.0000
   5.000   0.9724   0.02060   0.01164  -0.0849   0.5032   1.0000
   5.250   0.9980   0.02102   0.01212  -0.0845   0.4922   1.0000
   5.500   1.0241   0.02137   0.01247  -0.0840   0.4818   1.0000
   5.750   1.0500   0.02171   0.01287  -0.0835   0.4708   1.0000
   6.000   1.0749   0.02220   0.01352  -0.0830   0.4597   1.0000
   6.250   1.1004   0.02269   0.01411  -0.0826   0.4502   1.0000
   6.500   1.1267   0.02305   0.01451  -0.0821   0.4406   1.0000
   6.750   1.1511   0.02318   0.01477  -0.0814   0.4267   1.0000
   7.000   1.1757   0.02288   0.01442  -0.0803   0.4099   1.0000
   7.250   1.1983   0.02274   0.01446  -0.0792   0.3922   1.0000
   7.500   1.2208   0.02246   0.01437  -0.0780   0.3728   1.0000
   7.750   1.2423   0.02197   0.01409  -0.0766   0.3471   1.0000
   8.000   1.2575   0.02163   0.01360  -0.0742   0.2630   1.0000
   8.250   1.2457   0.02605   0.01643  -0.0702   0.0835   1.0000
   8.500   1.2484   0.02882   0.01917  -0.0673   0.0690   1.0000
   8.750   1.2551   0.03081   0.02135  -0.0648   0.0630   1.0000
   9.000   1.2556   0.03306   0.02369  -0.0619   0.0587   1.0000
   9.250   1.2538   0.03530   0.02596  -0.0586   0.0558   1.0000
   9.500   1.2589   0.03700   0.02778  -0.0559   0.0529   1.0000
   9.750   1.2666   0.03887   0.02971  -0.0535   0.0507   1.0000
  10.000   1.2815   0.04078   0.03158  -0.0517   0.0487   1.0000
  10.250   1.3150   0.04323   0.03386  -0.0515   0.0466   1.0000
  10.500   1.3587   0.04733   0.03793  -0.0530   0.0444   1.0000
  10.750   1.3703   0.04918   0.04009  -0.0511   0.0432   1.0000
  11.000   1.3857   0.05183   0.04304  -0.0497   0.0425   1.0000
  11.250   1.3994   0.05508   0.04662  -0.0483   0.0425   1.0000
  11.500   1.4080   0.05859   0.05046  -0.0466   0.0427   1.0000
  11.750   1.4124   0.06239   0.05458  -0.0448   0.0432   1.0000
  12.000   1.4131   0.06656   0.05904  -0.0429   0.0437   1.0000
  12.250   1.4323   0.07369   0.06639  -0.0434   0.0452   1.0000
  12.500   1.4209   0.07469   0.06767  -0.0399   0.0457   1.0000
  12.750   1.4011   0.07646   0.06977  -0.0367   0.0466   1.0000
  13.000   1.3712   0.07983   0.07350  -0.0353   0.0472   1.0000
  13.250   1.3406   0.08448   0.07850  -0.0358   0.0479   1.0000
  13.500   1.3110   0.09023   0.08456  -0.0378   0.0486   1.0000
  13.750   1.2825   0.09688   0.09149  -0.0411   0.0493   1.0000
  14.000   1.2541   0.10432   0.09916  -0.0453   0.0499   1.0000
  14.250   1.2251   0.11259   0.10764  -0.0506   0.0505   1.0000
  14.500   1.1949   0.12188   0.11711  -0.0570   0.0511   1.0000
  14.750   1.1630   0.13273   0.12807  -0.0647   0.0518   1.0000
  15.000   1.1322   0.14505   0.14049  -0.0732   0.0532   1.0000
  15.250   1.1193   0.15404   0.14949  -0.0778   0.0552   1.0000
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