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Compressibility effects for the AGARD-B model

Tuling, S.; Tuling, Sean; Vallabh, B.; Morelli, M. F.

Authors

Sean Tuling Sean.Tuling@uwe.ac.uk
Senior Lecturer in Aerospace Engineering

Sean Tuling Sean.Tuling@uwe.ac.uk
Senior Lecturer in Aerospace Engineering

B. Vallabh

M. F. Morelli



Abstract

A numerical study of the flow topologies over the 60° delta wing of the AGARD-B model at Mach 0.80 has revealed that vortex bursting occurs between 13°-15° angle of attack, while vortex separation occurs above 18°. These aerodynamic features have been identified as additional comparison criteria which need to be replicated for facilities using the model for calibration or inter-tunnel comparison purposes. The numerical simulations were performed using ANSYS Fluent V13, a structured mesh with near wall treatment and the Spalart-Allmaras and κ-ω SST turbulence models, and validated experimentally in a 5’x5’ transonic facility. Other aspects not previously identified or studied are firstly a recovery shock between the primary and secondary vortex that exists only when vortex bursting occurs, and secondly the lack of a shock between the wing and vortex when the flow topology corresponds to the centreline shock region as observed in other studies.

Citation

Tuling, S., Vallabh, B., & Morelli, M. F. (2015). Compressibility effects for the AGARD-B model. Aeronautical Journal, 119(1214), 543-552. https://doi.org/10.1017/S0001924000010605

Journal Article Type Article
Acceptance Date Sep 15, 2014
Online Publication Date Jan 27, 2016
Publication Date Jan 1, 2015
Journal The Aeronautical Journal
Print ISSN 0001-9240
Publisher Cambridge University Press (CUP)
Peer Reviewed Peer Reviewed
Volume 119
Issue 1214
Pages 543-552
DOI https://doi.org/10.1017/S0001924000010605
Keywords AGARD-B, vortex bursting, compressibility
Public URL https://uwe-repository.worktribe.com/output/844843
Publisher URL http://dx.doi.org/10.1017/S0001924000010605
Additional Information Corporate Creators : Council for Scientific and Industrial Research

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