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dc.contributor.authorNavó, Alex
dc.contributor.authorBergadà Granyó, Josep Maria
dc.contributor.otherUniversitat Politècnica de Catalunya. Departament de Mecànica de Fluids
dc.date.accessioned2020-12-03T12:32:01Z
dc.date.available2020-12-03T12:32:01Z
dc.date.issued2020-11-19
dc.identifier.citationNavó, A.; Bergadà, J.M. Aerodynamic study of the NASA's X-43A hypersonic aircraft. "Applied sciences", 19 Novembre 2020, vol. 10, núm. 22, p. 8211:1-8211:23.
dc.identifier.issn2076-3417
dc.identifier.urihttp://hdl.handle.net/2117/333858
dc.description.abstractA 2D aerodynamic study of the NASA’s X-43A hypersonic aircraft is developed using two different approaches. The first one is analytical and based on the resolution of the oblique shock wave and Prandtl–Meyer expansion wave theories supported by an in-house program and considering a simplified aircraft’s design. The second approach involves the use of a Computational Fluid Dynamics (CFD) package, OpenFOAM and the real shape of the aircraft. The aerodynamic characteristics defined as the lift and drag coefficients, the aerodynamic efficiency and the pitching moment coefficient are calculated for different angles of attack. Evaluations are made for an incident Mach number of 7 and an altitude of 30 km. For both methodologies, the required angles of attack to achieve a Vertical Force Balance (VFB) and a completely zero pitching moment conditions are considered. In addition, an analysis to optimise the nose configuration of the aircraft is performed. The mass flow rate throughout the scramjet as a function of the angle of attack is also presented in the CFD model in addition to the pressure, density, temperature and Mach fields. Before presenting the corresponding results, a comparison between the aerodynamic coefficients in terms of the angle of attack of both models is carried out in order to properly validate the CFD model. The paper clarifies the requirements needed to make sure that both oblique shock waves originating from the leading edge meet just at the scramjet inlet clarifying the advantages of fulfilling such condition
dc.language.isoeng
dc.publisherMultidisciplinary Digital Publishing Institute
dc.rightsAttribution 3.0 Spain
dc.rights.urihttp://creativecommons.org/licenses/by/3.0/es/
dc.subjectÀrees temàtiques de la UPC::Enginyeria mecànica::Mecànica de fluids
dc.subject.lcshComputational fluid dynamics
dc.subject.lcshAerodynamics
dc.subject.lcshGas dynamics
dc.subject.lcshAerodynamics, Hypersonic
dc.subject.lcshX-43A (Hypersonic plane)
dc.subject.lcshDrone aircraft
dc.subject.otherX-43A
dc.subject.otherComputational fluid dynamics (CFD)
dc.subject.otherAerodynamics
dc.subject.otherCompressible flow
dc.subject.otherHypersonic flow
dc.titleAerodynamic study of the NASA’s X-43A hypersonic aircraft
dc.typeArticle
dc.subject.lemacDinàmica de fluids computacional
dc.subject.lemacAerodinàmica
dc.subject.lemacDinàmica de gasos
dc.subject.lemacAerodinàmica hipersònica
dc.subject.lemacAvions no tripulats
dc.contributor.groupUniversitat Politècnica de Catalunya. TUAREG - Turbulence and Aerodynamics in Mechanical and Aerospace Engineering Research Group
dc.identifier.doi10.3390/app10228211
dc.relation.publisherversionhttps://www.mdpi.com/2076-3417/10/22/8211
dc.rights.accessOpen Access
local.identifier.drac29930127
dc.description.versionPostprint (published version)
local.citation.authorNavó, A.; Bergadà, J.M.
local.citation.publicationNameApplied sciences
local.citation.volume10
local.citation.number22
local.citation.startingPage8211:1
local.citation.endingPage8211:23


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Attribution 3.0 Spain
Except where otherwise noted, content on this work is licensed under a Creative Commons license : Attribution 3.0 Spain