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Magnetohydrodynamic aerobraking shock stand-off measurements with flight representative electrodynamic boundary conditions. Gildfind, David E., Smith, Daniel, Lefevre, Alexis, Jacobs, Peter A. Magnetohydrodynamic aerobraking shock stand-off measurements with flight representative electrodynamic boundary conditions doi: 10.2514/6.2022-0828Įlectron number density measurements in a Saturn entry conditionĪn Experimental Study of CO2 Thermochemical Nonequilibrium Reston, VA, United States: American Institute of Aeronautics and Astronautics. (2022).Įxperimental measurements of total heat flux for superorbital earth reentry with magnetohydrodynamic flow control.ĪIAA SCITECH Forum, San Diego, CA, United States & Virtual, 3-7 January 2022. Lefevre, Alexis, Gildfind, David E., Gollan, Rowan J., Jacobs, Peter A., James, Christopher M. doi: 10.2514/1.J061037Ĭonference Publication: Experimental measurements of total heat flux for superorbital earth reentry with magnetohydrodynamic flow control (2022).Īn Experimental Study of CO2 Thermochemical Nonequilibrium. Gu, Sangdi, Morgan, Richard G., McIntyre, Timothy J. Journal Article: An Experimental Study of CO2 Thermochemical Nonequilibrium (2022).Įlectron number density measurements in a Saturn entry condition.

Liu, Yu, James, Christopher M., Morgan, Richard G., Jacobs, Peter A., Gollan, Rowan and McIntyre, Timothy J. Journal Article: Electron number density measurements in a Saturn entry condition We use optical techniques, including laser induced fluorescence, to observe and measure the flow species in order to develop our understanding and to ultimately improve the engine design. However the mixing and combustion processes in such engines are still not well understood. In the longer term they may also lead to hypersonic flight lowering travel times around the globe. Supersonic combustion ramjet engines offer the ability of low cost delivery of payloads to space.

Laser based imaging and measurement of supersonic combusting flows in a shock tunnel.

Along with flow visualisation we conduct measurements to determine heating of the surface of the vehicle due to convective and radiative processes. We conduct tests over various shaped bodies in test gases including air, carbon-dioxide and hydrogen/neon. Ground-based facilities allow us to generate and study such flows. Vehicles entering a planetary atmospheres at hypersonic speeds generate gas flows that are characterised by high temperatures leading to chemical and thermal non-equilibrium.

Use of super-orbital expansion tubes for the experimental study of high enthalpy reacting flows.

We make use of spectroscopic, interferometric and fluorescence approaches in order to obtain measurements that can be develop our understanding of these flows and for use in comparing with advanced numerical simulations. This is a particularly challenging and unique environment in which to make such measurements due to its short duration (~ 50 ms), high temperature (~10,000 K) and low density. We develop and apply optical imaging and measurement techniques to characterise high temperature hypersonic flow.

Development of advanced optical diagnostics for high enthalpy flows in superorbital expansion tubes.