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

Paredes Gonzalez, Pedro and Theofilis, Vassilios (2013). Accurate Parabolic Navier-Stokes solutions of the supersonic flow around and elliptic cone. In: "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.

Description

Title: Accurate Parabolic Navier-Stokes solutions of the supersonic flow around and elliptic cone
Author/s:
  • Paredes Gonzalez, Pedro
  • Theofilis, Vassilios
Item Type: Presentation at Congress or Conference (Article)
Event Title: 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
Event Dates: 07/01/2013 - 10/01/2013
Event Location: Grapevine, TX, USA
Title of Book: AIAA 2013-0670
Date: 7 January 2013
Subjects:
Faculty: E.T.S.I. Aeronáuticos (UPM)
Department: Motopropulsión y Termofluidodinámica [hasta 2014]
Creative Commons Licenses: Recognition - No derivative works - Non commercial

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Abstract

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

More information

Item ID: 30169
DC Identifier: http://oa.upm.es/30169/
OAI Identifier: oai:oa.upm.es:30169
DOI: 10.2514/6.2013-0670
Official URL: http://arc.aiaa.org/doi/abs/10.2514/6.2013-670
Deposited by: Memoria Investigacion
Deposited on: 03 Nov 2014 18:13
Last Modified: 27 Apr 2016 07:31
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