Delta Wing Configurations

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Delta Wing Configurations

J. Szodruch

The flow field over a slender delta wing at angle of attack immersed in a supersonic stream can be divided into two characteristic regions. The windward or pressure side faces the oncoming flow and is strongly influenced by the bow shock wave; the leeward or suction side is dominated by the effects of inviscid/viscous interaction. It is mainly the leeward flow which is then affected by Reynolds number changes and especially these effects are discussed in more detail. In the past, for subsonic, transonic, and supersonic free stream Mach numbers the essential issue of design with slender wings, where vortices occur over the wing at virtually every flight condition, is to fix the location of the separation lines so that the vehicle is always controllable. This is why Reynolds number effects in these flow regimes were considered of secondary importance. On the other hand at hypersonic speeds the influence of Reynolds number on peak heating as well as on the development and size of characteristic patterns in the flow field are more important. Here hypersonic viscous interaction is dominating, especially near the wing apex, and the vortices induce high rates of heat transfer along the attachment line. The discussion is confined to free stream Mach numbers from high subsonic to supersonic. With respect to Reynolds number effects it is of major importance to define the different types of vortical flow in that velocity range and to consider the influence of wing geometry.