A transverse side jet in a supersonic crossflow causes a significant region of separated flow in its vicinity. This separation alters the effectiveness of the jet in producing control forces and moments. In this study, numerical simulations are carried out in order to estimate this change in effectiveness. The effect of a number of parameters such as the angle of attack, angle of yaw, jet pressure ratio, injection Mach number, and presence or absence of a flare aft of the injection are studied. For the geometry considered, it is seen that the effectiveness is enhanced significantly as the angle of attack, angle of yaw, or the jet pressure ratio are increased. The jet injection Mach number does not have a significant effect as long as the jet pressure ratio and jet mass flow rate are unchanged.

This paper is associated with a video winner of a 2021 American Physical Society's Division of Fluid Dynamics (DFD) Milton van Dyke Award for work presented at the DFD Gallery of Fluid Motion. The original video is available online at the Gallery of Fluid Motion, https://doi.org/10.1103/APS.DFD.2021.GFM.V0038.

In this Letter, we have carried out the two-dimensional numerical simulation of axisymmetric relativistic jet in cylindrical coordinates by employing higher order finite volume method in PLUTO [Mignone et al., “PLUTO: A numerical code for computational astrophysics,” Astrophys. J. Suppl. Ser. 170, 228 (2007)] solver. The modified vorticity transport equation has been proposed for relativistic flow by taking the curl of the momentum equation, which shows significant change in the baroclinic vorticity production term due to relativistic effect. Both mathematical analysis and numerical results show that the vorticity production term due to baroclinic torque is heavily influenced due to the presence of specific enthalpy gradient and square of Lorentz factor gradient in a relativistic fluid flow.

In this study, shock wave diffraction has been investigated through a numerical simulation of a moving normal shock incident on a sharp-edged wedge. Schardin's problem is revisited using some existing and new mathematical tools. Two-dimensional compressible Navier–Stokes equation is solved using a higher-order version of the rhoCentralFoam solver in the OpenFOAM platform. Overall flow structures are captured with high efficacy. The divergence of the Lamb vector is used to probe the interaction between vorticity bearing and fluid straining motion, which increases dramatically inside the primary vortex after collision with the reflected Mach stem and increases the turbulent kinetic energy (TKE). In the separated shear layer that emerges from the wedge tip, there is a reduction of TKE after the collision between the lambda shock and accelerated shock. The vorticity pumping into the mean flow by the baroclinic torque is dominant in the separated shear layer before the above collision, whereas after collision it is only dominant inside the primary vortex. A new vector M is introduced here, which is the cross product of the vorticity vector and the pressure gradient vector. The divergence of M shows the interaction between the pressure gradient and the vorticity gradient. This interaction affects the separation bubble formed over the base wall of the wedge due to the shock-wave/boundary layer interaction induced by the lambda shock. Dynamic mode decomposition shows a dominant mode at a frequency of 125.7 Hz, which is due to low-frequency shock oscillation.

Flapping is an energy-demanding mode of fast animal locomotion that requires physiology, wing kinematics, and unsteady mechanics to work in unison. The trailing flow or wake is a signature of flapping mechanics, which makes it a popular candidate for visualization and analysis. While there are multiple ways to analyze wakes, we need a general framework to ensure utility of the analysis in bio-inspired flapping flight. In this article, we develop a theoretical framework to analyze the transport phenomena of wakes. To illustrate, we apply the theory to a two-dimensional modeled hovering flight comprising engineered rigid flapping plates, which vary in aspect ratio, wingbeat frequency, and the use of winglet. The results potentially explain certain observations in natural flight.