Page 245 - Aerodynamics for Engineering Students
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228  Aerodynamics for Engineering Students


























                    Fig. 5.19

                    filaments. In order to satisfy Helmholtz’s second theorem (Section 5.2.1) each fila-
                    ment must either be part of a closed loop or form a horseshoe vortex with trailing
                    vortex filaments running to infinity. Even with this restriction there are still infinitely
                    many ways of arranging such vortex elements for the purposes of modelling the flow
                    field  associated with  a  lifting wing.  For  illustrative purposes consider the  simple
                    arrangement  where  there  is  a  sheet  of  vortex  filaments passing  in  the  spanwise
                    direction through a given wing section (Fig. 5.19). It should be noted, however, that
                    at two, here unspecified, spanwise locations each of these filaments must be turned
                    back to form trailing vortex filaments.
                      Consider the flow in the vicinity of a sheet of fluid moving irrotationally in the xy
                    plane, Fig. 5.19. In this stylized figure the ‘sheet’ is seen to have a section curved in
                    the xy plane and to be of thickness Sn, and the vorticity is represented by a number of
                    vortex filaments normal to the xy plane. The circulation around the element of fluid
                    having sides Ss, Sn is, by definition, AI? = 56s. Sn where 5 is the vorticity of the fluid
                    within the area SsSn.
                      Now for a sheet Sn -0  and if 5 is so large that the product [Sn remains finite, the
                    sheet is  termed  a  vortex  sheet  of  strength  k = CSn. The  circulation around  the
                    element can now be written
                                                    AI? = kSs                          (5.21)
                    An alternative way of finding the circulation around the element is to integrate the
                    tangential flow components. Thus
                                                 AI?= (UZ - u~)SS                      (5.22)

                      Comparison of Eqns (5.21) and (5.22) shows that the local strength k of the vortex
                    sheet is the tangential velocity jump through the sheet.
                      Alternatively, a flow situation in which the tangential velocity changes discontinu-
                    ously in the normal direction may be mathematically represented by a vortex sheet of
                    strength proportional to the velocity change.
                      The vortex sheet concept has important applications in wing theory.
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