The Hy-V project will conduct the first-ever mode-transition flight-test for a dual-mode hypersonic scramjet, which will occur at approximately 90,000 feet onboard a sounding rocket. At altitude, atmospheric conditions and inlet flow speed will match the flow conditions simulated in the UVA Aerospace Research Laboratory (ARL) hypersonic wind tunnel. Geometric similarity between the wind tunnel ...

The high performance and instability in combustion chamber are the most challenging requirements for faster developments and technical advances in most of the engines. The design and development challenges of such engines are highly influenced by its combustion behavior taking place inside the combustion chamber. Studies on the injection, vaporization and combustion phenomena inside combustion ...

Significant advancements in hypersonic airbreathing vehicle technology have been made in the country’s research centers and industry over the past 40 years. Some of that technology is being validated with the X-43 flight tests. This paper presents an overview of hypersonic airbreathing technology status within the US, and a hypersonic technology development plan. This plan builds on the nation’...

This experimental investigation focused on the ignition and combustion characteristics of a tandem cavity-based scramjet combustor with side-by-side identical cavities. study utilized Pusan National University-direct connect (PNU-DCSC), which was capable simulating flight conditions at Mach number 4.0–5.0 altitudes 20–25 km using vitiated air heater (VAH). The tests were conducted under off-des...

In order to rapidly predict the performance of hydrocarbon-fueled regeneratively cooled scramjet engine in system design, a quasi-one-dimensional model has been developed. The consists supersonic combustor with finite-rate chemistry and cooling channel real gas working medium, which are governed by two sets ordinary differential equations separately. Additional models for wall friction, heat tr...

The numerical prediction of scramjet in-flight performance is a landmark example in which current simulation capability is overwhelmed by abundant uncertainty and error. The aim of this work is to develop a decision-making tool for balancing the available computational resources in order to equally reduce the effects of all sources of uncertainty and error below a confidence threshold. To that ...

Research into hypersonic flow phenomona has been conducted by numerous groups within Australia for over 40 years. The genesis of all the modern day work can be traced back to the return of the then Dr Ray Stalker from England, to take a faculty position in the Physics Department of the Australian National University, Canberra, in 1962. Dr Stalker had a keen interest in the aerodynamics of bodie...