XFOIL         Version 6.8
  
 Calculated polar for: e387                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =    .000     Re =      .375 e 6     Ncrit =   7.000
  
   alpha     CL        CD       CDp       CM    Top Xtr Bot Xtr
  ------- -------- --------- --------- -------- ------- -------
  -2.000    .1721    .01004    .00247   -.0796   .6868   .0295
  -1.500    .2269    .00922    .00214   -.0797   .6737   .1805
  -1.000    .2807    .00844    .00204   -.0799   .6617   .4185
   -.500    .3267    .00736    .00209   -.0777   .6501   .7971
    .000    .3915    .00711    .00197   -.0789   .6381  1.0000
    .500    .4472    .00728    .00194   -.0789   .6273  1.0000
   1.000    .5027    .00745    .00196   -.0788   .6162  1.0000
   1.500    .5585    .00761    .00205   -.0788   .6049  1.0000
   2.000    .6139    .00781    .00216   -.0788   .5941  1.0000
   2.500    .6691    .00802    .00230   -.0787   .5821  1.0000
   3.000    .7242    .00819    .00247   -.0786   .5676  1.0000
   3.500    .7790    .00838    .00267   -.0784   .5516  1.0000
   4.000    .8335    .00860    .00290   -.0782   .5346  1.0000
   4.500    .8875    .00884    .00317   -.0779   .5153  1.0000
   5.000    .9406    .00910    .00343   -.0775   .4820  1.0000
   5.500    .9921    .00953    .00380   -.0769   .4351  1.0000
   6.000   1.0364    .01073    .00445   -.0754   .3138  1.0000
   6.500   1.0742    .01279    .00579   -.0735   .1760  1.0000
   7.000   1.1111    .01487    .00728   -.0714   .0736  1.0000
   7.500   1.1463    .01698    .00905   -.0689   .0177  1.0000
   8.000   1.1858    .01847    .01069   -.0668   .0141  1.0000
   8.500   1.2219    .02007    .01249   -.0643   .0125  1.0000
   9.000   1.2520    .02194    .01458   -.0612   .0117  1.0000
   9.500   1.2706    .02412    .01699   -.0566   .0112  1.0000
  10.000   1.2799    .02684    .01992   -.0518   .0107  1.0000