Please use this identifier to cite or link to this item: https://gnanaganga.inflibnet.ac.in:8443/jspui/handle/123456789/16110
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dc.contributor.authorDnyandeo, Raut Adesh-
dc.contributor.authorPatel, Bindu B-
dc.contributor.authorSurakshaa, V C-
dc.contributor.authorJoseph, Athul-
dc.date.accessioned2024-07-22T03:50:51Z-
dc.date.available2024-07-22T03:50:51Z-
dc.date.issued2024-05-01-
dc.identifier.citation47p.en_US
dc.identifier.urihttps://gnanaganga.inflibnet.ac.in:8443/jspui/handle/123456789/16110-
dc.description.abstractTo improve the single stage rocket's current performance, new rocket designs are being used. However, the concept of the aerospike nozzle, which has been developed since the 1950s, has not been applied to a launch platform. The aerospike nozzle is more efficient than other nozzle types because of its geometry, which allows it to change its outer jet boundary in response to changes in its surroundings. The nozzle contour's coordinates are obtained using MATLAB and a straightforward approximation technique. The flow behaviour of an aerospike nozzle was analysed in Ansys software by applying various boundary conditions. The nozzle was designed in CATIA V5 with some assumptions. Additionally, these designs were simulated for various pressure outlet conditions in order to assess the effectiveness of the full-length spike at various altitudes. The outcomes were then compared between the Bell nozzle and the currently in use aerospike nozzleen_US
dc.language.isoenen_US
dc.publisherAlliance College of Engineering and Design, Alliance Universityen_US
dc.relation.ispartofseriesAE_G05_2024 [20030141AE006; 20030141AE011; 20030141AE016]-
dc.subjectMatlaben_US
dc.subjectRocket Designsen_US
dc.subjectAnsys Softwareen_US
dc.titleComputational Exploration of Flow Field Within An Aerospike Nozzleen_US
dc.typeOtheren_US
Appears in Collections:Dissertations - Alliance College of Engineering & Design

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