1. 1-14.There you will find detailed descriptions of the techniques used to generate these waveriders, how the optimized configurations are obtained, and extensive discussions of their performance. Hence, no further elaborationwillbe givenhere. If you are unfamiliar with what these viscous-optimized waveriders looklike, takea peek atFigure 1.We note finally that the work at the University of Maryland has resulted in a computer code, MAXWARP, for the generation of the viscousoptimizedwaveriders;MAXWARP,and various derivativesof it, arenow in use at more than a dozen agencies and companies throughout the world. A new version, MAXWARP2, has just beendeveloped whichincludestheheat transfer analysistobedescribedin thepresent paper.
2. 1-14.These configurations are slender, sharp-edged bodies, with a blunt base and a delta-like planform. On the other hand, therealityofaerodynamicheatingdemandsthat theleading edgeof the waverider be blunt. This immediately introduces a compromise; a blunt leadingedgecreates a detached shockwave-an anathema to the very definitionof a waverider. Question: How do you blunt the leading edge, and stillpreservetheessenceoftheaerodynamic advantage affordedby waveriders? There isno pat answer. In the present work, a little bit of logic is mixed with some intuitive feeling, as describedbelow.
3. Considerthe flow over a sweptcylinder,as sketched in Figure 5. If the flow is inviscid, the stream surface that wets the upper and lower surfacesdivides along the line AA, called the attachment line. If the sweep angle were zero, line AA would be thelocusof stagnation points inatwo-dimensionalflow.Inthecasewithfinite sweep,therearenostagnation points;lineAAis simply the dividing line between the flow that wets the upper and lower surfaces. Moreover, there isa finitecomponent of velocityalong the attachment line. In the high Reynolds number viscous case, there will be a three-dimensional boundary layer along the cylinder. Exterior to the boundary layer, there will be a finite component of velocity in the direction of the attachment line.Thiscreatesthe possibilitythat transition fromlaminar to turbulent flow might occur along the attachment line.This transition phenomena has been extensively studied by Poll 19-21. In order to characterize the possible transition along the swept leading edge of a hypersonic waverider, we assume that it behaves asa sweptcylinder,and wewill utilize theresultsof Poll.InReference 19,Polldefinesfi asacharacteristicReynoldsnumber,where