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9.6  Conformal  Mapping  Methods                                      285



         (b)  Compute  R  from  Eq.  (9.6.10). that  is,

                                                   2
                                      R  =  \Jx\>  +  y p
         (c)  Determine  £ and  77 at  p  from  Eq.  (9.6.12), that  is,

                             =  V2i?cos  ( ^  1  ,  77P  =  V2i?sin  ( J
                          £ P
         The  calculation  of the  (£,  77) net  for  off-body  points  requires  the  determination
         of  £ =  const  and  77  =  const  lines.  One  procedure  is  to  start  at  77  =  ryp,  where
         £p  is  known,  and  vary  77 in  small  increments  and  compute  r  and  6  from  Eq.
         (9.6.5). This  procedure  is repeated  for  other  values  of £p  in  uniform  increments
         in  77 except  for  the  region  close  to  the  airfoil  surface  where  the  77-increments
         are  determined  by  the  body  points.  Note  that  in  the  region  behind  the  airfoil
         yp  =  0,  ?7P  =  0 and  £p  =  2xp.
            The  £p-constant  and  77-constant  lines  determined  in  this  manner  produce  a
         parabolic  grid  in  the  computational  plane.  The  inverse  transformation  follows
         from  Eq.  (9.6.2);  for  each  value  of  £  and  77,  x  and  y  are  determined  in  the
         physical  plane.


         9.6.2  Wind  Tunnel  Mapping   Function

         The  C-mesh  generated  by  the  parabolic  mapping  function  discussed  above  is
         essentially  a  set  of  confocal,  orthogonal  parabolas  wrapping  around  the  airfoil.
         With  this mapping the outer boundary  of the  grid  given  by the  last  parabola  ex-
         tends  far  away  from  the  airfoil  surface.  This  feature  may be  unnecessary  and/or
         undesirable  in  some  practical  applications.  A  different  mapping  function  that
         addresses  this  problem  is  the  infinite  "wind-tunnel"  mapping  function  defined
         by
                                         l
                                    Z  = n(l-coshC)                        (9.6.14)
         Where
                                        Z  =  x  +  iy                   (9.6.15a)
                                        C  =  £ +  ZT7                   (9.6.15b)
         and
                                      coshC  =  1 -e z                    (9.6.16)
         In this transformation,  the  singular  point  located  at  half the  leading  edge  radius
         is  at  (In 2,0)  and  all  values  of  y  lie  between  ±n.  As  shown  in  Fig.  9.11a,  this
         mapping  allows  the  airfoil  and  its  wake,  indicated  by  the  contour  ABCDE,  to
         be  transformed  into  a  nearly  straight  77  =  TT  line  in  the  computational  plane.
         The  far-field  boundaries  HI  and  GF  are  mapped  to  the  r\ =  0  line.  Points  on
         the  upper  surface  of  the  airfoil  are  mapped  to  the  left  of  the  77-axis and  points
         on  the  lower  surface  are  mapped  to  the  right  of the  77-axis.
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