Compressibility effects for the AGARD-B model

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

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.

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