The e ect of initial nonequilibrium dissociated air constituents on the combustion of hydrogen in highspeed ows for a simulated Mach 17 ight condition was investigated by analyzing the results of comparative combustion experiments performed in a re ected shock tunnel test gas and in a shock expansion tunnel test gas. The results were analyzed and interpreted with a one-dimensional quasi-three-s...

Boundary-layer wind tunnel provides a unique platform to reproduce urban, suburban and rural atmospheric boundary layer (ABL) by using roughness devices such as vortex generators, floor roughness, barrier walls, and slots in the extended test-section floor in the contraction cone. Each passive device impacts wind properties in a certain way. In this study, influence of various passive devices o...

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 ...

Recent advances in computing subsonic flow have been applied to helicopter configurations with various degrees of success. This paper is a comparison of two specific methods applied to a particularly challenging regime of helicopter flight, very low speeds, where the interaction of the rotor wake and the fuselage are most significant. Comparisons are made between different methods of predicting...

This paper presents recent results from an Industry-University-Defence collaborative project whose aim is to characterise the hydroacoustic environment of the Australian Maritime College Cavitation Tunnel. After summarising the operation of the tunnel, a methodology for measuring and processing the hydroacoustic measurements is presented that includes a technique for reducing the level of turbu...

The stability boundaries of a very flexible wing are sought to inform wind-tunnel flutter test campaign. objective is twofold: identify via simulation the relevant physical processes be explored while ensuring safe and nondestructive experiments, provide benchmark case for which computational models data freely available. Analyses have been independently carried out using two geometrically nonl...