The preliminary study is regarding the scramjet thermal management, choice of fuel for better combustion and cooling, utilizing the heat sink capacity of endothermic fuels for enhanced cooling, passive cooling technology to prevent ablation of aero structures, where concentrate on material selection or providing thermal barrier coatings. From the work it is clear that there is a tremendous progress in thermal management of scramjet components like leading edges, fuselage and combustor walls. But one critical component needs attention, it is wedge strut. Cooling technology prevents the component from becoming sacrificial under high thermal loads. Apart from passive cooling, active cooling is better for thermal management of wedge strut. To felicitate as a research, incorporated wedge strut model that would utilize the benefits of endothermicity of fuels, and structural analysis using ANSYS Software to designate the dimensional stability under thermal loads.
Fluid-structure interaction (FSI) is the commerce between a flexible structure and the surrounding fluid gives a variety of phenomenon. Application of this phenomenon in many areas like vibrational analysis of aircraft wings, machinery, bridges, etc. This computational analysis leads to many aerodynamic and structural dynamicproblems. In the present article, we review the structural analysis of cropped delta wing aircraft with fence and without the fence . One of the key aspects of developing a better design from the data collected by FCI. Several such techniques are reviewed in this paper. As a part of this work, the experimental model setup for analysis the cropped delta wing by using wind tunnel and validate with software analysis values. The model of a cropped delta wing with the fence at different Mach number and angle of attack are selected to high spot the futuristic of computational problems.
Manufacturing and maintaining different aircraft fleet leads to various purposes, which consumes more money as well as man power. Solution to this, nations that are leading in the field of aeronautics are performing much research and development works on new aircraft designs that could do the operations those were done by varied aircrafts. The foremost benefit of this delta wing is, along the huge rearward sweep angle, the wing’s leading edge would not contact the boundary of shock wave. Further, the boundary is produced at the fuselage nose due to the speed of aircraft approaches and also goes beyond the transonic to supersonic speed. Further, rearward sweep angle greatly worse the airspeed: wings under normal condition to leading edge, so permits the aircraft to fly at great transonic, subsonic, or supersonic speed, whereas the over wing speed is kept to minimal range than that of the sound speed. The cropped delta wing with fence has analysed in three cases: Fences at 3/4th distance from the centre, with fences at half distance from the centre and with fences at the centre. Further, the delta wing that cropped is exported to ANSYS FLUENT V14.0 software and analysed by making the boundary condition settings like sonic Mach number of flow over wing along with the angle of attack.
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