Flow separation control over a three-dimensional contour bump using jet in a Mach 1.9 supersonic freestream has been experimentally investigated using a transonic/supersonic wind tunnel. Jet total pressure in the range of 0–4 bar was blowing at the valley of the contour bump. Schlieren photography, surface oil flow visualisation and particle image velocimetry measurements were employed for flow...

Supersonic flow over a capsule-shaped abort system with angle of attack (AoA) of α, which is boosted by supersonic aerodynamic interference, is investigated numerically through the 3D simulation. The objective of this study is to examine the effects of AoA on aerodynamic stability. In the previous study, the flowfield around this system at α = 0 is unsteady and has a strong periodic flow oscill...

The response of choked nozzles and supersonic diffusers to one-dimensional flow perturbations is investigated. Following previous arguments in the literature, small flow perturbations in a duct of spatially linear steady velocity distribution are determined by solution of a hyper-geometric differential equation. A set of boundary conditions is then developed that extends the existing work to a ...

For experimental studies of transition from laminar to turbulent boundary layer flow it is important to know the ambient noise spectrum in the facility. In supersonic wind tunnels this is often assessed by measuring pitot pressure noise. A discussion of such measurements is given, e. g., by Salyer et al. [1], see also Parziale et al. [2]. The question arises as to whether the noise measured by ...

This invited paper presents efficient solutions of the Euler and Navier-Stokes equations based on finite difference and finite volume formulations. They were obtained with several methods recently developed for the efficient analysis of steady and unsteady external flows. (i) A biased-flux method based on an explicit finite volume formulation is first presented for the solution of the Euler equ...

Intake design for supersonic engines, in common with other engineering design problems, is application dependent and the true challenges are in meeting performance targets over the required Mach and Reynolds number ranges while complying with the multitude of constraints imposed by the aircraft/missile and its mission. The fundamentals and limitations of efficient ram compression are well under...