Buttsworth, D. R. (2009) Nitrous oxide decomposition for supersonic combustion experiments in the USQ Ludwieg Tube facility. In: Australian Combustion Symposium 2009 (ACS09), 2-4 Dec 2009, Brisbane, Australia.
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Wind tunnel facilities are required to support the development of the scramjet engine. The performance of a short duration wind tunnel which uses the thermal decomposition of nitrous oxide to augment the flow stagnation enthalpy is simulated in the present work. In its normal model of operation, the wind tunnel being considered uses a free piston compression process to compress the test gas to a moderate stagnation temperature and pressure, suitable for cold flow hypersonic aerodynamics experiments. However, by introducing a mixture of nitrous oxide and nitrogen ahead of the piston, it should be possible to provide a test gas which closely simulates the properties of air. A simulation which models the thermo-chemistry of the free piston compression process with nitrous oxide is described. Results indicate that relatively large magnitude fluctuations in the test gas are likely to arise due to the rapid decomposition process, rendering the compressed gas unsuitable for supersonic combustion testing. Piston braking or some other change to the configuration would be necessary in order to successfully use nitrous oxide decomposition to enhance the enthalpy of the test gas.
|Item Type:||Conference or Workshop Item (Commonwealth Reporting Category E) (Paper)|
|Additional Information:||No evidence of copyright restrictions.|
|Uncontrolled Keywords:||nitrous oxide; thermal decomposition; short duration wind tunnel|
|Depositing User:||Assoc Prof David Buttsworth|
|Date Deposited:||23 Feb 2010 09:56|
|Last Modified:||02 Jul 2013 23:40|
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