Design and Optimization of a Notional Scramjet by Means of Stream Thrust Analysis and Design of Experiments

dc.authorscopusid 57203990469
dc.authorscopusid 56353249900
dc.authorscopusid 24400712600
dc.contributor.author Akpolat,M.T.
dc.contributor.author Toker,K.A.
dc.contributor.author Genç,M.S.
dc.contributor.other Airframe and Powerplant Maintenance
dc.date.accessioned 2024-07-05T15:44:07Z
dc.date.available 2024-07-05T15:44:07Z
dc.date.issued 2014
dc.department Atılım University en_US
dc.department-temp Akpolat M.T., Atilim University Civil Aviation School, 06836 Incek Golbasi, Ankara, Turkey, Wind Engineering and Aerodynamics Research Laboratory, Department of Energy Systems Engineering, Erciyes University, Kayseri, Turkey; Toker K.A., Roketsan Missiles INC., Elmadag, Ankara, Turkey; Genç M.S., Wind Engineering and Aerodynamics Research Laboratory, Department of Energy Systems Engineering, Erciyes University, Kayseri, Turkey en_US
dc.description Airbus; Boeing; Dunmore; et al; Georgia Innovation Aerospace; Lockheed Martin en_US
dc.description.abstract Within the scope of this study, a 0-dimensional code is developed by using Stream Thrust Analysis in order to evaluate scramjet cycle performance with respect to selected performance parameters (specific impulse, overall efficiency) and combustion chamber exit temperature. By using the results of this code an analysis employing "Design of Experiments" (DoE) is performed to determine the most effective input parameters and/or interactions on the scramjet performance. The results showed that most effective input parameter for all of the selected parameters is fuel/air ratio. Selected parameters are evaluated first individually then simultaneously. The purpose of evaluating the performance parameters simultaneously is to determine the input parameter set which gives the highest values of specific impulse and overall efficiency while giving the lowest value of combustion chamber exit temperature. As a result the input parameter sets for different cases are determined. en_US
dc.identifier.citationcount 0
dc.identifier.doi 10.2514/6.2014-2788
dc.identifier.isbn 978-162410284-4
dc.identifier.scopus 2-s2.0-85088181127
dc.identifier.uri https://doi.org/10.2514/6.2014-2788
dc.identifier.uri https://hdl.handle.net/20.500.14411/3727
dc.institutionauthor Akpolat, Muhiddin Tuğrul
dc.institutionauthor Toker, Kemal Atılgan
dc.language.iso en en_US
dc.publisher American Institute of Aeronautics and Astronautics Inc. en_US
dc.relation.ispartof AIAA AVIATION 2014 -19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference -- AIAA AVIATION 2014 -19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2014 -- 16 June 2014 through 20 June 2014 -- Atlanta, GA -- 107455 en_US
dc.relation.publicationcategory Konferans Öğesi - Uluslararası - Kurum Öğretim Elemanı en_US
dc.rights info:eu-repo/semantics/closedAccess en_US
dc.scopus.citedbyCount 0
dc.subject [No Keyword Available] en_US
dc.title Design and Optimization of a Notional Scramjet by Means of Stream Thrust Analysis and Design of Experiments en_US
dc.type Conference Object en_US
dspace.entity.type Publication
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