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Numerical experiment with inviscid vortex‐stretched flow around a cranked Delta wing: supersonic speed

Arthur Rizzi (FFA The Aeronautical Research Institute of Sweden, S‐161 11 Bromma, Sweden)
Charles J. Purcell (ETA Systems, Inc., St. Paul, MN 551 08, USA)

Engineering Computations

ISSN: 0264-4401

Article publication date: 1 March 1986

49

Abstract

A numerical method that solves the Euler equations for compressible flow is used to study vortex stretching. The particular case simulated is supersonic flow M∞=1.2 α=10 degrees around the twisted and cambered cranked‐and‐cropped TKF delta wing of MBB. This geometry induces multiple leading‐edge vortices in a straining velocity field that brings about flow instabilities but the result is a state of statistical equilibrium. The discretization contains over 600,000 cells and offers sufficient degrees of freedom in the solution to resolve the small‐scale unstable modes that lead to disordered vortex flow.

Citation

Rizzi, A. and Purcell, C.J. (1986), "Numerical experiment with inviscid vortex‐stretched flow around a cranked Delta wing: supersonic speed", Engineering Computations, Vol. 3 No. 3, pp. 230-234. https://doi.org/10.1108/eb023661

Publisher

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MCB UP Ltd

Copyright © 1986, MCB UP Limited

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