This article reports on the use of a shock tunnel to study the operation of scramjet powered
configurations at sub-orbital velocities above 2km/s. Thrust, as given by a net thrust …

This paper analyzes different techniques for the calibration of force balances for use in short-
duration impulse hypersonic facilities such as shock tunnels. The background to how …

At hypersonic flight the kinetic energy of the flow is large enough that high temperature
effects such as vibrational excitation or dissociation of the fluid molecules occur. Due to the …

Three force measurement techniques in a shock tunnel, the free-flight, movable-support
force balance, and stress-wave force balance techniques were employed, and each …

Two force balance techniques for use in hypersonic impulse facilities are compared by
measuring the drag force on a 30° semi-apex-angle blunt cone model in a hypersonic shock …

THE long and slender shapes of hypersonic vehicles cause thick and mostly turbulent
boundary layers. The resulting skinfriction drag can contribute a significant amount of the …

Recent advances in hypersonic research activities have led to the development in ground
based test facilities for simulating near-realistic flight conditions in the laboratory. Basic …

Current investigations solely focus on application of an impulse facility in diverse area of
high‐speed aerodynamics and structural mechanics. Shock tube, the fundamental impulse …

The measurement of forces in hypervelocity expansion tubes is not possible using
conventional techniques. The stress wave force balance technique can be applied in …

A key issue that can affect the implementation of boundary-layer combustion for viscous
drag reduction in scramjet combustors is the potential of nonuniform flow entering the …