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Compressibility effects for the AGARD-B model

Published online by Cambridge University Press:  27 January 2016

S. Tuling ,
B. Vallabh  and
M.F. Morelli
B. Vallabh
Affiliation:
CSIR, Pretoria, South Africa
M.F. Morelli
Affiliation:
CSIR, Pretoria, South Africa
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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′ × 5′ 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.

Type
Research Article
Information
The Aeronautical Journal , Volume 119 , Issue 1214 , April 2015 , pp. 543 - 552
Copyright
Copyright © Royal Aeronautical Society 2015

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