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This can be referred in future studies into the hypersonic regime and shape optimization to get the best suited geometry with high aerodynamic performance for a given free stream condition.

The study's outcomes advance our understanding of the complex relationship between the radius of leading edges and hypersonic boundary layer stability and pave the way for tangible advancements in hypersonic vehicle design and operation, offering valuable contributions to developing safer and more efficient hypersonic vehicles. ...This research employs a comprehensive methodology to explore hypersonic boundary layers' stability and transition dynamics, focusing specifically on the influence of sharp and blunt leading edges. ...The Linear Stability Solver analysis constitutes a crucial phase wherein the research delves into the eigenvalue spectra, identifying dominant modes and closely scrutinizing the role of the modes in the transition process within the hypersonic boundary layers. This investigation into stability characteristics is paramount for designing and optimizing hypersonic vehicles, providing valuable insights to enhance their efficiency and performance.

Severe problem of aerodynamic heating and drag force are inherent with any hypersonic space vehicle like space shuttle, missiles etc. For proper design of vehicle, the drag force measurement become very crucial.

Scramjet-based hypersonic airbreathers are needed for next-generation defense and space applications. Two scramjet configurations, namely, rectangular and axisymmetric, are primarily studied in the literature.

The study of aerodynamic forces in hypersonic environments is important to ensure the safety and proper functioning of aerospace vehicles. ...In this paper, computational analysis has been performed on a blunt cone model to study the aerodynamic characteristics when hypersonic flow is allowed to pass through the model. The flow has a Mach number of 8.44 and the angle of attack is varied from 0º to 20º. ...This study helps in understanding the aerodynamic and stability characteristics of hypersonic vehicles at various angles of attack that is significantly different from those of the subsonic or supersonic vehicles.

Hypersonic flight vehicles have potential applications in strategic defence, space missions, and future civilian high-speed transportation systems. ...Scramjet-powered air-breathing hypersonic vehicles experience extreme heat loads induced by combustion, shock waves and viscous heat dissipation.

The urgent need to combat global warming has spurred legislative efforts within the transport sector to transition away from fossil fuels. Hydrogen is increasingly being utilised as a green energy vector, which can aid the decarbonisation of transport, including internal combustion engines. Computational fluid dynamics (CFD) is widely used as a tool to study and optimise combustion systems especially in combination with new fuels like hydrogen. Since the behaviour of the injection event significantly impacts combustion and emissions formation especially in direct injection applications, the accurate modelling of H2 injection is imperative for effective design of hydrogen combustion systems. This work aims to evaluate unsteady Reynolds-Averaged Navier Stokes (URANS) modelling of the advective transport process and related numerical methods.

In this work, an investigation of the enthalpy effects on the thermochemical non-equilibrium in hypersonic nozzles is performed. Three different nozzles, with different geometries and stagnation enthalpy conditions are used in this study.

This work aims to expand the applicability of an open-source numerical tool to solve hypersonic gas dynamic flows for space propulsion geometries. This is done by validating the code using two well-known hypersonic test cases, the double cone and the hollow cylinder flare, used by the NATO Research and Technology Organization for the validation of hypersonic flight for laminar viscous-inviscid interactions (D. ...This is done by validating the code using two well-known hypersonic test cases, the double cone and the hollow cylinder flare, used by the NATO Research and Technology Organization for the validation of hypersonic flight for laminar viscous-inviscid interactions (D. ...This is done by validating the code using two well-known hypersonic test cases, the double cone and the hollow cylinder flare, used by the NATO Research and Technology Organization for the validation of hypersonic flight for laminar viscous-inviscid interactions (D. Knight, “RTO WG 10 - Test cases for CFD validation of hypersonic flight,” in 40th AIAA Aerospace Sciences Meeting & Exhibit, 2002).

Tests for this experiment were conducted using the West Virginia University (WVU) Hypersonic Arc Jet Wind Tunnel. A series of twelve N52 grade neodymium magnets were placed in different orientations around a steel toroid mounted around the arc jet’s exhaust plume.

After de-boosting by the VEGA AVUM upper stage the vehicle will execute an autonomous flight from hypersonic to subsonic regimes allowing terminal area energy maneuvers, approach and landing on conventional runways.

Examples are presented for aircraft with highly flexible structure, reentry vehicle with lateral departure tendency, and hypersonic vehicle with extreme forward instantaneous center of rotation. Common design practices, including sensor blending, control mixing and vehicle configuration design changes, to eliminate the NMP response are first described.

A single lightweight engine capable of operating over a wide range of Mach numbers from startup to the hypersonic regime is proposed for automobiles and airplanes. Traditional piston engines, turbojet engines, and scram jet engines operate only under a narrower range of conditions.

Protruding objects from the surface of space orbiters induce aerodynamic heating at transonic to hypersonic speeds. The gap-filler material which came loose from between the insulation tiles on the surface of the space orbiter Discovery during its reentry is a case in point.

This paper presents a quantitative process to track the progress of technology developments within NASA’s Vehicle Systems Program (VSP) as implemented on a Supersonic Business Jet (SBJ). The process, called the Technology Metric Assessment and Tracking (TMAT) process, accounts for the temporal aspects of technology development programs such that technology portfolio assessments, in the form of technological progress towards VSP sector goals, may be tracked and assessed. Progress tracking of internal research and development programs is an essential element to successful strategic endeavors and justification of the pursuit of capital projects [1].

It is found that control of heat transfer on a wing at hypersonic wing can act as a control device, comparable to that due a moderate flap deflection.

Actual trends with regard to light weight design in the automotive industry, in order to reduce fuel consumption and pollution emissions as well as improve the engine efficiency lead to the increasing use of light weight engine components. Due to the harsh operation conditions, the aluminum cylinder surface must be reinforced, and new techniques have been developed and applied. A very promising technological alternative is the use of HVOF (high velocity oxygen fuel) deposited internal coatings, showing improved coating quality results compared to APS (atmospheric plasma spray) coatings. Several HVOF (High Velocity Oxygen Fuels) coating processes (with different fuel gases/fluids) were compared and studied, with a complete mechanical characterization and evaluation of the coatings. Also an economical comparison for the different coating systems is shown.

Almost all aerospace vehicles that depend on aerodynamic lift use changes in geometry for control. Examples include ailerons, elevators and flap deflections. As a theoretical concept these controls represent changes in one of the necessary boundary conditions for the solution of the Navier Stokes equations, which model the airflow. The complete boundary conditions require that the velocities and the temperature on the body surface be defined. In principle, the airflow can be changed by altering the temperature on the body surface. The effectiveness of controlling a vehicle by altering the surface temperature, which is equivalent to an extraction of energy from the airflow, is the topic of this research.

Actual research activities are focused on the development of advanced HVOF sprayed coating systems on cylinder liners, the coating optimization and the cost effective implementation of this technology in an automated series production process. In hypersonic flame spraying (HVOF), the coating is deposited by an elliptically moving HVOF gun, whereas the cylinder liner is rotating.

Starting from the Astrium heritage which is the development experience for a metallic multiwall (MMW) TPS concept originally foreseen to be applied on the hypersonic transportation system SAENGER a requirements analysis in conjunction with a design tradeoff was performed which lead finally to the selection of the most promising metallic TPS concepts for the temperature ranges considered.