We introduce a straightforward experimental approach for determining the mean flow velocity of a supersonic jet with very high precision. While time measurements easily can achieve accuracies of Δt/t ≤ 10(-4), typically the absolute flight distances are much less well-defined. This causes significantly increased errors in calculations of the mean flow velocity and mean kinetic energy. The basic...

The weight of the oxidizer dominates the take-off weight of rocket based propulsion systems. Therefore, airbreathing engines that consume the oxygen from the atmosphere offer a promising alternative. At flight conditions with Mach numbers above 6 SCramjet propulsion systems represent a better suited concept than ramjet systems, as the high static temperature resulting from the deceleration to s...

In this paper the supersonic ejectors are experimentally and analytically studied. Ejector is a device that uses the energy of a fluid to move another fluid. This device works like a vacuum pump without usage of piston, rotor or any other moving component. An ejector contains an active nozzle, a passive nozzle, a mixing chamber and a diffuser. Since the fluid viscosity is large, and the flow is...

In the present work, we propose a reformulation of the fluxes and interpolation calculations in the PISO method, a well-known pressure-correction solver. This new reformulation introduces the AUSM up flux definition as a replacement for the standard Rhie and Chow method of obtaining fluxes and central interpolation of pressure at the control volume faces. This algorithm tries to compatibilize t...

A review of recent and historical work in the field of transonic and supersonic ground effect aerodynamics has been conducted, focussing on applied research on wings and aircraft, present and future ground transportation, projectiles, rocket sleds and other related bodies which travel in close ground proximity in the compressible regime. Methods for ground testing are described and evaluated, n...

We present the construction and report on the experimentation of a shapeoptimization method applied to the aerodynamic design of a transonic or supersonic business jet. The main numerical ingredients are: a 3D unstructured-grid compressible-flow finite-volume solver, free-form deformation approach for shape and mesh movement based on self-adaptive and multilevel 3D tensorial Bézier polynomial r...

A numerical analysis is carried out to determine the flowfield and starting characteristics of a straight cylindrical supersonic exhaust diffuser of a high-altitude simulation of a high expansion ratio rocket nozzle. The flow field inside the high-altitude facility is analyzed for a conical nozzle of expansion ratio of 25, diffuser inlet-to-nozzle throat area ratio of 28.9, and diffuser length-...

The unsteady compressible flow around a body tail projectile is numerically solved with a Large Eddy Simulation (LES) method, Smagorinsky-Lilly model was used as the Sub-Grid Scale (SGS). The computed results are obtained in supersonic flow regime for a viscous fluid in order to determine the aerodynamic coefficients with different angles of attack. The flow around a body tail projectile was so...

The renewed interest in high-speed flight has recently demonstrated the need for the development of hypersonic air-breathing propulsion systems, i.e., in which the ambient air is used as oxidizer. These systems have long been recognized as the most well-suited for hypersonic propulsion. Although a traditional ramjet is most appropriate for supersonic speeds (Mach 3 to 5), hypersonic speeds (Mac...