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CFD investigation of the VLM-1 interstage

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CFD investigation of the VLM-1 interstage

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dc.contributor.advisor Buffetti, Barbara es_ES
dc.contributor.advisor Hoyas Calvo, Sergio es_ES
dc.contributor.author Fabra Pérez, Miguel es_ES
dc.date.accessioned 2015-05-08T07:54:17Z
dc.date.available 2015-05-08T07:54:17Z
dc.date.created 2014-09-30
dc.date.issued 2015-05-08
dc.identifier.uri http://hdl.handle.net/10251/49914
dc.description.abstract The Hot Separation staging method is supposed to provide an e cient separation of the rocket stages. Nevertheless, it requires a non-conventional con guration of the interstage that includes a grid and a plume de ector for the lower stage. The Brazilian launcher VLM-1 is designed to employ this staging method and therefore, aerodynamic studies have to be accomplished in order to investigate the ow eld within the interstage. The aim of the presented work is the prediction of the drag coe cient of the VLM-1, considering all rocket components. Three main numerical studies have been performed applying the ow solver TAU for the Qmax and Hot Separation trajectory point which correspond to a Mach number of 1.55 and 2.16, respectively. The rst analysis concerns the estimation of the drag coe cient for each component of the launcher, considering the contribution of the body, ns and base for a closed con guration of the rocket (without interstage) for the in ow conditions with an angle of attack of 3:3 . The other two are parametric studies performed for a 2D-axisymmetric model. One is aimed to identify the best de ector geometry, inducing the highest drag on the rst stage at the Hot Separation trajectory point. The last study investigates the in uence on the drag of the di erent interstage clearance and grid models, comparing the results also with the one obtained for the open con guration (open interstage, without grid). These studies have been performed for a non-viscous ow. In order to estimate the inaccuracies introduced by the hypotheses taken, two extra studies have been accomplished for both 3D and viscous simulations. The results of these studies have been analyzed separately. On the one hand, the de ector study has shown that the best con guration, among the ones studied, is the conic de ector with the lowest volume. On the other hand, the drag coe cient for all rocket con gurations has been analyzed in order to combine the results and to predict the drag of the VLM-1 for the angles of attack of 0:0 and 3:3 at both trajectory points. The drag prediction has been accomplished taking into account also the results for the 3D and viscous simulations. From these estimation, three main conclusions have been made. First, the VLM-1 with interstage grid provides a drag coe cient more similar to the one for the closed interstage con guration than to the one for the open interstage without grid. Second, the clearance length has a low in uence on the drag coe cient for the interstage con gurations with grid. Third, the higher the number of elements of the interstage grid, the lower is the drag coe cient. es_ES
dc.description.abstract Puedes encontrar el trabajo académico en la biblioteca de la ETSID (P E-PFC/10082) es_ES
dc.format.extent 138 es_ES
dc.language Inglés es_ES
dc.rights Reserva de todos los derechos es_ES
dc.subject Hot Separation - FITH staging es_ES
dc.subject Rocket es_ES
dc.subject Supersonic aerodynamics es_ES
dc.subject CFD es_ES
dc.subject Aerodynamic prediction es_ES
dc.subject VLM-1 es_ES
dc.subject.classification INGENIERIA AEROESPACIAL es_ES
dc.subject.other Grado en Ingeniería Aeroespacial-Grau en Enginyeria Aeroespacial es_ES
dc.title CFD investigation of the VLM-1 interstage es_ES
dc.type Proyecto/Trabajo fin de carrera/grado es_ES
dc.rights.accessRights Cerrado es_ES
dc.contributor.affiliation Universitat Politècnica de València. Escuela Técnica Superior de Ingeniería del Diseño - Escola Tècnica Superior d'Enginyeria del Disseny es_ES
dc.description.bibliographicCitation Fabra Pérez, M. (2014). CFD investigation of the VLM-1 interstage. http://hdl.handle.net/10251/49914. es_ES
dc.description.accrualMethod Archivo delegado es_ES


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