Accurate Parabolic Navier-Stokes solutions of the supersonic flow around and elliptic cone

Paredes Gonzalez, Pedro y Theofilis, Vassilios (2013). Accurate Parabolic Navier-Stokes solutions of the supersonic flow around and elliptic cone. En: "51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition", 07/01/2013 - 10/01/2013, Grapevine, TX, USA. pp.. https://doi.org/10.2514/6.2013-0670.

Descripción

Título: Accurate Parabolic Navier-Stokes solutions of the supersonic flow around and elliptic cone
Autor/es:
  • Paredes Gonzalez, Pedro
  • Theofilis, Vassilios
Tipo de Documento: Ponencia en Congreso o Jornada (Artículo)
Título del Evento: 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
Fechas del Evento: 07/01/2013 - 10/01/2013
Lugar del Evento: Grapevine, TX, USA
Título del Libro: AIAA 2013-0670
Fecha: 7 Enero 2013
Materias:
Escuela: E.T.S.I. Aeronáuticos (UPM) [antigua denominación]
Departamento: Motopropulsión y Termofluidodinámica [hasta 2014]
Licencias Creative Commons: Reconocimiento - Sin obra derivada - No comercial

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Resumen

Flows of relevance to new generation aerospace vehicles exist, which are weakly dependent on the streamwise direction and strongly dependent on the other two spatial directions, such as the flow around the (flattened) nose of the vehicle and the associated elliptic cone model. Exploiting these characteristics, a parabolic integration of the Navier-Stokes equations is more appropriate than solution of the full equations, resulting in the so-called Parabolic Navier-Stokes (PNS). This approach not only is the best candidate, in terms of computational efficiency and accuracy, for the computation of steady base flows with the appointed properties, but also permits performing instability analysis and laminar-turbulent transition studies a-posteriori to the base flow computation. This is to be contrasted with the alternative approach of using order-of-magnitude more expensive spatial Direct Numerical Simulations (DNS) for the description of the transition process. The PNS equations used here have been formulated for an arbitrary coordinate transformation and the spatial discretization is performed using a novel stable high-order finite-difference-based numerical scheme, ensuring the recovery of highly accurate solutions using modest computing resources. For verification purposes, the boundary layer solution around a circular cone at zero angle of attack is compared in the incompressible limit with theoretical profiles. Also, the recovered shock wave angle at supersonic conditions is compared with theoretical predictions in the same circular-base cone geometry. Finally, the entire flow field, including shock position and compressible boundary layer around a 2:1 elliptic cone is recovered at Mach numbers 3 and 4

Más información

ID de Registro: 30169
Identificador DC: http://oa.upm.es/30169/
Identificador OAI: oai:oa.upm.es:30169
Identificador DOI: 10.2514/6.2013-0670
URL Oficial: http://arc.aiaa.org/doi/abs/10.2514/6.2013-670
Depositado por: Memoria Investigacion
Depositado el: 03 Nov 2014 18:13
Ultima Modificación: 27 Abr 2016 07:31
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