Extensive wind-tunnel tests were performed on a Y-shaped diverterless supersonic inlet
(DSI). All tests were conducted at a free stream Mach number of M∞= 1.65, the design Mach …

Flow in a convergent–divergent nozzle is studied for pressure ratios (NPR) of 1–11 and exit-
to-throat area ratios of 1.2 to 2.0. The unsteady compressible Navier–Stokes equations …

Ambient air is ingested into the engine of military aircrafts using the air-intake system within
a limited space. The flow non-uniformity produced in the air-intake creates flow separation …

A series of wind-tunnel tests were conducted on a Y-shaped diverterless supersonic inlet
(DSI) in order to investigate its performance at various operating conditions. The present DSI …

It is of great significance to study the hysteresis phenomenon in the unstart/restart process of
supersonic inlets for restart control in the practical operation of ramjet engines. In this paper …

This research investigates the performance of a MRD intake design for supersonic aircraft
engines, focusing on its behavior under varying Mach numbers and angles of attack …

The turbulent transonic two-dimensional airflow in 9°-bent channels is studied numerically
on the basis of the Reynolds-averaged Navier–Stokes equations. The flow is supersonic at …

Two-and three-dimensional turbulent airflows in a 9-degrees-bent channel are studied
numerically. The inner surfaces of upper and lower walls are parallel to each other upstream …

The turbulent airflow in 2D and 3D channels with bends of opposite walls is studied
numerically. The channels are slightly divergent in the longitudinal direction upstream and …

The two-dimensional turbulent airflow in a 9-degrees-bent channel is studied numerically.
Inner surfaces of the top and bottom walls are parallel to each other upstream and …