XFOIL         Version 6.8
  
 Calculated polar for: RG-15 8.9%                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =    .000     Re =      .300 e 6     Ncrit =   9.000
  
   alpha     CL        CD       CDp       CM    Top Xtr Bot Xtr
  ------- -------- --------- --------- -------- ------- -------
  -2.000   -.0079    .00828    .00384   -.0538   .9625   .7282
  -1.500    .0643    .00804    .00362   -.0565   .9505   .7904
  -1.000    .1292    .00775    .00336   -.0574   .9351   .8326
   -.500    .1876    .00748    .00310   -.0569   .9146   .8681
    .500    .2941    .00708    .00267   -.0534   .8579   .9350
   1.000    .3603    .00701    .00248   -.0547   .8227   .9676
   1.500    .4391    .00698    .00233   -.0595   .7798   .9971
   2.000    .4943    .00717    .00233   -.0597   .7318  1.0000
   2.500    .5433    .00747    .00244   -.0584   .6805  1.0000
   3.000    .5930    .00784    .00260   -.0572   .6256  1.0000
   3.500    .6422    .00830    .00284   -.0559   .5660  1.0000
   4.000    .6910    .00883    .00319   -.0545   .5017  1.0000
   4.500    .7393    .00946    .00360   -.0532   .4353  1.0000
   5.000    .7869    .01021    .00414   -.0518   .3597  1.0000
   5.500    .8336    .01113    .00478   -.0505   .2802  1.0000
   6.000    .8795    .01223    .00558   -.0491   .2013  1.0000
   6.500    .9233    .01361    .00664   -.0475   .1244  1.0000
   7.000    .9664    .01510    .00786   -.0458   .0712  1.0000
   7.500   1.0086    .01668    .00934   -.0440   .0374  1.0000
   8.000   1.0435    .01925    .01200   -.0406   .0183  1.0000
   8.500   1.0663    .02304    .01607   -.0359   .0146  1.0000
   9.000   1.0969    .02609    .01940   -.0323   .0137  1.0000
   9.500   1.1252    .03015    .02380   -.0286   .0132  1.0000
  10.000   1.1521    .03488    .02893   -.0252   .0128  1.0000